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3. Mission and SystemOverview

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3.1 Introduction

Previous studies of human exploration ofMars have tended to focus on spacecraft andflight, rather than on what the crew would doon the surface. The Reference Mission takesthe point of view that surface exploration isthe key to the mission, both for science andfor evaluation of the potential for settlement.As a consequence, the Reference Missionarchitecture allows for a robust surfacecapability with significant performancemargins: crews will explore in the vicinity ofthe outpost out to a few hundred kilometers,will be able to study materials in situ and in asurface laboratory, and will iterate theirfindings with their exploration plan. Inaddition, the development and demonstrationof the key technologies required to testsettlement issues will provide a substantialworkload. To make surface explorationeffective, the supporting systems (such asEMU, life support, vehicles, robotics) must behighly reliable, highly autonomous, andhighly responsive to the needs of the crew.Some needs may not be anticipated duringcrew preparation and training, which willsignificantly challenge the management andoperations systems.

An infinite number of designs arepossible for a mission of this type. Theapproach taken here is based on two generalprinciples.

•A hierarchy of requirements (startingfrom mission objectives) is followed,which, as they gain greater depth anddefinition, merge with the proposedimplementation through a set of systemspecifications (note that the ReferenceMission has followed these requirementsdown to the system level only).

•A reasonable number of alternatives willbe considered, through trade studies ateach level of definition allowingcomparisons and choices.

3.1.1 Mission Objectives

Section 1 of this report discussed a seriesof workshops conducted by NASA to define aset of objectives and supporting rationale fora Mars exploration program. The workshopattendees (see Table 2-1) identified andrecommended for adoption three objectivesfor analysis of a Mars exploration programand the first piloted missions in that program.

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They are to conduct:

•Human missions to Mars and verify thatpeople can ultimately inhabit Mars.

•Applied scientific research for usingmartian resources to augment life-sustaining systems.

•Basic scientific research to gain newknowledge about the solar system’sorigin and history.

A Mars Study Team composed of NASApersonnel representing most NASA fieldcenters (see Table 2-2) used inputs from theadopted objectives to construct the ReferenceMission. In addition, the Study Teamrecognized that past mission studies hadcharacterized piloted Mars missions asinherently difficult and exorbitantlyexpensive. Therefore, the Mars Study Teamadded three objectives. These were to:

•Challenge the notion that humanexploration of Mars is a 30-year programthat will cost hundreds of billions ofdollars.

•Challenge the traditional technicalobstacles associated with sendinghumans to Mars.

•Identify relevant technologydevelopment and investmentopportunities.

3.1.2 Surface Mission ImplementationRequirements

To satisfy the objectives for the ReferenceMission, the Mars Study Team developed aseries of capabilities and demonstrations thatshould be accomplished during surfacemission activities. Table 3.1 defines theactivities and capabilities that must exist tomeet the first three program objectives to thenext level of detail. The three objectives addedby the Study Team are useful in selectingamong feasible mission implementationoptions that could be put forth to satisfy thecapabilities and demonstrations listed in thetable.

3.1.2.1 Conduct Human Missions to Mars

From the point of view of the surfacemission, conducting human missions impliesthat the capability for humans to live andwork effectively on the surface of Mars mustbe demonstrated. This includes several sub-objectives to:

•Define a set of tasks of value for humansto perform on Mars and provide thetools to carry out the tasks.

•Support the humans with highly reliablesystems.

•Provide a risk environment that willmaximize the probability ofaccomplishing mission objectives.

•Provide both the capability and therationale to continue the surfaceexploration beyond the first mission.

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These then require a set of functionalcapabilities on the surface, including habitats,surface mobility systems, and supportingsystems (such as power and communicationssystems).

3.1.2.2 Conduct Applied Scientific Researchto Use Mars Resources to Augment Life-Sustaining Systems

This objective will require that anassessment be made of the location andavailability of specific resources (such aswater) that are useful for human habitation ortransportation. It will also require that

effective system designs be developed anddemonstrated to extract and use indigenousresources. Opportunities exist to useindigenous resources as demonstrations inthe life support subsystem, in energy systemsas fuel or energy storage, and as propellantfor spacecraft. These may eventually developinto essential systems for the preservation ofthe outpost. In addition, the followinghabitation activities and demonstrationssatisfy the first and second objectives.

•Demonstrate that martian habitabilityhas no fundamental limitations due touniquely martian characteristics such as

Table 3-1 Capabilities and Demonstrations for Surface Mission Activities

Conduct Human Missions to Marsa. Land people on Mars and return them safely to Earth.b. Effectively perform useful work on the surface of Mars.c. Support people on Mars for 2 years or more without resupply.d. Support people away from Earth for periods of time consistent with Mars mission durationss

(2 to 3 years)e. Manage space operations capabilities including communications, data management, and

operations planning to accommodate both routine and contingency mission operationalsituations; and understand abort modes from surface or space contingencies.

f. Identify the characteristics of space transportation and surface operations systems consistentwith sustaining a long-term program at affordable cost.

Conduct Applied Science Research to Use Mars Resources to Augment Life-Sustaining Systemsa. Catalog the global distribution of life support, propellant, and construction materials

(hydrogen, oxygen, nitrogen, phosphorous, potassium, magnesium, iron, etc.) on Mars.b. Develop effective system designs and processes for using in situ materials to replace products

that otherwise would have to be provided from Earth.Conduct Basic Science Research to Gain New Knowledge About the Solar System’s Origin andHistorya. Using robotic and human investigations, gain significant insights into the history of the

atmosphere, the planet’s geological evolution, and the possible evolution of life.b. Identify suitable venues at Mars, in the martian system, and during Earth-Mars transits for

other science measurements.

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low gravity, absence of a magnetic field,soil toxicity, or the radiationenvironment.

•Demonstrate that self-sufficiency can beachieved on the local scale of a Marsbase. This includes providing areasonable quality of life and reasonablylow risk for the crews, and shouldinclude operating a bioregenerative lifesupport system capable of producingfood and recycling air and water.

•Determine the potential for expansion ofbase capabilities using indigenousresources. This would include thesuccessful extraction of life supportconsumables from the martianenvironment and storage for later use.

•Investigate the biological adaptation ofrepresentative plant, animal, andmicrobial species to the martianenvironment over multiple generations.

These activities and demonstrations areaimed at establishing the feasibility andapproach required to move beyond theexploratory phase toward the development oflong-term activities on the planet. Theyinfluence the selection of elements that areincluded in the surface systems (habitats,mobility, life support, power, andcommunications systems).

To the support facilities identified in theprevious section must be added explorationsystems (orbital or surface), resourceextraction and handling systems, and

additional systems for producing food andrecycling air and water.

3.1.2.3 Conduct Basic Scientific Research toGain New Knowledge About the SolarSystem’s Origin and History

This will require that a variety ofscientific explorations and laboratoryassessments be carried out on the surface ofMars by both humans and robots. Thescientific research will not be conductedcompletely at any one site, which will create aneed for crew member mobility andtransportation systems to supportexploration, the specialized tools requiredoutside the outpost to collect and documentmaterials, and the facilities inside the outpostto perform analyses.

The principal science activities anddemonstrations for Mars exploration includeanswering the following questions.

•Has Mars been a home for life?

This set of objectives will combine fieldand laboratory investigations in geology,paleontology, biology, and chemistry. Theunderlying assumption is that this questionwill not have been answered by previousrobotic Mars exploration programs, and thebest way to get an answer is throughjudicious use of humans on Mars as fieldgeologists and laboratory analysts. Recentevidence indicating past life on Mars found ina martian meteorite has placed increasedemphasis on this question (McKay, et al.,1996).

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•What are the origin and evolution ofMars, particularly its atmosphere, andwhat does it tell us about Earth?

This set of objectives involves geologyand geophysics, atmospheric science,meteorology and climatology, and chemistry.Iterative sampling of geological units will berequired as well as monitoring of a globalnetwork of meteorological stations. (A globalnetwork will most likely be established byrobotic elements of the program.)

•What resources are available on Mars?

The resource discovery and verificationof accessibility will require investigations ingeology, atmospheric science, and chemistry.A general strategy for accomplishing this willbegin with a global mapping (from orbit) ofselected elemental and mineralogicalabundances. This activity is best suited for arobotic spacecraft sent prior to the flight ofthe first human crew. Robotic missions arealso likely for verifying the abundances andmaking an initial assessment of accessibilityof the resources. The data gathered will alsobe important for selecting likely sites for thesurface outpost to be used by human crews.

3.1.2.4 Surface Operations Philosophy

In addition to the facilities andequipment mentioned above, the crew musthave a general operating philosophy forconducting activities, demonstrations, andexperiments on the surface. The targetedinvestigations to be carried out from the Marsoutpost depend on humans and automated

rover sample collectors having accessibility tointeresting or significant sites at increasingdistances from the outpost. Figure 3-1 showsa photomosaic of the Candor region of theValles Marineris in which the location of anoutpost could address fundamental questionsof Mars’ origin and history. This region islocated roughly between 70 degrees and 75degrees west longitude and between 2.5degrees and 7.5 degrees south latitude. Ageneral geological map of the region of theoutpost site should be prepared using datagathered by robotic missions prior to selectingand occupying the initial site.

Once the outpost is established,exploration activity will consist of surfaceobservations made by robotic vehicles andhuman explorers, collection of samples, andexamination of samples in the outpostlaboratory. Crews will be given broadly statedscientific questions or exploration objectivesto be addressed in relatively large regionsnear the outpost site. Operations will not beas highly choreographed over the 600-daysurface stay-time as they are for currentspaceflight missions. The crews and Earth-based supporting investigators will plancampaigns lasting days or weeks, eventuallyextending to months, but always with theassumption that replanning may be necessarybased on discoveries made. It is likely that astrategy of general reconnaissance followedby detailed investigations will be followed.The outpost laboratory will be outfitted toprovide mineralogical and chemical analysesand, depending on technical development, it

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Figure 3-1 A regional map illustrating potential locations for a Mars outpost.

DesiredLandingArea

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may be possible to perform simple kinds ofgeochronologic analysis. The purpose of thesestudies will be to support the fieldinvestigations, answer “sharper” questions,and allow human explorers to narrow theirfocus to the sites of optimum samplecollection. Ultimately, selected samples willbe returned to Earth for more detailedanalysis.

Science equipment, experiments, andtools must be proven in order for theexploration and science objectives of themissions to be accomplished, and theirselection is at the core of the argument thathumans can effectively perform scientificresearch on the planet. Failure to equiphumans properly will be a failure to takeadvantage of their unique potential. Over-equipping them may be counterproductive aswell, at least from the cost aspect oftransporting unneeded equipment to Mars.The exploration and science objectives to beperformed on the surface can be broken intofour categories: field work, teleroboticexploration, laboratory and intravehicularactivity experiments, and preparation ofmaterials for return to Earth.

•Observations related to exobiology,geology, and martian atmosphere studieswill be made by humans in the field.Samples and data will be collected andreturned to the outpost laboratory foranalysis. The information from theanalyses will be used to plan or replanfuture traverses as scientific andexploration questions are sharpened.

Information will be transmitted toscientists on Earth so they canparticipate in the replanning activity.Crews will also emplace geophysical andmeteorological instruments to measureinternal properties and atmosphericdynamics. Drilling short depths into thesurface should be standard capability. Atsome point it will be appropriate to drilldeeply into the surface to addressstratigraphic issues and to locate and tapinto water reservoirs.

•The Mars crews will also have thecapability to operate telerobotic systemsconducting even broader exploratorytasks using the ability to communicatewith and direct these systems in nearreal-time. Some teleoperated rovers(TROVs) may be emplaced before crewsarrive on Mars and may collect samplesfor assembly at the Mars outpost. TheTROVs may be designed to provideglobal access and may be able to returnsamples to the outpost from hundreds ofkilometers distance from the site. Theserobotic systems may also emplacegeophysical monitoring equipment suchas seismometers and meteorologicalstations.

•Scientific experiments will also beconducted that are uniquely suited tobeing performed on the surface of Mars.These will typically be experiments thatmake use of the natural martianenvironment (including reduced gravity)or involve interaction with martian

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surface materials. Studies will beperformed on biological systems, bestperformed in conjunction with anexperimental bioregenerative lifesupport system. The deployment of abioregenerative life support capabilitywill be an early activity after crewlanding. Although this system is notrequired to maintain the health andvitality of the crew, it will improve therobustness of the life support system andis important to the early objectives of theoutpost. Field samples will be studied inlaboratory facilities shared between thegeosciences, biosciences, and facilitiessupport systems. For example, analyticalsystems used to monitor organisms inthe biological life support system mayalso be used to monitor the environmentof the habitat in general. Some analyticalcapabilities (such as gaschromatographs) find use in bothgeological and biological analysis. Allsamples and data (geological, biological,medical, etc.) will be documented andcataloged for later research.

•One crew task will be to select andpackage samples for return to Earth formore detailed study. This will require thecreation of a minicuratorial facility andprocedures to ensure thatuncontaminated samples are returned toEarth.

As experience grows, the range of humanexploration will grow from the local to theregional. Regional expeditions, lasting several

weeks and using mobile facilities, may beconducted at intervals of a few months.Between these explorations, analysis in thelaboratory will continue. The crew will alsospend a significant portion of timemaintaining and ensuring the continuingfunctionality of life support and materialsprocessing systems and performingmaintenance on robotic vehicles and EVAsuits (systems should be designed to helpkeep these activities to a minimum).

Crew activities related to living onanother planet should be viewed not only asexperiments but also as activities necessary tocarry out the mission. With minormodifications in hardware and software,ordinary experiences can be used to provideobjective databases for understanding therequirements for human settlement.

To optimize the performance of themission, it will be necessary to pick a landingsite primarily on the basis of satisfyingmission objectives. However, the landing sitemust be consistent with landing and surfaceoperational safety. Detailed maps of candidatelanding sites should be available to define thesafety and operational hazards of the site, aswell as to confirm access (by humans orrobotic vehicles) to scientifically interestinglocations. Depending on the results of priormissions, it would be desirable to site theoutpost where water can be readily extractedfrom minerals or from subsurface deposits.

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3.1.3 Ground Rules and Assumptions

Translating these goals and objectivesinto specific missions and systems requiredadopting a number of guidelines andassumptions.

•Balance technical, programmatic,mission, and safety risks. Marsexploration will not be without risks.However, the risk mitigation philosophyas well as the acceptability of the missionconcept to the public, its elected leaders,and the crews will be critically importantin the technical and fiscal feasibility ofthese missions. Mars is not “3 daysaway,” and overcoming the temptationto look back to Earth to resolve eachcontingency situation may be the mostchallenging obstacle to overcome inembarking upon the human explorationof Mars.

•Provide an operationally simple missionapproach emphasizing the judicious useof common systems. For example, anintegrated mission in which a singlespacecraft with all elements needed tocarry out the complete mission islaunched from Earth and lands on Marsto conduct the long exploration programis not feasible due to launch massconsiderations alone. It is necessary todetermine the simplest and most reliableset of operations in space or on thesurface of Mars to bring all of thenecessary resources to the surface wherethey are to be used. A strategyemphasizing multiple uses for single

systems can potentially reduce the totalprogram costs and enhance crew safetyand system maintainability.

•Provide a flexible implementationstrategy. Mars missions are complex, somultiple pathways to the desiredobjectives have considerable value inensuring mission success.

•Limit the length of time the crew iscontinuously exposed to theinterplanetary space environment. Doingthis will reduce the physiological andpsychological effects on the crew andenhance their safety and productivity. Inaddition, the associated life scienceconcerns are partially mitigated. It isassumed that crews will arrive at Marsin good health, that full physicalcapability can be achieved within a fewdays, and that crew health andperformance can be maintainedthroughout the expedition.

•Define a robust planetary surfaceexploration capacity capable of safelyand productively supporting crews onthe surface of Mars for 500 to 600 dayseach mission. The provision of a robustsurface capability is a definingcharacteristic of the Reference Missionphilosophy. This is in contrast toprevious mission studies that haveadopted short stay-times for the first orfirst few human exploration missionsand focused attention principally onspace transportation.

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•Be able to live off the land. Thecapability to manufacture resources atMars, particularly propellants, has longbeen known to have significant leveragein terms of the amount of material thatmust be launched from Earth. It alsoprovides a risk reduction mechanism forthe crew when viewed as a cache of lifesupport consumables to back up thosebrought from Earth. Additional systemdevelopment effort will be required, butthe advantages outweigh the cost anddevelopment risk, particularly if theinfrastructure supports more than onehuman exploration expedition.

•Rely on reasonable advances inautomation to perform a significantamount of the routine activitiesthroughout the mission. This includes acapability to land, set up, operate, andmaintain many of the Mars surfacesystems needed by the crew prior totheir arrival.

•Ensure that management techniques areavailable and can be designed into aprogram implementation that cansubstantially reduce costs.

•Use the Earth-Mars launch opportunitiesoccurring from 2007 through 2014. A2009 launch represents the most difficultopportunity in the 15-year Earth-Marstrajectory cycle. By designing the spacetransportation systems for thisopportunity, particularly those systemsassociated with human flights, they canbe flown in any opportunity with faster

transit times for the crew or increasedpayload delivery capacity for cargo. Thisenhances program flexibility.

•Examine at least three human missionsto Mars. The initial investment to send ahuman crew to Mars is sufficient towarrant more than one or two missions.Each mission will return to the site of theinitial mission, with missions two andthree launching in the 2012 and 2014launch opportunities, respectively. Thisapproach permits an evolutionaryestablishment of capabilities on the Marssurface and is consistent with the statedgoals for human exploration of Mars.Although it is arguable that scientificdata could be enhanced by landing eachhuman mission at a different surface site,the goal of understanding how humanscould inhabit Mars seems more logicallydirected toward a single outpostapproach. This leaves global explorationto robotic explorers or perhaps laterhuman missions.

3.2 Risks and Risk MitigationStrategy

Several related but also separable aspectsof risk are associated with a Mars mission andmust be considered in designing theReference Mission. Reference Missionactivities will inevitably be hazardousbecause they are conducted far from home inextreme environments. However, the hazardscan be reduced by proper design andoperational protocols. Before a Mars

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exploration program is approved, it will benecessary to decide whether the elements ofrisk to the enterprise can be reduced to a levelconsistent with the investment in resourcesand human lives.

3.2.1 Risks to Human Life

Crews undertaking the humanexploration of Mars will encounter the activespace environment, the in-space environment,and the planetary surface environment.

The active space environment includeslaunch from Earth, maneuvers in near-Earthspace, launch on a trajectory to Mars, entryand landing on Mars, launch from Mars, Marsorbital maneuvers, launch on a trajectory toEarth, reentry of Earth’s atmosphere, andlanding on Earth. Because these are energeticevents, the risk is relatively high. In 100launches of United States manned spacecraftand a similar number of Russian spacecraft,the only fatal accidents have occurred inlaunch or landing. Once in space, theenvironment has been relatively benign.(Apollo 13 was an exception. En route to themoon, it experienced an equipment failurewhich jeopardized the crew. Because of thecharacteristics of the Earth-Moon trajectoriesand the spacecraft design, it was possible torecover the crew. This type of risk can beaddressed in part by the Mars explorationarchitecture, and can be different for humansand cargo.)

The quiescent in-space environment isrelatively benign from the point of view ofexplosions and other spacecraft accidents.

However, there are important and potentiallydeadly environmental hazards (such asradiation and meteoroid damage) which mustbe addressed. Two radiation hazards exist.First and most dangerous is the probability ofa solar proton event (SPE) which is likely tooccur during any Mars mission. Solar protonevents can rise to the level where an unshield-ed person can acquire a life threateningradiation dosage. However, shielding withmodest amounts of protective material canalleviate this problem. The task becomes oneof monitoring for events and taking shelter atthe appropriate time. Galactic cosmic rays, theother radiation hazard, occur in smallnumbers, are very energetic, and can causedeleterious effects over a long period of time.For astronauts in LEO, exposure to cosmicradiation has been limited to that level whichcould induce an additional 3 percent lifetimerisk of cancer (curable or incurable). Becauseof a policy that radiation hazards should bekept as low as reasonably achievable, space-craft and space operations must be designedto minimize exposure to cosmic rays. Thehealth risk today from radiation exposure ona trip to Mars cannot be calculated with anaccuracy greater than perhaps a factor of 10.The biomedical program at NASA has givenhigh priority to acquiring the necessary healthdata on HZE radiation, including the designshielding materials, radiation protectantmaterials, and SPE monitoring and warningsystems for the Mars crew. (For additionaldiscussion and explanation of this topic, seeNASA, 1992; Townsend, et al., 1990; andSimonsen, et al., 1990.)

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The planetary surface is the thirdenvironment which provides risks to crews.Because operational experience on Mars islimited, this environment is the leastunderstood. As the objective of humanexploration of Mars will be to spend time onthe surface of Mars, extensive EVA will berequired as part of the mission. EVAs willinvolve exiting and reentering pressurizedhabitats and conducting a variety of activitieson the surface in space suits or otherenclosures (including vehicles). In this area,accidents and equipment failures are thebiggest concerns. These risks must beaddressed by examining a combination ofdetailed information about the surfaceenvironment, designing and testinghardware, and training the crew. To someextent, EVA can be reduced or simplified byusing telerobotic aids operated by the crewfrom their habitat. (The risks associated withthe habitat itself are probably similar to thosefaced in free space, with somewhat morebenign radiation and thermal environments.)Finally, the presence of dust on Mars willpresent risks, or at least annoyances, tosurface operations. Robotic missions to Marsprior to human expeditions should improveunderstanding of the surface hazards crewswill encounter.

3.2.2 Risks to Mission Success

The risk of a Mars exploration mission ismeasured by the degree to which the programobjectives can be accomplished. A successful

trip to and from Mars, without accomplishingany surface exploration objectives, would beonly minimally successful. Mission risk isrelated to the integrated capability of the crewand their systems to conduct the mission. Forthe crew or the systems to fail to perform putsthe mission at risk of failure. On the humanside, this requires attention to health, safety,performance, and other attributes of aproductive crew. On the system side, thisrequires that systems have low failure rates,have robust backups for systems that may failor require repair, and be able to operatesuccessfully for the required period of themission. Strategies to minimize failure can bedesigned at the architecture level or at thesystem level.

3.2.3 Risks to Program Success

Program risk is a term that refers to theprogrammatic viability of the explorationprogram—that is, once the program has beenapproved, what are the risks that it will not becompleted and the exploration notundertaken? These are programmatic issuesthat in many cases seem less tractable thanthe technical risks. They can be influencedwhen management of the enterprise fails tomeet milestones on schedule and cost, whenunforeseen technical difficulties arise, orwhen political or economic conditionschange. They can be mitigated by soundprogram management, good planning, andadvocacy or constituency building on thepolitical side.

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3.2.4 Risk Mitigation Strategy

The riskiest part of the first explorationmissions to Mars may well be the risk ofaccident on launch from Earth, and theenergetic events of launches and landingsduring other phases of the mission are likelyto make up the remaining high risk parts ofthe mission. Yet, the environment on thesurface of Mars will be new and untried, themissions will be long, and the opportunitiesto make up for error small. Therefore, aconscious approach to minimizing risks onthe martian surface must be adopted. For astarting point, it is assumed that this riskmust be smaller than the combined risks of allof the energetic events. Design requirementswill have been developed with this in mind.

The strategy for reduction of risks on thesurface involves four levels of consideration.At the top level, the mission architectureprovides for assurance that all systems willoperate before crews are launched from Earth.The strategy must be flexible in allowingsubsequent robotic missions to replace anysystems shown not to be functional prior tosending crew. This, in turn, places designrequirements on the hardware to allowproblems to be identified, isolated, fixed inplace if possible, and bypassed if necessarythrough the addition of a parallel capabilitysent on a subsequent flight.

The second level of risk reductioninvolves providing redundancy through theoverlapping functional capabilities betweenvarious systems, the ability to repair any life-critical systems, and the provision of a

suitable suite of replacement systems asbackups to the prime systems. The followingpriorities are recommended.

•Crew health and safety are top priorityfor all mission elements and operations;life-critical systems are those absolutelyrequired to ensure the crew’s survival.This implies that life-critical systems willhave two backup levels of functionalredundancy; if the first two levels fail, thecrew will not be in jeopardy but will notbe able to complete all mission objectives.At least the first level of backup isautomated. (This is a fail operational/failoperational/fail-safe system.)

•Completing the defined mission to asatisfactory and productive level(mission-critical) is the second priority.This implies that mission-criticalobjectives will have one automatedbackup level. (This is a fail operational/fail-safe system.)

•Completing additional, possiblyunpredicted (mission-discretionary),tasks which add to the total productivityof the mission is third priority. The crewwill not be in jeopardy if the mission-discretionary systems fail, and a backupis not needed. (This is a fail-safe system.)

The systems contributing to this backupstrategy were assumed to be provided byeither real redundancy (multiple systems ofthe same type) or functional redundancy(systems of a different type which provide therequired function). Recoverability or

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reparability by the crew will provide yetadditional safety margins.

The third level of risk reduction involvesthe automation of systems including faultdetection, failure projection, and maintenanceactivities, and the provision of data thatdemonstrate current status and predict futurestates. Such systems are not only conservativeof crew time, but also more effective andprecise, particularly on routine monitoringand control tasks.

The fourth level of risk reduction isrelated to crew training and proficiency. Thebiggest concern in this area is that the crewwill be away from the traditional Earth-basedtraining environment for years at a time.Those areas with direct humaninvolvement—EVA, life support systems,high capacity power systems, propellantproduction and storage, mobile vehicles, andother complex facilities—all carry a high riskfor accident, particularly if training is notrecent or crew members becomeoverconfident. Crews will most likely berequired to participate in continuous tasktraining for safety awareness requirements.

3.3 Flight Crew

Humans are the most valuable missionasset for Mars exploration and must notbecome the weak link. The objective forhumans to spend up to 600 days on themartian surface places unprecedentedrequirements on the people and theirsupporting systems. Once committed to themission on launch from LEO, the crew must

be prepared to complete the full missionwithout further resupply from Earth.Unlimited resources cannot be providedwithin the constraints of budgets and missionperformance. Their resources will either bewith them or will have already been deliveredto or produced on Mars. So trade-offs must bemade between cost and comfort as well asperformance and risk. Crew self-sufficiency isrequired because of the long duration of theirmission and the fact that their distance fromEarth impedes or makes impossible thetraditional level of communications andsupport by controllers on Earth. The crewswill need their own skills and training andspecialized support systems to meet the newchallenges of the missions.

Crews should be selected who will agreeto conduct operational research willingly andopenly. Crew members should be selectedwho can relate their experiences back to Earthin an articulate and interesting manner, andthey should be given enough free time toappreciate the experience and the opportunityto be the first explorers of another planet.

Because the objectives of the missions areto learn about Mars and its capability tosupport humans in the future, there will be aminimum level of accomplishment belowwhich a viable program is not possible.Survival of humans on the trip there and backis not a sufficient program objective.

3.3.1 Crew Composition

The number of crew members to be takento Mars is an extremely important parameter

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for system design, because the scale of thehabitats, space transportation system, andother systems supporting the mission aredirectly related to the number of crewmembers. This, in turn, will have a directrelationship to the cost of the first missions.The size of the crew also is probably inverselyproportional to the amount of newtechnology which must be developed to allowall tasks to be performed. Because ofcommunication time delays between Earthand Mars, some functions that havepreviously been performed by people onEarth will be carried out autonomously or bycrew members. Generally, there will be a highdegree of automation required for routineoperations on the Mars journey to allow crewmembers to do specialized tasks.

For the Reference Mission study, it wasassumed that crew health and safety are offirst priority in successfully achieving missionobjectives and that the surface system designrequirements for operability, self-monitoring,maintenance, and repair will be consistentwith the identified minimum number of crewmembers. The crew size and composition wasdetermined in a top-down manner (objectives➝ functions ➝ skills ➝ number of crewmembers + system requirements) as thesystems have not been defined in a bottoms-up manner based on an operational analysisof the system.

The Mars Study Team workload analysisassumed that the crew would spend availabletime in either scientific endeavors orhabitation-related tasks. From that analysis,

lists of required skills were developed.Expertise is required in three principal areas.

•Command, control, and vehicle andfacility operations functions. Thesefunctions include command,management, and routine andcontingency operations (piloting andnavigation, system operations,housekeeping, maintenance, and repairof systems). Maintenance must beaccomplished for facility systems,human support systems (medicalfacilities, exercise equipment, etc.), EVAsystems, and science equipment.

•Scientific exploration and analysis. Thisarea includes field and laboratory tasksin geology, geochemistry, paleontology,or other disciplines associated withanswering the principal scientificquestions.

•Habitability tasks. These tasks includeproviding medical support; operatingthe bioregenerative life support systemexperiment; performing biological,botanical, agronomy, and ecologyinvestigations; and conducting otherexperiments directed at the long-termviability of human settlements on Mars.

The types of crew skills needed areshown in Table 3-2 (Clearwater, 1993). If eachskill is represented by one crew member, thecrew size would be too large. Personnel willhave to be trained or provided the tools toperform tasks which are not their specialty.

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Special skill requirements appear to be in theareas of medicine, engineering, andgeoscience.

•Medical treatment. In a 3-year mission, itis very likely that an accident or diseasewill occur. At least one medically trainedperson will be required as well as abackup who is capable of conducting

procedures under the direction ofmedical experts on Earth (throughtelemedicine).

•Engineer or technician. A person skilledin diagnosing, maintaining, andrepairing mechanical and electricalequipment will be essential. A highdegree of system autonomy, self-diagnosis, and self-repair is assumed forelectronic systems; however, the skill to

Table 3-2 Surface Mission Skills

Specialized Operations Focused and Services Objectives In-Common

GeologyGeochemistryPaleontologyGeophysics including Meteorology and Atmospheric Science

BiologyBotanyEcologyAgronomySocial Science

Management/planningCommunicationsComputer SciencesDatabase Management

Food Preparation• routine greenhouse operations• plants to ingredients• ingredients to food

Vehicle ControlNavigationTeleoperated Rover Control

Journalism

Housekeeping

Mechanical Systems Operations, Maintenance and Repair

Tool-Making

Electrical Systems Operations, Maintenance and Repair

Electronics Systems Operations,Maintenance and Repair

General Practice Medicine

Surgery Biomedicine

Psychology Psychology

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identify and fix problems, in conjunctionwith expert personnel on Earth, has beenrepeatedly demonstrated to be essentialfor space missions.

•Geologist-Biologist. A skilled fieldobserver-geologist-biologist is essentialto manage the bioregenerative lifesupport system experiment. All crewmembers should be trained observers,should be highly knowledgeable of themission science objectives, and should beable to contribute to the mission science.

Other factors will also contribute to thefinal determination of crew size: systemautonomy, simultaneous operations,contingency situations, human factors, andinternational participation.

•Electronic and mechanical equipmentmust be highly autonomous, self-maintained or crew-maintained, andpossibly self-repairing. The amount oftime taken to do routine operations mustbe minimized through system design. Inprinciple, the operation of supportingsystems (such as power, life support, insitu resource recovery) should betransparent to the crew. The bestapproach in this area is to define therequirement for technologicaldevelopment based on the missionrequirements for a given crew size.

•Simultaneous operations will berequired during the nominal mission. Allcrew members will be fully occupiedduring their assigned working hours,

and a minimum number of crewmembers will be required by thedistribution of tasks. For example, EVAsare likely to require at least two peopleoutside the habitat at any one time inorder to assist each other. A third personis likely to be required inside to monitorthe EVA activities and assist if necessary.If other tasks (repair, science,bioregenerative life support systemoperation) are required to be donesimultaneously, the number of crewmembers may need to be increased.

•Specific contingency situations andmission rules have not been establishedfor the Reference Mission because it istoo early in the design phase. However,the choice of what the crew will beallowed to do or not do can impact thesize of the crew. For example, duringexploration campaigns, mission rulesmay require that some portion of thecrew be left in the main habitat while theremainder of the crew is exploring in themobile unit. It will be necessary to havea backup crew to operate a rescuevehicle in case the mobile unit has aproblem. If the exploration crew requiresthree people, the requirement to haveone driver for a backup unit and one leftat the outpost implies a crew of not lessthan five.

•In terms of human factorsconsiderations, the psychologicaladjustment is more favorable in largercrews of six to eight than in smaller

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crews of three to five. However, thepsychological environment may be metby system and support provisions ratherthan by the crew size itself.

•It is conceivable that each country thatmakes a major contribution to aninternational Mars exploration missionwill demand representation on the crew.Currently, a Mars crew might bepatterned after the International SpaceStation with representatives from theUnited States, Russia, European SpaceAgency, and Japan. However, in anenterprise of this magnitude, ThirdWorld representatives might also beselected by the United Nations.

At a summary level, the five mostrelevant technical fields required by theexploration and habitation requirementsinclude mechanical engineer, electrical andelectronics engineer, geologist, life scientist,and physician-psychologist. These fieldsshould be represented by a specialist, with atleast one other crew member cross-trained asa backup. Crew members would also becross-trained for the responsibilities of a widevariety of support tasks as well as tasks ofcommand and communications.

The result of the workload analysisindicates that the surface mission can beconducted with a minimum crew of five,based on the technical skills required.However, loss or incapacitation of one ormore crew members could jeopardize mission

success. Therefore, a larger crew may berequired to address the risk issues. Currently,the Reference Mission is built on theassumption of a crew of six.

3.3.2 Crew Systems Requirements

To survive, the crew will need adequateshelter, including radiation protection;breathable, controlled, uncontaminatedatmosphere (in habitats, suits, andpressurized rovers); food and water; medicalservices; psychological support; and wastemanagement. During the 4- to 6-month transitto Mars, the chief problems will bemaintaining interpersonal relationshipsneeded for crew productivity andmaintaining physical and mentalconditioning in preparation for the surfacemission. On the Mars surface, the focus willturn to productivity in a new and harshenvironment. The transit environment islikely to be a training and conditioningenvironment, the surface environment iswhere the mission-critical tasks will be done.

For long-duration missions withinevitably high stress levels, the trade-offbetween cost and crew comfort must beweighed with special care. High qualityhabitats and environmental design featuresare critical to assuaging stress and increasingcrew performance—conditions that willgreatly increase the likelihood of missionsuccess. Providing little more than thecapability to survive invites mission failure.

Not all amenities need be provided onthe first mission. The program should be

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viewed as a sequence of steps which, overtime, will increase the amount of habitablespace on the surface, increase the amount oftime available to the crew to devote tomission objectives and personal activities,increase the amount of crew autonomy,improve the quality of food, increase access toprivacy, and increase the quality and quantityof communications with Earth. In addition,experience in Mars surface operations mayreduce some of the stresses associated withthe unfamiliarity of the environment.

The quality of life can be enhanced byaccess to and use of indigenous resources. Inthe near term, use of indigenous resourcesreduces some of the mission risks (creation ofcaches, use of local resources for radiationshielding, etc.). In the long term, use of localresources may allow more rapid expansion ofusable space. Achieving the capability toproduce water and oxygen from localresources may have physical andpsychological benefits over continuedrecycling (for example, reducing limitationson water utilization for hygiene purposes).The ability to grow food on site also has anenhancing psychological effect. Thepsychological impacts of these developmentsis difficult to quantify, however real the effectsmay be.

Finally, crew support by intelligent robotsand automated systems appears to be a goodinvestment from the point of view of totalmission productivity. The workload analysisindicates that the total amount of time spentin the field (on foot or in a rover) by a crew

member will be from 10 percent to 20 percentof the amount of their time on Mars.Automated or teleoperated rovers couldextend the effective field time by crewmembers.

3.4 Mission Operations

Central to the success of the ReferenceMission is the accomplishment of all activitiesassociated with mission objectives. To thisend, crew operations are an essential part ofensuring program success and must befactored into all aspects of program planning.All crew activities throughout each mission,from prelaunch through postlanding,constitute crew operations. The majority ofcrew activities fall into four categories:training, science and exploration, systemsoperation and maintenance, andprogrammatic.

•Training activities include such areas asprelaunch survival training for all criticallife support systems, operational andmaintenance training on mission-criticalhardware, prelaunch and in-flightproficiency training for critical missionphases, and science and researchtraining for accomplishing primaryscience objectives.

•The majority of science and explorationactivities will be accomplished on thesurface of Mars. They include, but arenot limited to, teleoperated roboticactivities, habitability experiments, localand regional sorties, and planetary

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science investigations. Supplementalscience objectives may be accomplishedduring other phases of the mission aswell.

•During the first mission, a substantialamount of crew time will be spentoperating and maintaining vehiclesystems. This time allocation is expectedto decrease with subsequent missions asthe systems and operational experiencebase matures.

•Lastly, programmatic activities for thecrews include publicity, documentation,reporting, and real-time activityplanning.

This report does not make specificconclusions regarding hardwarerequirements, facilities requirements, andtraining programs, but a number ofrecommendations and guidelines regardingthese areas have been developed and tailoredto the various mission phases that will beexperienced by each crew sent to Mars. Whilethese and other crew activities may not beseen as directly affecting program success, allareas contribute to the successful completionof each mission and are, therefore, essential tothe overall success of the Reference Mission.

3.4.1 Training Guidelines

The key to successful operations ishaving well prepared, knowledgeable teammembers. This knowledge and preparation ismost effectively obtained by training fornominal and contingency operations.

Extensive training in these areas will improveoverall mission success as well as contributeto meeting science and exploration objectives.Several overriding principles must govern theway training is conducted for the ReferenceMission. Due to time constraints, crewtraining in preparation for the first missionmust be done concurrently with vehicle andtraining facility development. The first crewand mission controllers will be supplantingoperational training with involvement insystem design and testing. This will providethe mission team with the needed systemfamiliarity which would otherwise come fromoperational training exercises. Operationsinput on system designs also has the addedbenefit of enhancing vehicle functionality andoperability (for example, nominal dailyoperations such as housekeeping, foodpreparation, and system maintenance willbenefit from input by the actual users).

Additional prelaunch training mustemphasize developing a working knowledgeof life-critical and mission-critical elements.Because reliance on Earth-based groundcontrol becomes more difficult and less time-responsive as the mission progresses towardMars, crew self-sufficiency becomes essential.In-depth training on life-critical and mission-critical systems will enable crews to becomemore self-sufficient. Contingency survivaltraining for failures in critical life supportsystems will also be required as real-timeground support will not be possible duringMars surface operations and similar remotephases of flight.

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Extensive preflight and in-flight trainingon critical event activities (such as majorpropulsive maneuvers, Mars atmosphericentry, surface sorties, and Earth atmosphericentry) will be required to ensure crewproficiency during these busy time periods.The need for such training will requirepreflight development of a well-definedactivity plan for all critical events.Significantly less preflight training will berequired for noncritical, mission-success-oriented activities such as surface scienceoperations. The initial surface operationsrequired for the establishment of the Marssurface base and preliminary surface scienceactivities will be well defined before the firstcrew departs. Subsequent exploration andscience activities will depend on the findingsfrom the initial scientific investigations. As aresult, training for more than the initialscience activities will not be feasible. Instead,it will be necessary to ensure that crews havethe skills to enable them to plan and prioritizereal-time activities in support of the overallmission objectives. Some planning assistanceand direction will be provided by groundpersonnel; however, the responsibility fordetailed planning and execution will residewith the crew. They are on the surface andhave firsthand knowledge of environmentaland logistical considerations.

Due to the length of the mission andlength of time between critical eventactivities, proficiency training will benecessary during all phases of the mission. Inflight and on the martian surface, training for

critical events will ensure that crews areadequately prepared for both nominal andcontingency situations. From Earth launchuntil Mars ascent and TEI is about 2 yearswhich necessitates an ongoing trainingregime to maintain proficiency. The Earth-based training the crews received 2 yearsearlier prior to Earth launch will not besufficient. Training for the Mars atmosphericentry and landing phase will be conducted bythe crew during the transit between Earth andMars. While on the martian surface andintermixed with other surface activities, thecrew will conduct proficiency training for thecritical Mars ascent phase, subsequentdocking with the ERV, and trans-Earthpropulsive maneuver. In-flight and surfacetraining requirements dictate the need foreffective training facilities in the habitatvehicles or in the ascent vehicles. Design anddevelopment of such facilities will requirefurther investigation and is beyond the scopeof this preliminary report.

Documentation in the form of computer-based libraries must be available foroperational instruction, maintenance of andtroubleshooting systems, and hardwarefailures. Reliable and immediate access to thistype of information will supplement crewtraining for all types of activities frommission-discretionary to life-critical. Extensivecomputer-based resources will have theadded effect of increasing crew self-sufficiency during remote mission phases.

The final, but by no means leastsignificant, element of crew training will be

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the feedback provided by the early crews ontraining applicability and effectiveness relatedto all mission phases. Feedback from the firstcrew in particular will need to beincorporated into training procedures,hardware, and facilities to be used bysubsequent crews. An effective channel forincorporating this feedback into redesign andupgrading of systems and procedures will beessential for follow-on crew training.

3.4.2 Science and Exploration

The majority of science and explorationactivities will be accomplished on the surfaceof Mars. They include, but are not limited to,teleoperated robotic activities, habitabilityexperiments, local and regional sorties, andplanetary science investigations. Additionalscience activities which supplement theprimary science objectives may beaccomplished during other phases of themission as well; however, the largest portionof time and activity allocated in support ofscience and exploration will occur on theplanetary surface.

Initial surface science activities will bewell defined before each crew departs Earth.Detailed activity planning to maximize thecrews useful science and exploration time willincrease overall mission success and will benecessary to ensure the successful completionof many primary science objectives andmission safety requirements. Manyinvestigative results designed to satisfy safetyrequirements (for example, tracking crewhealth) will contribute to satisfying science

objectives as well. Detailed identification ofsafety requirements and related activities isnot required until later in the missionplanning process and will not be discussedhere.

Subsequent exploration and scienceactivities will depend on the findings fromthe initial scientific investigations. As a result,it will be necessary for crews to do real-timescience activity planning to continue researchactivities. Principal investigators and groundsupport personnel will provide the guidelinesfor use in planning priorities of missionobjectives. However, the detailed proceduresfor executing science activities must be left, ingeneral, to the crews who have firsthandknowledge of the unique environmental andlogistical considerations of this mission.Additionally, eliminating the excessiveground planning and replanning activitieswhich have been customary for near real-timemanned space operations will reduce cost.

Beyond the initial investigations, severalsurface science and exploration activities canbe identified preflight as targets for detailedplanning and execution: teleroboticexploration and local and regional surfacesorties. Such preflight planning will maximizethe crew’s useful science time, maximizescience return, improve crew safety ondifficult exercises, and increase overallmission success.

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3.4.3 Systems Operations andMaintenance

During the first mission, a substantialamount of crew time will likely be spentoperating and maintaining vehicle systems.This time is expected to decrease withsubsequent missions as the systems andoperational experience base mature.However, until that time, the more familiarthe crews are with all systems, the less timeoperations and maintenance will take fromscience and exploration activities. To enhancecrew familiarity with the numerous vehiclesystems prior to launch, crews should beinvolved in the design and testing of primaryvehicle systems. The resulting intimateknowledge of the vehicle systems has theadded benefit of supplementing crew trainingon their operational use. Another way tofacilitate crew familiarity is to ensure thatsystem designs are modular and easilyrepairable. The simpler and more familiar thedesign, the easier it is to repair and maintain.

Due to the nature of the ReferenceMission program design (where vehicles areplaced in a standby mode and subjected tohostile environments for long durations), in-depth vehicle and system checkouts will berequired periodically. Crew participation inthese activities should be minimized but maybe necessary due to their access to some of thesystem hardware. Such access andparticipation may make the crews uniquelysuited for analysis of anomalous results thatmight appear in the system testing.

Where applicable, autonomous vehiclehealth monitoring and testing will enablecrew members to use their time performingscience and exploration activities. Inconjunction with this automation, access tohardware and software documentation for allsystems can expedite operations andmaintenance activities which require crewparticipation. Additionally, due to largeresource requirements, some of the vehicleoperations, such as long-term healthmonitoring, trend development or prediction,and failure analysis, may be accomplished byground system support personnel. Thedelineation between which system functionsare automated, crew-managed, or ground-support-managed is not clear and is subject toa host of variables. Some of the considerationsto be used in making this determination arecrew useful time, availability of supportingdocumentation, knowledge of systemperformance (that is, are we operating outsidethe envelope?), time criticality of failurerecognition and recovery, and constraints ondevelopment time and cost. Generalguidelines of responsibility for vehicleoperations are best determined early in thedesign process as automation of functionswill affect mission and vehicle design.

3.4.4 Programmatic Activities

Programmatic activities for the crewsinclude publicity, documentation, reporting,and real-time activity planning. These typesof activities are not usually seen as directlyaffecting program success. They do, however,

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and if properly planned and coordinated, willenhance crew performance and interaction.Like vehicle performance, crew performanceis key to a successful mission.

Successful team performance andinteraction depends on having defined rolesand responsibilities and the flexibility tohandle real-time events. For complexprograms like the Reference Mission, this isimportant not only among crew memberteams, but also among ground supportpersonnel teams and between ground supportand the crews. For the crews, knowing who isresponsible for what and when makes forsmoother operations and can alleviate someof the stress associated with long-term, smallspace, personnel interaction. For ground andcrew interaction, clear rules governing who isin charge of what activities and whodetermines what gets done and when areessential for maximizing mission and scienceobjective returns and alleviating confusionespecially during remote operations. This willenhance operational performance whencombined with a flexible operationalarchitecture allowing crews to create andoptimize the methods required to handle real-time events and achieve set objectives andgoals. (Further discussion on groundoperations and team interaction can be foundin Section 3.8.)

Public affairs activities have been andalways will be an integral part of crewactivities. While they absorb resources(mostly time), they also bring public and

political support to programs and contributeto program success. Crew resources frompreflight through postlanding will have to beallocated in support of this activity.

Another element which contributes toprogram success is the crew feedback on allaspects of the mission. Their input on systemdesigns, operations, science activities (forexample, appropriateness, preparedness,required hardware), and training effectivenessis necessary for the continued improvementand enhancement of follow-on missions.Along these same lines, documentation of allactivities (such as procedural changes, lessonslearned, observations, hardwarediscrepancies) is a time-consuming butnecessary crew activity. (Using variouselectronic systems rather than similar papersystems for documentation preparation willprovide savings in terms of mass, reliability,reduced consumables, etc.) Crew records canbe used to contribute to mission feedback aswell as documentation. Documentation andfeedback are important, especially for the firstcrew, to ensure optimal use of the subsequentcrew’s time and to enhance the chances ofsuccess of future missions of this type.

3.4.5 Activity Planning

The level of crew operations in training,science and exploration, systems operationsand maintenance, and programmaticactivities varies throughout different phasesof the mission; however, some characteristicsare consistent throughout the phases. Forinstance, life-critical or mission-critical

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activities, regardless of mission phase, requiredetailed planning and precise execution. Incontrast, non-life-critical or mission-criticalscience and exploration activities may rely onreal-time procedures generated by the crewwhose guidelines for planning will be toachieve set mission objectives and goals.Guidelines for crew activity planning mustincorporate the flexibility to adapt to thecrew’s experience as they learn to live andwork in a new environment.

In general, crew activity planning mustbe done using a relatively fixed format andtimeline. This will allow crew members toreadily adapt to the various environments inwhich they will be expected to work and live.Having regular awake and sleep times,consistent meal times, etc., from phase tophase will help the crew adapt to missionphase transitions. Having a consistent lengthworkday is also important. With the Mars daylasting nearly 25 hours, adhering to an Earth-based daily schedule of 24 hours wouldroutinely have the crew awake duringmartian night. A consistent 25-hour daythroughout all phases of flight should beconsidered.

A typical work schedule on the SpaceShuttle has crew members workingthroughout an entire flight, only getting timeoff during extremely long flights (thoseapproaching 2 weeks in duration). Formissions that can last a number of years, aconsistent long-term work schedule must bedeveloped that will give crew memberssufficient time off yet maintain productivity

and the success of mission objectives.Feedback from the crew will be importantduring the early phases of this mission, asboth ground support and flight crewmembers adapt to the unique environmentaland operational challenges of the mission.

3.4.5.1 Prelaunch Phase

Crew activities during the prelaunchphase of the mission will concentrate ontraining activities for all mission phases. Earlyon in the program development, crewinvolvement in design and testing of primarysystems will help facilitate crew familiaritywith the systems and enhance applicability ofsystem designs. The resulting intimateknowledge of the vehicle systems has theadded benefit of supplementing crew trainingon their operational use. Extensive training onnominal everyday operations (such ashousekeeping and food preparation) will alsomake the crew more comfortable in theirchanging environments. Strong emphasis oncritical life support and mission-criticalsystems training will also be required.

An important part of crew trainingactivities in this prelaunch phase will beparticipation in integrated training activitieswith scientists and systems engineers.Preflight interaction with the sciencecommunity, in the form of experimentalexercises (crews learn to conduct scientificinvestigations) and exploration exercises(crews simulate local and remote sortieoperations) will enhance overall missionsuccess and scientific return. This will benefit

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not only the crew but also the ground scienceand systems teams by forcing them to interactin a way that will be unique to remoteoperations.

Crew involvement in integrated trainingfor critical activities (such as launch, injectionphase, Earth orbit systems checkout, Marslanding phase, return phases) will be neededto ensure crew proficiency and performanceduring these phases. Simulations which stressthe crew and ground support by introducingfailures and abort scenarios will help ensurecrew safety should such instances occurduring the mission.

In addition to prelaunch trainingactivities, extensive medical testing will berequired of the crew during this time. Theirlong- and short-term health will be criticalfactors in the success of this type of long-duration mission.

3.4.5.2 Earth Launch Phase

The Earth launch phase is defined as thecrew activities required to support missionactivities from launch through TMI andsubsequent powerdown of nonessentialhardware. It is expected that some systemsused during the launch phase will not berequired until later in the mission. Thehardware which fits in this category will beplaced in a quiescent mode to conserveresources.

During the Earth launch phase of themission, the crew’s primary focus will be toensure a safe launch and Mars injection.

Nominal actions directly associated with thelaunch are expected to be minimal. Once inorbit, crew activities will center on a completecheckout of vehicle systems prior to leavingEarth orbit while near real-timecommunications with ground support arepossible. This checkout will include all life-critical, mission-critical, and mission-discretionary systems with appropriateactions being taken for anomalies on eachsystem according to its criticality. Such acheckout, which will be as automated aspossible, will require some crew and groundsupport actions either for testing or fortroubleshooting failures.

While in Earth orbit but before TMI,limited time or personnel may cause some ofthe less critical pre-TMI testing to be deferred.For instance, testing on mission-discretionaryhardware intended for use only on themartian surface may be delayed until later inthe transit to Mars. Such decisions will bemore appropriately made when vehiclesystem checkout requirements are identifiedduring the design process. Additionally, suchreal-time decisions may be made based onassessments of other activities during theEarth orbit phase.

Training activities will not be scheduledduring the Earth launch through TMI phaseof the mission as the crew will have beentrained for these activities prior to launch.Additionally, with the exception of thoseactivities related to crew health maintenanceand monitoring, planned science activitieswill not be performed during this high

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systems activity time frame. Medical testingand assistance may be required during thisphase as crew members adapt to the changein environment. (The number of crewmembers who typically do not experiencespace sickness during the first few days ofweightlessness is just one in three based on171 Shuttle crew members (Reschke, et al.,1994).) Any serious life- or mission-threatening crew illness prior to TMI will bereason to abort the mission.

Throughout all mission phases,documentation of activities and feedback ontraining effectiveness will be required of allcrew members. This will be essential in orderto make effective use of the training time ofthe follow-on crew and the program’straining hardware. Due to the high systemsactivity during this phase, documentationand other programmatic activities will beeither minimal or deferred to a later time.

3.4.5.3 Trans-Mars Phase

The trans-Mars phase of the mission isdefined as crew activities from post-TMIsystem powerdown through Mars OrbitInsertion (MOI) preparation. Thisinterplanetary transit phase will be fairlyhomogeneous from the standpoint ofenvironment and crew activity. Crewactivities related to vehicle systems areexpected to be minimal. Only nominaloperations (housekeeping, food preparation,etc.) will be required unless mission-discretionary systems testing has beenpostponed until after TMI. This decision may

be made prior to launch based on time orpersonnel constraints or based on the result ofearlier failures. Activities for failure analysisand troubleshooting will be accomplished onan as needed basis.

The relatively quiescent vehicle systemactivity during the transit phase makes itwell-suited for crew training activities.During this time, additional training time canbe made available for the training above andbeyond the preflight training that is requiredto maintain crew proficiency during therelatively long Mars transit time. The need forin-flight training will require that trainingsimulators be available to the crew in thetransit-habitat vehicle. Critical events that willrequire training during this time are MOI,landing, and Mars launch activities.Additional time may also be made availablefor training and review of payload andscience hardware to be used on the surface.

During the transit phase, time may beavailable for limited science activities. Theprimary restriction on conductinginterplanetary science activities will likely bemass related. Interplanetary science(astronomy, solar observations) is not theprimary science objective for this type ofmission; and, as such, related hardware willonly be provided for crew use if massmargins exist at the appropriate point in thedesign process. However, there may beopportunities for useful scientific data returnwhich can “piggy-back” on instrumentsprovided for crew safety issues. An examplewould be conducting some solar science

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experiments as part of meeting requirementsfor crew safety (as in solar flare detection).Also, medical testing will be requiredperiodically throughout this phase to verifycrew health. Related studies on crewadaptation to the space environment andother health-related biomedical scienceexperiments may benefit from such testing.

As with all mission phases,documentation of activities and feedback ontraining effectiveness will be required of allcrew members in order to make effective useof the follow-on crew’s training time.Additionally, the information will provideengineers on Earth with guidelines forupgrading and improving the vehicle systemsand training hardware. Transit time is idealfor documenting current and earlier phases ofthe mission.

Due to the high interest in such amission, the crew will be required toparticipate in numerous public affairsactivities. International participation in thistype of mission will only increase pressdemands on crew time. Press and crewexchanges will be particularly productiveduring relatively quiescent periods early inthe transit phase when communication lagtimes are short. As communication lag timeincreases, the necessity for crew autonomywill become evident. However,communication with Earth will still have tobe provided for failure assistance and crewpersonal interaction with Earth.Communication activities will be higherduring the initial and critical mission phases,

and appropriate time must be allocatedduring the crew schedule for such activities.

3.4.5.4 Mars Landing Phase

The Mars landing phase is a verydynamic phase of the mission and is definedas the time from MOI preparation throughpostlanding crew recovery and surfacesystem activation. Many of the activitiesduring this time frame will have beenplanned in detail before launch and perhapsupdated during the interplanetary transit.

Prior to MOI the crew will have toprepare the transit-habitat vehicle fortransition from a zero-g to a partial-g surfacevehicle. All peripherals, supplies, andhardware that have been taken out for useduring transit will have to be safely stowed.Nonessential equipment will be powereddown in exchange for equipment necessaryfor this phase of flight. During this time, thecrew will have to checkout or verify theoperational status of all hardware andsoftware required for the upcoming criticalMOI and landing activities.

Pre-MOI activities must be initiated earlyenough to allow sufficient time totroubleshoot any failures or discrepanciesprior to the critical phase. Many of theactivities during this phase will, by necessity,be automated. However, crew interventionand override must be available due to theuniqueness and criticality of this phase of themission (for example, doing critical activitieswithout real-time support in a new andunique environment) and in general as abackup to the automated systems.

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After landing, a thorough vehiclecheckout will be necessary due to the drastictransition in operational environment fromvacuum and zero g to a planetary surfaceenvironment. Initially, the only checkoutwhich will be done will be on those systemsrequired to certify that crew safety and life-support systems and their backups areoperational.

Crew training activities during the latterpart of the transit phase and the early part ofthe landing phase will intensely focus oncritical activities for the MOI and landingphase so that the crew is adequately preparedfor upcoming events. Again, this will requirethat adequate training facilities be available tothe crew on the transit-habitat vehicle.

Minimal science activities will be doneduring the Mars landing phase. Time may beavailable for limited orbital observations totake advantage of the unique opportunity tophotograph and gather remotely sensed dataof Mars on approach and from orbit.However, this will depend on the availablemass allocated for this type of equipment, thesuccess of the higher priority critical systems,and the training activities during this timeframe.

Due to the high systems activity duringthis phase, documentation and otherprogrammatic activities will be minimal.Those activities necessary to improve thefollow-on crew’s training time and programtraining hardware will be deferred until thecrew has time available.

On approach and on the surface of Mars,communication lag time with Earth will benear or at its maximum. During such a criticalphase of flight, crew functions will, ofnecessity, be virtually autonomous fromEarth-based support. Some communicationwith Earth will still have to be provided forfailure assistance and vehicle healthmonitoring of trend data. Such requirementsmay drive the need for regular, perhapscontinuous, communications capability withEarth.

3.4.5.5 Mars Surface Phase

The Mars surface phase is defined aspostlanding recovery operations to prelaunchoperations. In general, this phase of themission will receive a minimal amount ofmission-specific planning and training priorto departing Earth; its focus will be on themission’s primary science and explorationactivities which will change over time toaccommodate early discoveries. A generaloutline of crew activities for this time periodwill be provided before launch and updatedduring the interplanetary cruise phase. Thisoutline will contain detailed activities toensure initial crew safety, make basicassumptions as to initial science activities,schedule periodic vehicle and systemcheckouts, and plan for a certain number ofsorties. Much of the detailed activity planningwhile on the surface will be based on initialfindings and therefore cannot beaccomplished before landing on Mars.However, the crew will be provided with

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extensive, but not mission-specific, trainingrelated to scientific investigation and vehiclesystems. This will assist the crew in planningspecific activities in these areas, as required,while on the martian surface.

Initial postlanding systems activities willfocus on hardware testing and verification forlife support, then mission-critical, and finallymission-discretionary systems. The initialphase of these checkouts must be donewithout the requirement for EVAs. EVAs willbe restricted until sufficient data have beencollected to fully characterize the immediatemartian environment. Once it has beenconfirmed that the martian environment isnot a threat to crew health or mission success(assuming this has not been done by priorrobotic missions), EVAs may then beaccomplished to complete required systemstesting and verification.

During the crew stay-time on the surfaceof Mars, additional full-scale testing andverification of some hardware will berequired. After vehicle system checkout of thecrew habitat shortly after crew arrival,activities for joining the crew habitat with apreviously landed laboratory may begin.Complete connection of these two vehicleswill be accomplished after a full verificationof each vehicle’s individual integrity iscompleted. Also during the initialpostlanding time frame, verification andsystem status check of the vehicles needed forcrew launch and Earth return will berequired. While much of this activity will beautonomous and supervised by ground

operations personnel, crew involvementprovides the crew with confidence in theirreturn systems, enables visual verification ofascent vehicle system integrity, and allows forcrew interaction or intervention in anomalytroubleshooting on surface hardware. Beyondannual, comprehensive vehicle checkouts,system activities for the crew will consist ofmaintenance, housekeeping, consumablestracking, and repair operations.

Initial science activities during thesurface phase will concentrate on verifyingcrew health and safety on the martian surface.Atmospheric, chemical, and biological studiesof the immediate environment surroundingthe crew habitat will be critical to ensure crewsafety. Once the immediate environment ischaracterized and potential threats wellunderstood, planning for future local andregional sorties may begin. Some generalplanning of these initial science activities maybe done in advance; however, much of thecrew activity will depend on the initialfindings and therefore cannot be preparedprior to launch. The crew must be providedwith enough expertise and applicablehardware and resources to help them dealwith potential unforeseen discoveries andobstacles to their investigations.

Prior to the first EVA and sortie, roboticexploration may map local areas and allowinvestigators to seek out interesting sites forregional sorties. Mission preparation willhave assumed a minimum number and typeof EVAs; however, adaptation to real-time

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discoveries will be necessary for many ofthese excursions.

Additional biomedical health scienceactivities performed on the crew will berequired during the surface phase as well.Safety issues, health examinations,investigations to gather data on low-gadaptation, and long-term physiologicaleffects on the crew will also be conductedduring the surface phase.

As with other phases of flight, there maybe opportunities for some scientific datareturn which can piggy-back on instrumentsprovided for crew safety issues. For instance,limited solar science may be provided in partfor crew safety issues (as part of solar flaredetection), thus providing opportunity foradditional solar science observations while onthe martian surface.

Training during surface operations willbe periodic to maintain proficiency formission-critical activities (such as launch andEarth return). Additional training activities,on an as needed basis, may be required foractivities such as sorties and EVAs.

Documentation of activities and feedbackon training effectiveness will be required ofall crew members in order to make effectiveuse of the follow-on crew’s training time. Theinformation will provide engineers on Earthwith guidelines for upgrading and improvingthe vehicle systems and training hardware.Additional documentation of scientificexperiments and results will need to berelayed to Earth for use by the science teamsin analysis and future planning.

Time will also be allocated for publicaffairs events. These types of events will notbe interactive due to the time lag, but will berecorded and subsequently transmitted toEarth. Requests from news media and otherorganizations will be reviewed, scheduled,and then relayed to the crew through missionmanagement personnel on Earth. Activitiessuch as these will require a flexible planningarchitecture in which crew and groundsupport both participate.

All of the above mentioned surfaceactivities will require some level ofcommunication with mission teams onEarth—both science and systems teams.Analysis of the communication requirementswill result from a combination of system datarequirements, crew health data requirements,crew personal communications, and sciencedata requirements.

3.4.5.6 Mars Launch Phase

The Mars launch phase is a very dynamicphase of the mission and is defined as theactivities from preparation for launch throughTEI and nonessential hardware powerdown.Many of the activities during this time framewill have been planned in detail prior tolaunch from Earth.

Before committing the crew to Marsascent and Earth return activities, full systemscheckout of the MAV and ERV is required.Because both vehicles are critical to crewsafety and survival, sufficient time must beprovided prior to launch to verify systemsand troubleshoot any anomalous indications

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prior to crew use. Additional crew time willbe spent preparing the surface habitat andother facilities for an untended mode. Suchactivities will include stowing anynonessential hardware, safing critical systemsand their backups, and performing generalhousekeeping duties which will facilitate useof the facilities by future crews.

Once the crew has prepared all surfaceequipment for departure, the actual departureactivities will begin. Detailed activities for thisdeparture will have been prepared andsimulated on Earth, so a detailed plan forMars launch through TEI will be availableand executed at the appropriate time.Contingency scenarios will also have beenplanned prior to Earth launch, and enoughtime will be allocated during ascent andrendezvous activities to enable successfuloperations within these contingencies. Aftersuccessful launch, rendezvous with the returnvehicle, and TEI, the crew will again placenonessential hardware in a quiescent modefor the return trip.

In the time period leading up to the Marslaunch phase, the crew will spend anincreasing amount of time training andpreparing for this extremely critical phase ofthe mission. In particular, the rendezvouswith the ERV will require attention. Sufficienttraining facilities must be available on thesurface to ensure crew proficiency in theseactivities prior to execution. Also,physiological training for the return to a zero-g and eventually a one-g environment will bedramatically increased during prelaunch.

During this most critical of time frames,other activities such as public affairs eventsand documentation of activities will beminimized. Due to the critical nature of thismission phase, communication transmissionsto Earth will be necessary for failureassistance and vehicle health monitoring.However, due to the nature of the lag timeand the criticality of events, vehicle and crewactivities will remain fairly autonomous.

3.4.5.7 Trans-Earth Phase

The trans-Earth phase is defined as thepost-TEI powerdown through preparation forEarth landing. This interplanetary transitphase will be fairly homogeneous from anenvironment and crew activity standpoint.The crew activities related to vehicle systemsare expected to be minimal. Only thoseactivities required for nominal operations willbe required (housekeeping, food preparation,etc.).

Crew training activities during this timeframe will focus on the critical Earth entryand landing phase of flight. This will drive anERV hardware requirement to provide thecrew with adequate simulators and on-boardtraining facilities to maintain proficiency invehicle operations. The crew will also begin aregime of zero-g countermeasure activities(such as exercise, lower body negativepressure, etc., depending on the best availableknowledge at the time) to prepare themselvesphysically for return to a one-g environment.

Again, due to the relatively quiescentsystem activity during the transit phase, time

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may be available for the crew to do limitedscience activities. The restrictions oninterplanetary science activities will be massrelated. Medical testing will be requiredperiodically throughout this phase in order tomeet biomedical science objectives and verifycrew health for entry.

During this time frame, documentationactivity will be extremely important due tothe fact that the next crew will be launchedprior to the return crew’s landing.Additionally, the information will provideengineers on Earth with guidelines forupgrading and improving the vehicle systemsand training hardware. Due to timeconsiderations, some handoverdocumentation for the next crew will havebeen prepared prior to leaving Mars. Finaltransfer of vehicle status is recommended tobe direct from crew to crew to preventconfusion and ensure thoroughness. Someaspects of the hand over may be filteredthrough ground support in order to simplifycommunications requirements.

Due to the high interest in such amission, the crew will be required toparticipate in numerous public affairsactivities. Quiescent periods of transit timecan provide opportunities for press and crewinteraction.

3.4.5.8 Earth Entry and Landing

The Earth entry and landing phase isdefined as the crew activities which supportpreentry preparation through landing andcrew health recovery. Because it is not

currently known how prolonged low-g andzero-g environments will affect the humanphysiology, the main focus of this phase offlight will be the safe return and recovery ofthe crew.

Crew activities related to vehicle systemswill be emphasized prior to entry. Systemcheckout will be required with sufficient timeprior to entry to allow for troubleshootingany failures and guarantee a safe crewlanding. Upon landing, vehicle safing andpowerdown will be required. Due to the highprobability of lower than normal physicalcapability among the crew, many of thepostlanding system activities should beautomated.

No training or science activities will beplanned during this critical phase of flight.Crew health monitoring will be conducted forthe purposes of crew health and safety. Also,due to the time-critical nature of this phase,documentation will be minimal and willpertain only to crew preparedness and systemperformance.

3.4.5.9 Postlanding

The postlanding phase of crewoperations is defined as the activitiesconducted after vehicle powerdown throughmission termination. In most instances,mission termination will not be a well-definedtime and may be different for differentmembers of the crew as crew involvement inadditional program activities is subject tovarious conditions.

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Face-to-face debriefings with theengineers responsible for individual systemsand vehicles will be beneficial after landing.Such meetings can be more productive andprovide more information than writtendocumentation. Feedback on all trainingactivities and facilities throughout the missionwill also be beneficial postlanding as it willfacilitate the training of follow-on crews.

Medical testing after landing willcontinue as part of long-term healthmonitoring. This may be required for anindefinite period of time. Some effects fromthe mission may not appear until months oreven years after the flight phases of themission have ended. Therefore, the crewmembers should be subject to periodicmedical testing for observation of long-termeffects of the mission. It may also be necessaryto satisfy quarantine issues, whether real orpolitical, immediately upon return to Earth.(Quarantine issues will have to be addressedearly in the mission planning phases toensure that adequate facilities are availablewhen and if they are needed.)

Formal documentation of all aspects ofthe mission will be required of all crewmembers after landing. Additional emphasiswill be placed on providing engineers on theground with guidelines for upgrading andimproving vehicle systems and traininghardware.

Due to the high interest in such amission, the crew will be required toparticipate in many public events anddebriefings after they return to Earth.

3.5 Mission Design

The focus of this section is to describe afeasible sequence of flights on specifictrajectories with specific systems thataccomplish Reference Mission goals andobjectives. Foremost among the choices thatmust be made is the type of trajectory to use.It must be one that can accomplish missionobjectives using a reasonable transportationsystem and at the same time address the riskmitigation strategy and still provide forflexibility within a development and flightprogram. Other assumptions made that affectthe “how” of mission implementation arediscussed as part of the overall missionstrategy. With these elements in place, thissection presents a discussion that includessuch information as launch and arrival dates,payload manifests, and crew activities foreach flight in the set studied for this ReferenceMission.

3.5.1 Trajectory Options

Trajectory options between Earth andMars are generally characterized by thelength of time spent in the Mars system andthe total round-trip mission time. The firstoption is typified by short Mars stay-times(typically 30 to 90 days) and relatively shortround-trip mission times (400 to 650 days).This is often referred to as an opposition-classmission, although this report has adopted theterminology “short-stay” mission. Thetrajectory profile for a typical short-staymission is shown in Figure 3-2. This class hashigher propulsive requirements than the often

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considered long-stay missions, and typicallyrequires a gravity-assisted swingby at Venusor the performance of a deep-spacepropulsive maneuver to reduce total missionenergy and constrain Mars and Earth entryspeeds. Short-stay missions always have oneshort transit leg, either outbound or inbound,and one long transit leg, that requires closepassage by the Sun (0.7 AU or less). Asignificant characteristic of this class oftrajectory is that the vast majority of theround-trip time, typically over 90 percent, isspent in interplanetary space. The secondmission class consists of long-duration Marsstay-times (as much as 500 days) and longtotal round-trip times (approximately 900days). This mission type is often referred to as

conjunction-class, although this report hasadopted the terminology “long-stay” mission.These represent the global minimum-energysolutions for a given launch opportunity. Thetrajectory profile for a typical long-staymission is shown in Figure 3-3.

Within the long-stay category ofmissions, the option exists to dramaticallydecrease the transit times to and from Marsthrough moderate propulsive increases. Thetotal round-trip times remain comparable tothose of the minimum-energy, long-staymissions; but the one-way transits aresubstantially reduced, in some cases to lessthan 100 days, and the Mars stay-times areincreased modestly to as much as 600 days.The round-trip energy requirements of thisclass, referred to as a “fast-transit” mission,are similar to the short-stay missions eventhough the trajectories are radically different.The profile for a typical fast-transit mission isshown in Figure 3-4.

Figure 3-3 Typical long-stay missionprofile.

i 6 i i i fi

γ

MISSION TIMES

OUTBOUND 224 daysSTAY 458 days RETURN 237 days

TOTAL MISSION 919 days

Earth Launch1/17/2014

Depart Mars11/30/2015

Arrive Mars8/29/2014

Earth Return7/24/2016

Figure 3-2 Typical short-stay missionprofile.

Fi 5 T i l h t t i i fil

γ

DEPART MARS

9/26/2014

EARTH RETURN7/14/2015

ARRIVE MARS

8/27/2014

VENUS FLYBY

2/23/2015

DEPART EARTH

1/15/2014

MISSION TIMES

OUTBOUND 224 daysSTAY 30 days RETURN 291 days

TOTAL MISSION 545 days

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3.5.2 Trajectory Selection Factors

Three factors make the selection of thetrajectory class critical to the ReferenceMission. First, the selection must be consistentwith achieving the Mars exploration goalsand objectives. Second, the selection must beconsistent with the risk philosophy of theReference Mission. And third, forprogrammatic reasons, the trajectory classselection must provide the flexibility toconduct missions in all opportunities withinthe 15-year Earth-Mars trajectory cycle and toconduct missions supporting the evolution ofMars exploration objectives andimplementation strategies.

3.5.2.1 Satisfying Reference Mission Goalsand Objectives

The goals and objectives of the ReferenceMission focus on allowing human crews tospend the greatest amount of time on thesurface of Mars for the investment made totransport them there and to learn as much as

possible about how humans react in thisenvironment. Verifying the ability of peopleto inhabit Mars requires more than a briefstay of 30 days at the planet. In addition, thelow return on investment associated with a30-day stay at Mars (of which significantlyless than 30 days would actually beproductively spent on the Mars surface due tothe crew adaptation to the Mars gravity, crewpreparations for Mars departure, etc.) wasconsidered unacceptable. Following theAugust 1992 Workshop (Duke, et al., 1992), itwas decided that the “Plant the Flag” missionobjective was not a tenable rationale tosupport the substantial investment involved.Consequently, a long-stay trajectory optionwas considered to be best able to satisfy thegreatest number of mission goals andobjectives.

3.5.2.2 Satisfying Reference Mission RiskStrategy

The applicability of each of thepreviously discussed mission types to thehuman exploration of Mars has been thesubject of much debate. The general opinionis that the initial flights should be short-staymissions performed as fast as possible (so-called “sprint” missions) to minimize crewexposure to the zero-g and space radiationenvironment, to ease requirements on systemreliability, and to enhance the probability ofmission success. However, when considering“fast” Mars missions, it is important tospecify whether one is referring to a fastround-trip or a fast-transit mission. Past

Figure 3-4 Fast-transit mission profile.

γ

Earth Launch2/1/2014

Depart Mars3/11/2016

Arrive Mars7/1/2014

Earth Return6/29/2016

MISSION TIMES

OUTBOUND 150 daysSTAY 619 days RETURN 110 days

TOTAL MISSION 879 days

Nominal Departure3/11/2016

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analyses have shown that decreasing round-trip mission times for the short-stay missionsdoes not equate to fast-transit times (that is,less exposure to the zero-g and spaceradiation environment) as compared to thelong-stay missions. Indeed, fast-transit timesare available only for the long-stay missions.This point becomes clear when looking atFigure 3-5 which graphically displays thetransit times as a function of the total round-trip mission duration. Although the short-staymission has approximately half the totalduration of either of the long-stay missions,over 90 percent of the time is spent in transit,compared to 30 percent for the fast-transitmission.

The interplanetary ionizing radiation ofconcern to mission planners consists of twocomponents: galactic cosmic radiation (GCR)and solar particle events. NASA policyestablishes that exposure of crews to radiationin space shall not result in heath effectsexceeding acceptable risk levels. At present,acceptable risk levels are based on not

exceeding long-term cancer risk by more than3% above the natural cancer death probability(which is approximately 20% lifetime risk forthe US population as a whole). At present,the information required to calculateacceptable risk from radiation exposureduring a Mars mission, especially for theGCR, is not available. Although doses (theaverage physical energy deposition byincident particles) can be calculated, theconversion of this information into apredicted radiation risk cannot be doneaccurately. The National Research Councilrecently issued a report estimating theuncertainty in risk predictions for GCR can beas much as 4-15 times greater than the actualrisk, or as much as 4-15 times smaller.

Current knowledge does allow for somequalitative conclusions to be drawn. Radia-tion risk on the Mars surface, where the GCRfluence is attenuated by 75 percent due to theMars atmosphere and the planet itself, islikely to involve less risk than a comparablelength of exposure in interplanetary space. Ifthe difference in radiation effectivenessbetween the interior of a shielded spacecraftand a habitat on the surface of Mars is notconsidered, the GCR fluence to which crewsare exposed during a 500 plus day transit toMars is equivalent to approximately 125 daysof Mars surface exposure. A significantreduction in transit time, to 100 days for theone-way transit, would result in a radiationexposure comparable to the short-staymission. Thus, the risk to crews on fast-transit missions may be even less than the risk

Return Transit Time at Destination Outbound Transit

0 100 200 300 400 500 600 700 800 900 1000

Short-Stay

Long-Stay (Fast-Transit)

Long-Stay (Minimum Energy)

Mission Duration, Days

Figure 3-5 Round-trip missioncomparisons.

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to crews on short-stay missions, not onlybecause of minimized exposure to GCR butalso reduced probability of exposure to solarparticle events in interplanetary space.

A similar analysis of mission classes isinvolved in considering the crew’s exposureto the zero-g environment during transits toand from Mars. Significant physiologicalchanges occur when zero-g time begins to bemeasured in weeks or months. (Bonedecalcification, immune and cardiovascularsystem degradation, and muscular atrophyare a few of the more unpleasant effects.)Research on the effects of long-term zero-g onthe human body is in an elementary stage. Atthe time of the writing of this report, thelongest continuous stay in space by a U.S.astronaut is the 181 days of Shannon Lucid(aboard the Russian MIR Space Station); thelongest stay by a Russian cosmonaut is 366days. In none of the cases were crews exposedto zero-g/partial-g/zero-g sequences similarto that projected for Mars missions. Currentdata indicates that recovery in a one-genvironment can be fairly rapid (a few days),but development of full productivity couldrequire significantly more time. Upon arrivalon the martian surface, the crew will need tospend some currently unknown, but probablyshort, time re-adapting to a partial-g field.This may be of concern for the short-staymissions where a substantial portion of thesurface stay-time could be consumed by crewadaptation to martian gravity. Conversely,ample time will be available for the crew toregain stamina and productivity during the

long surface stays associated with theminimum-energy, fast-transit missions.

Several potential solutions to thephysiological problems associated with zero-gtransits to and from Mars may exist:countermeasures (exercise, body fluidmanagement, lower body negative pressure),artificial-g spacecraft, and reduced transittimes.

The usefulness of countermeasures toreduce some of the zero-g effects is stillunknown. Russian long-duration crews haveexperienced physiological degradation evenwhen rigorous exercise regimens have beenfollowed. However, most of these effects seemto be quickly ameliorated upon return to aone-g environment, at least when immediatemedical aid is available.

Rotating the Mars transfer vehicle (MTV)and ERV is a method of providing anartificial-g environment for the crew and ismost often associated with low-performancepropulsion systems, or the short-stay class oftrajectories (since both require long transittimes). Studies have indicated that the MTVdesign mass penalties are on the order of 5percent to 20 percent if artificial g isincorporated. Depending on the specificconfiguration, there may also be operationalcomplications associated with artificial-gspacecraft including EVA, maintenance, andthe spin-up/spin-down required formidcourse maneuvering and rendezvous anddocking.

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Figure 3-6 illustrates some exampletransit times for minimum-energy, fast-transit,and short-stay missions. Note that all one-way transits are within the Russian zero-gdatabase.

However, the surface stay-times forshort-stay missions are typically 1 to 3months. It is unknown whether such a shorttime spent in a 0.38-g field will counteract 5months of outbound zero-g exposure. Incontrast, the one-way trip times ofrepresentative fast-transit missions are nearlywithin the current U.S. zero-g database,which will certainly be augmented by normalInternational Space Station operations prior toexecuting human interplanetary missions.Also note that the fast-transit mission’s zero-gtransfer legs are separated by a substantialperiod of time in the martian gravitationalfield. This long period on the surface of Mars

may prove sufficient to ameliorate thephysiological effects of the relatively shortoutbound transit.

3.5.2.3 Satisfying Reference Mission ProgramFlexibility

Finally, the selection of trajectory typedepends on its allowance for flexibility torespond to mission opportunities andimplementation strategies. The higher energy,short-stay missions significantly vary in bothpropulsive requirements and round-trip flighttimes across the 15-year Earth-Mars trajectorycycle. Additionally, these missions generallyrequire the use of a Venus swingby maneuverto keep propulsive requirements withinreason. However, these swingbys are notalways available on the return transit leg andmust be substituted in the outbound transitleg. Because the transit leg containing theVenus swingby is the longer of the two, thecrew will spend up to 360 days on the trip toMars, with any associated physiologicaldegradation occurring at the beginning of themission—that is, prior to the crew’s arrival atMars. These variations in the trajectoryenergy requirements can significantly impactthe configuration of the Earth-Marstransportation elements for different Earth-Mars opportunities. Programmatically, such aresult is unattractive. In contrast, theminimum-energy, long-stay missions exhibitvery little variation over the 15-year cycle,while the fast-transit long-stay missionsreflect only moderate variations across thesame 15-year cycle. In addition, neither

Figure 3-6 Microgravitycomparisons for various mission

classes.

0

100

200

300

400

500

600

Minimum Energy * Fast-transit * Short Stay **

Outbound

Inbound

Total

Time(Days)

Maximum Soviet

Experience (366 Days)

* Zero-g transits separated by long surface stay (450-600 days)** Zero-g transits separated by short surface stay (30-90 days)

Maximum USExperience (84 Days)

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mission requires a Venus swingby or travelinside the Earth’s orbit around the Sun.

3.5.3 Mission Design Strategy

Keeping the Reference Mission goals andobjectives in mind, numerous alternativeswere considered that could successfullyaccomplish the basic mission. Two majorconsiderations that drove many of themission design-related selections include:

•Reducing the amount of propellantneeded to move mission hardware fromone location to another (propellant massis the single largest element of allcomponents in the Reference Mission)

•Extending the amount of time spent bythe crew conducting usefulinvestigations on the surface of Mars.

The alternatives selected by the MarsStudy Team that impact mission designstrategy have been grouped into six majorareas and are presented here. Otheralternatives will be discussed in subsequentsections.

3.5.3.1 Trajectory Type

The discussion presented in the previoussection led to the selection of the fast-transit,long-stay class trajectories. However, theamount of reduction sought in the Earth-Marsand Mars-Earth transit times must bebalanced with other considerations.Reductions below 180 days in the one-waytransit times (for the 2009 opportunity, theworst case) would require either significant

propulsive capability improvements or wouldnecessitate much larger interplanetaryspacecraft launched into LEO for the humanmissions, thereby requiring assembly anddocking in LEO and higher ETO launch rates.Indeed, others have demonstrated thatreductions in trip times reach a point ofdiminishing returns from the space transfervehicle design perspective (Drake, 1991).Thus, a C3 leaving Earth of 20 to 25 km2/sec2

appears to be appropriate for humanmissions. This results in maximum Earth-Mars transit times of approximately 180 days(2009 opportunity) and minimum transittimes of approximately 120 days (for the 2018opportunity, the best case). Similarly, a C3leaving Mars of ~16 km2/sec2 appears to beappropriate for human missions, resulting insimilar Mars-Earth transfer times for theseopportunities. (C3 is a measure of the energyrequired to get from Earth to Mars or viceversa. Specifically, C3 is the square of thevelocity of departure from a planet. Low C3sare desirable because there is a directcorrelation between C3 and the size of thetransportation system.)

3.5.3.2 Split Mission Strategy

The split mission approach has beenadopted for the Reference Mission because itallows mission elements to be broken intomanageable pieces rather than trying tointegrate all necessary hardware elements fora single, massive launch. For this mission,“manageable” was defined to mean piecesthat can be launched directly from Earth andsent to Mars, using launch vehicles of the

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Saturn V or Energia class, withoutrendezvous or assembly in LEO. A keyattribute of the split mission strategy is that itallows cargo to be sent to Mars without acrew, during the same launch opportunity oreven one or more opportunities prior to thecrew’s departure. This creates a situationwhere cargo can be transferred on low energy,longer transit time trajectory, and only thecrews must be sent on a high-energy, fast-transit trajectory. By using a low energytransfer, the same transportation system candeliver more payload to the surface of Mars atthe expense of longer flight times. Spacing thelaunches needed to support a mission acrosstwo launch windows allows much of theinfrastructure to be pre-positioned andchecked out prior to committing crews totheir mission. When combined with thedecision to focus all Mars surfaceinfrastructure at a single site, this approachallows for an improved capability toovercome uncertainties and outright failuresencountered by the crews. Launches ofduplicate hardware elements, such as ERVs,on subsequent missions provides eitherbackup for the earlier launches or growth ofcapability on the surface.

3.5.3.3 Aerocapture

Mars orbit capture and the majority ofthe Mars descent maneuver will be performedusing a single biconic aeroshell. The decisionto perform the Mars orbit capture maneuveraerodynamically was based on the fact that anaeroshell will be required to perform the Marsdescent maneuver no matter what method is

used to capture into orbit about Mars, andcurrent technology can develop an aeroshellwith a mass that is equal to or less than thepropulsion system required for capture. Thus,the strategy assumed the development of asingle aeroshell that can be used for bothMars orbit capture and descent maneuvers.Given the demands on a descent aeroshell ofthe Mars entry and landing requirements, theadditional capability to permit aerocapture isconsidered modest.

3.5.3.4 Surface Rendezvous

The hardware elements launched as partof the split mission approach must cometogether on the surface of Mars, which willrequire both accurate landing and mobility ofmajor elements on the surface to allow themto be connected or moved into closeproximity. The alternative was to link majorcomponents either in Earth orbit or in Marsorbit prior to entry and landing. Previousstudies (NASA, 1989) indicated that the heatshields for vehicles with the combined massimplied by such an orbital rendezvousapproach would be exceedingly large anddifficult to launch and assemble in orbit.Precision landing has been demonstrated forthe Moon (Apollo 12), and studies indicate(Barton, et al., 1994) that available guidanceand control systems combined with a simplebeacon transmitting from the surface(assumed to be carried by the first element atthe site) are sufficient to allow a vehicle toland at a designated location on Mars withuncertainties measured in meters.

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3.5.3.5 Use of Indigenous Resources

The highly automated production ofpropellant from martian resources is anotherdefining attribute of the Reference Mission.The hardware necessary to produce and storepropellants using raw materials available onMars (in this case, carbon dioxide from theatmosphere) is less massive than thepropellant needed to depart the martiansurface for orbit (Ash, et al., 1978). It is nowapparent that the technology for producingmethane and liquid oxygen from the martianatmosphere and some nominal hydrogenfeedstock from Earth is not only an effectiveperformance enhancement but also appears tobe technologically feasible within the next fewyears. Splitting the launch of missionelements allows the propellant productioncapability to be emplaced, checked out, andoperated prior to committing the crew tolaunch from Earth. In addition to spacecraftpropulsion, this production capability onMars can provide fuel for surfacetransportation, reactants for fuel cells, andbackup caches of consumables (water,oxygen, and trace gases) for the life supportsystem. All of these features allow for smalleramounts of consumable material to belaunched from Earth and contributes to thegoal of learning how to live on Mars.

3.5.3.6 Mars Orbit Rendezvous and DirectEntry at Earth

The last element of mission design isreturning the crew to Earth. There arepotentially three significant propulsive

maneuvers associated with the return:departing from the martian surface, departingfrom Mars orbit, and capturing into Earthorbit. Several alternatives are associated withthese three events, the proper selection ofwhich can result in a significant savings inpropellant and thus in mass that must belaunched from Earth. Three key choicesaffecting this portion of the mission are madein the Reference Mission. First, the Earth-return transit habitat used by the crew is leftin Mars orbit. While the outbound habitatcould have been used for this task, thepropellant needed to lift it is significant; andit is considered more valuable as part of agrowing surface infrastructure. The entireERV is composed of the TEI stage and theEarth-return transit habitat. The ERV isdelivered to Mars orbit fully fueled, and itloiters there for nearly 4 years before beingused by the crew in returning to Earth.Second, the crew is not captured into an Earthorbit at the completion of the mission, butdescends directly to the surface much as theApollo astronauts did when returning fromthe Moon. The Earth crew capture vehicle(ECCV) has the necessary heat shield forEarth reentry. Third, the crew rides into Marsorbit in a dedicated ascent capsule.

3.5.4 Mission Sequence

Figure 3-7 illustrates the missionsequence analyzed for the Reference Mission.In this sequence, three vehicles will belaunched from Earth to Mars in each of fourlaunch opportunities starting in 2007. The

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first three launches will send infrastructureelements to both Mars orbit and to the surfacefor later use. Each remaining opportunityanalyzed for the Reference Mission will sendone crew and two cargo missions to Mars.The cargo missions will consist of an ERV onone flight and a lander carrying a habitat andadditional supplies on the second. Thissequence will gradually build up assets on themartian surface so that at the end of the thirdcrew’s tour of duty, the basic infrastructurecould be in place to support a permanentpresence on Mars.

3.5.4.1 First Mission: 2007 Opportunity

In the first opportunity, September 2007,three cargo missions will be launched onminimum energy trajectories direct to Mars(without assembly or fueling in LEO). Thefirst launch delivers a fully fueled ERV toMars orbit. The crew will rendezvous withthis stage and return to Earth after completionof their surface exploration in October 2011.

The second launch delivers a vehicle tothe Mars surface which is comprised of anunfueled MAV, a propellant production

Figure 3-7 Mars Reference Mission sequence.

1

2

3

6

4

5

9

7

8

12

10

ETOFLIGHT 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016

∆ MAV-1 landing

∆ Initial Habitat landing

∆ ERV-1 parks in LMO

∆ Crew 1 ascent

∆ Crew 1 TEI

∆ Crew 1 Earth return

ERV loiter

ERV loiter

ERV loiter

∆ ERV-2 parks in LMO

∆ MAV-2 landing

∆ MAV 3 landing

Crew 1: launch ∆ ∆ Landing

Crew 2 launch ∆

Crew 3 launch ∆

∆ Landing

∆ Landing

∆ ERV-3 parks in LMO

∆ Crew 2 TEI∆ Crew 2 Earth return

∆ MAV 4 landing

∆ Ascent

∆ Crew 2 ascent

∆ ERV 4 LMO

2017

∆ Crew 3 TEI

2018

∆ Crew 3 Earth return

ERV loiter

11

ERV: Earth Return VehicleMAV: Mars Ascent VehicleTEI: Trans Earth InjectionLMO: Low Mars Orbit

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module, a nuclear power plant, liquidhydrogen (to be used as a reactant to producethe ascent vehicle propellant), andapproximately 40 tonnes of additionalpayload to the surface. After this vehiclelands on the surface in late August 2008, thenuclear reactor will be autonomouslydeployed approximately 1 kilometer from theascent vehicle, and the propellant productionfacility (using hydrogen brought from Earthand carbon dioxide from the Marsatmosphere) will begin to produce the nearly30 tonnes of oxygen and methane that will berequired to launch the crew to Mars orbit inOctober 2011. This production will becompleted within approximately 1 year—several months before the first crew’sscheduled departure from Earth in mid-November 2009.

The third launch in the 2007 opportunitywill deliver a second lander to the Marssurface; it will be comprised of a surfacehabitat/laboratory, nonperishableconsumables for a safe haven, and a secondnuclear power plant. It will descend to thesurface in early September 2008 and land nearthe first vehicle. The second nuclear powerplant will be autonomously deployed nearthe first plant. Each plant will providesufficient power (160 kWe) for the entiremature surface outpost, thereby providingcomplete redundancy within the powerfunction. The outpost laboratory will includetools, spare parts, and teleoperated rovers tosupport scientific exploration and willprovide geological and biological analyses.

Table 3-3 lists the various payload itemsdeployed to the surface during the firstopportunity. And Figure 3-8 illustrates thesurface outpost configuration afterdeployment of payloads from the first twocargo landers.

3.5.4.2 Second Mission: First Flight Crew,2009 Opportunity

In the second opportunity, opening inOctober 2009, two additional cargo missionsand the first crew mission will be launched.Before either the crew or additional cargomissions are launched from Earth in 2009, allassets previously delivered to Mars arechecked out and the MAV launched in 2007 isverified to be fully fueled. Should anyelement of the surface system required forcrew safety or critical for mission success notcheck out adequately, the surface systems willbe placed in standby mode and the crewmission delayed until the systems can bereplaced or their functions restored. Some ofthe systems can be replaced using hardwareoriginally intended for subsequent missionsand which would have otherwise providedsystem enhancement; others may befunctionally replaced by other systems.

Table 3-4 lists the manifested payloadsfor launch in the 2009 opportunity.

The first cargo launch in October 2009 is aduplicate of the first launch from the 2007opportunity, delivering a fully fueled Earth-return stage to Mars orbit. The second cargolaunch similarly mirrors the second launch ofthe 2007 opportunity, delivering a second

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unfueled ascent stage and propellantproduction module. These systems providebackup or extensions of the previouslydeployed capabilities. For example, thesecond MAV and second ERV provide the2009 crew with two redundant means for eachleg of the return trip. If, for some reason,either the first ascent stage or the first ERVbecome inoperable after the first crew departsEarth in 2009, the crew can use the systemslaunched in 2009 instead. They will arrive in

plenty of time to be available for the crew’sdeparture from Mars in October 2011. If theMAV and ERV delivered in 2007 operate asexpected, then the systems delivered in 2009will support the second crew of six that willlaunch to Mars early in 2012.

The first crew of six will depart for Marsin mid-November 2009. They leave Earthafter the two cargo missions launched inOctober 2009, but because they are sent on afast transfer trajectory of only 180 days, they

Table 3-3 General Launch Manifest: 2007 Launch Opportunity

Flight 1: Cargo Flight 2: Cargo Flight 3: Cargo

Surface Payload

• None • Ascent Capsule • Surface Habitat/Laboratory• Empty Ascent Stage • Nonperishable• LOX/CH4 Production Consumables Plant • Power Supply (nuclear-• LH2 Propellant Seed 160 kW)• Power Supply (nuclear- • Utility Truck 160 kW) • Spares• Utility Truck • Teleoperable Science• Pressurized Rover Rover• Additional Payload

Mars Orbit Payload

• Earth-Return Vehicle • None • None• Fueled (LOX/CH4) TEI Stage• Transit Habitat• Earth-Return Capsule

Space Transportation Vehicles

• NTR Transfer Stage • NTR Transfer Stage • NTR Transfer Stage• LOX/CH4 TEI Stage • LOX/CH4 Descent • LOX/CH4 Descent w/Mars Aerobrake Stage w/Mars Stage w/Mars

Aerobrake Aerobrake

TEI: Trans Earth Injection LOX: liquid oxygen LH2: liquid hydrogenNTR: Nuclear Thermal Rocket CH4: methane

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will arrive in Mars orbit approximately 2months prior to the cargo missions. Once theTMI burn has been completed, the crew mustreach the surface of Mars. During theoutbound portion of this mission, the crewwill use their time to monitor and maintainsystems on board the transit spacecraft,monitor and maintain their own physicalcondition, and train for those activitiesassociated with capture and landing at Mars.

Additional time will be available during theoutbound leg to conduct experiments andcontinue a dialog with Earth-bound scienceand exploration teams who may revise orrefine the initial set of surface activitiesconducted by this crew. The crew carries withthem sufficient provisions for the entire 600-day surface stay in the unlikely event thatthey are unable to rendezvous on the surfacewith the assets previously deployed.

Table 3-4 General Launch Manifest: 2009 Launch Opportunity

Flight 4: Cargo Flight 5: Cargo Flight 6: First Crew

Surface Payload

• None • Ascent Capsule • Crew• Empty Ascent Stage • Surface Habitat• LOX/CH4 Production • Consumables Plant • Spares• LH2 Propellant Seed • EVA Equipment• Bioregenerative Life • Science Equipment Support Outfitting Equipment• Science: 1 km drill• Science Equipment• Additional Payload /Spares

Mars Orbit Payload

• Earth-Return Vehicle • None • None• Fueled (LOX/CH4) TEI Stage• Transit Habitat• Earth-Return Capsule

Space Transportation Vehicles

• NTR Transfer Stage • NTR Transfer Stage • NTR Transfer Stage• LOX/CH4 TEI Stage • LOX/CH4 Descent • LOX/CH4 Descent w/Mars Aerobrake Stage w/Mars Stage w/Mars

Aerobrake Aerobrake

TEI: Trans Earth Injection LOX: liquid oxygen LH2: liquid hydrogenNTR: Nuclear Thermal Rocket CH4: methane

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The crew will land on Mars in a surfacehabitat almost identical to the habitat/laboratory previously deployed to the Marssurface. The transit habitat sits atop a descentstage identical to those used in the 2007opportunity. After capturing into a highlyelliptic Mars orbit (250 by 33793 km), the crewdescends in the transit habitat to rendezvouson the surface with the other elements of thesurface outpost. There is no requiredrendezvous in Mars orbit prior to the crewdescent. This is consistent with the riskphilosophy assumed for the ReferenceMission.

Figure 3-9 illustrates the surface outpostconfiguration at the end of the first crew's stay.

Surface exploration activity will consistof diverse observations by robotic vehiclesand human explorers, the collection ofsamples and their examination in the outpostlaboratory, and experiments designed togauge the ability of humans to inhabit Mars.Table 3-5 lists a representative set of scienceand exploration equipment that will bedelivered as part of the cargo on Flight 5.These payloads are simply examples; theselection of specific experimental capabilitywill depend on the requirements of martianscience at the time that the missions aredefined in detail. There is also a categorylisted for “discretionary principal investigator(PI) science.” This category of experimentalequipment will be allocated to investigatorswho have competed through a proposal andpeer review process and are selected for oneof these flights. This allows a wider range of

investigations and participants in theexploration of Mars.

Prior to the arrival of the first humancrew, teleoperated rovers (TROV) may bedelivered to the surface. When the crewarrives, these rovers will be available forteleoperation by the crew. It is also possiblefor the rovers to be operated in a supervisedmode from Earth. If used in this mode, theTROVs may be designed to provide globalaccess and may be able to return samples tothe outpost from hundreds of kilometersdistance from the site if they are deployedwith the first set of cargo missions launchedmore than 2 years before the crew arrives.

As experience grows, the range of humanexploration will grow from the local to theregional. Regional expeditions lastingperhaps 2 weeks, using mobile facilities, maybe conducted at intervals of a few months.Between these explorations, analysis in thelaboratory will continue. Figure 3-10 (Cohen,1993) provides a possible surface missiontimeline for the first 600-day mission.

The deployment of a bioregenerative lifesupport capability will be an early activityfollowing crew landing. This bioregenerativesystem is not required to maintain the healthand vitality of the crew; however, it willimprove the robustness of the life supportsystem and is important to the earlyobjectives of the outpost.

The first crew will stay at the outpostfrom 16 to 18 months. Part of their duties willbe to prepare the outpost site for the receipt of

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additional elements launched on subsequentmission opportunities. Systems associatedwith the ascent vehicle, although monitoredduring the entire stay on the surface, will bechecked and, if necessary, tested in detail toensure that they will operate satisfactorily.The surface crew will also spend increasingamounts of time rehearsing the launch andrendezvous phase of the Mars departure tosharpen necessary skills that have not beenused in over 2 years. Because the first crewwill have to depart before the second crewarrives, surface systems will have to be instandby mode for approximately 10 months.

After their stay on Mars, the crew usesone of the previously landed ascent vehiclesto return to orbit, rendezvous with the ERV,and return to Earth. Like the outbound transitleg, the crew rides in a habitat on the inboundtransit leg. This habitat is part of the Earth-return stage deployed in a previousopportunity by one of the cargo flights and

typically has been in an untended mode fornearly 4 years prior to the crew’s arrival.

During the return portion of the mission,the crew will again spend a significantportion of their time monitoring andmaintaining systems on board the transitspacecraft, monitoring and maintaining theirphysical condition, and training for theactivities associated with Earth return. Asmentioned previously, the second crew willbe in transit to Mars during a portion of thefirst crew’s return to Earth. This implies that adebriefing of the first crew, to gain insightfrom lessons learned and suggestions forfuture surface activities, will begin during thisreturn phase. This debriefing will be relayedto the outbound crew so that they canparticipate in the interaction with thereturning crew and modify their plans to takeadvantage of the first crew’s experience.

On landing, the first crew and theirreturned samples will be placed in quarantine

Table 3-5 Surface Science Payload for First Flight Crew

Payload Description Payload Mass (kg)Field Geology Package: geologic hand tools, cameras, 335 sample containers, documentation toolsGeoscience lab instruments: microscopes, 125 geochemical analysis equipment, cameraExobiology laboratory: enclosures, microscopes, 50 culture mediaBiomedical/bioscience lab 500Traverse geophysics instruments 400Geophysics/meteorology instruments (8 sets) 20010-meter drill 260Meteorology balloons 200Discretionary PI science 300Total 2370

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Figure 3-10 Possible surface mission time line.

Mars Surface Mission Time Allocation

(Total Time = 8 crew X 24 hr/day X 600 days = 115,200 hr)

8 crew X 24 hr day = 200)

Charge Fuel CellsCheck VehicleLoad VehiclePlan ExcursionDrive VehicleNavigateDon Suits (X 20)Pre-breathe (X 20)Egress (X 20)Unload EquipSet up Drill (X 10)Operate DrillCollect SamplesIn Situ AnalysisTake PhotosCommunicateDisassemble EquipLoad VehicleIngress (X 20)Clean Suit (X 20)Stow Suit, EquipInspect VehicleSecure for night(Sleep, eat, cleanuphygiene, etc.covered)

3 Crew X 7 hr X 10 Day =210 hrs total

600

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Analysis

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Analysis

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Analysis

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Analysis

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Week Off

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Personal14 hr

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3 hr(14,400 hr)

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90 days

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Figure 3-11 illustrates the surface outpostconfiguration at the end of the second crew'sstay.

As before, the second crew will continuewith the general type of activities conductedby the first crew: diverse observations byrobotic vehicles and human explorers,collection of samples and their examination inthe outpost laboratory, and experimentsdesigned to gauge the ability of humans toinhabit Mars. Specific crew activities willbuild on the lessons learned and questionsgenerated by the first crew. Table 3-7 lists arepresentative set of science and explorationequipment that will be delivered as part ofthe cargo on Flight 8. Note in particular thatthis manifest contains a drill designed toreach depths of 1 kilometer. (The deep drillingoperation must be consistent with planetaryprotection protocols.) This tool will be used togather subsurface core samples that will helpreconstruct the geologic history of Mars, andto try to locate subsurface deposits of water ineither liquid or solid form. Such a discoverywill substantially enhance the habitabilityprospects for future crews by possiblyupgrading propulsion systems to the use ofhydrogen and oxygen and expandingagricultural activities.

The second crew will repeat the activitiesof the first crew in preparing themselves, theascent vehicle, and the surface habitat for adeparture from Mars during December 2013.The third crew will already be in transit to

in accordance with the protocols in effect atthe time. The crew’s re-adaptation to a 1-genvironment will be monitored in detail tolearn more about how the human bodyadapts to the varying gravity conditions andto better prepare for the return of subsequentcrews.

3.5.4.3 Third Mission: Second Flight Crew,2011 Opportunity

In the third opportunity opening inDecember 2011, two additional cargomissions and the second crew mission will belaunched. As in the second opportunity, allassets previously delivered to Mars arechecked out and the MAV is verified to befully fueled. Any non-mission-criticalmaintenance items identified by the first crewor items noted prior to the departure ofFlights 7 through 9 are added to the sparesmanifest and delivered with other surfaceequipment. Table 3-6 lists the manifestedpayloads for launch in the 2011 opportunity.

Prior to the arrival of the second crew, theISRU plants are producing not only thepropellants needed for the ascent vehicle, butalso water, oxygen, and buffer gases to serveas an emergency cache for the life supportsystem. Teleoperated rovers are deployed onextended traverses, perhaps to distances ofmore than 100 kilometers, to take measure-ments, gather samples, and reconnoiter sitesfor the human crew to investigate in moredetail.

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Mars, again necessitating a debriefing of thesecond crew, with participation by the thirdcrew, during the return to Earth. Once onEarth, the second crew will likely benefit fromobservations of the first crew, particularly inthe areas of modifications to the re-adaptationregime and quarantine protocols.

3.5.4.4 Fourth Mission: Third Flight Crew,2014 Opportunity

In the fourth opportunity opening inMarch 2014, the final two cargo missions and

the third crew mission will be launched. As inthe second and third opportunities, all assetspreviously delivered to Mars are checked outand the MAV is verified to be fully fueled.Any non-mission-critical maintenance itemsidentified by the first two crews or itemsnoted prior to the departure of Flights 10through 12 are added to the spares manifestand delivered with other surface equipment.Table 3-8 lists the manifested payloads forlaunch in the 2014 opportunity. As listed, themanifests do not use the full cargo-carrying

Table 3-6 General Launch Manifest: 2011 Launch Opportunity

Flight 7: Cargo Flight 8: Cargo Flight 9: Second Crew

Surface Payload

• None • Ascent Capsule • Crew• Empty Ascent Stage • Surface Habitat• LOX/CH4 Production • Consumables Plant • Spares• LH2 Propellant Seed • EVA Equipment• Pressurized Rover • Science Equipment• Science Equipment• Additional Payload/ Spares

Mars Orbit Payload

• Earth-Return Vehicle • None • None• Fueled (LOX/CH4) TEI Stage• Transit Habitat• Earth-Return Capsule

Space Transportation Vehicles

• NTR Transfer Stage • NTR Transfer Stage • NTR Transfer Stage• LOX/CH4 TEI Stage • LOX/CH4 Descent • LOX/CH4 Descent w/Mars Aerobrake Stage w/Mars Aerobrake Stage w/Mars Aerobrake

TEI: Trans Earth Injection LOX: liquid oxygen LH2: liquid hydrogenNTR: Nuclear Thermal Rocket CH4: methane

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capacity of the landers. The experience gainedby the first two crews will dictate anyadditional equipment that can be used toeither upgrade existing equipment or addnew equipment to enhance the capabilities ofthis outpost.

Prior to the arrival of the third crew, theISRU plants are again producing not only thepropellants needed for the ascent vehicle, butalso water, oxygen, and buffer gases to serveas an emergency cache for the life supportsystem. Teleoperated rovers are againdeployed on extended traverses to takemeasurements, gather samples, andreconnoiter sites for the third crew toinvestigate in greater detail.

Figure 3-12 illustrates the surface outpostconfiguration at the end of the third crew'sstay. This represents the complete outpostconfiguration as envisioned by the MarsStudy Team. With the facilities and

capabilities available at this stage, the surfaceoutpost will be able to support larger crewsfor longer periods of time. The potential levelof self-sufficiency on Mars should also beevident by this time, and a decision can bemade regarding any further use or expansionof the outpost.

As before, the third crew will continuewith the general type of activities conductedby the first and second crews: diverseobservations by robotic vehicles and humanexplorers, collection of samples and theirexamination in the outpost laboratory, andexperiments designed to gauge the ability ofhumans to inhabit Mars. Specific crewactivities will build on the lessons learnedand questions generated by the first twocrews and should be focused on providinginformation needed to determine the futurestatus of the outpost. Table 3-9 lists arepresentative set of science and exploration

Table 3-7 Surface Science Payload for Second Flight Crew

Payload Description Payload Mass (kg)Field Geology Package: geologic hand tools, cameras, 335 sample containers, documentation toolsGeoscience lab instruments: microscopes, 125 geochemical analysis equipment, cameraExobiology laboratory: enclosures, microscopes, 50 culture mediaBiomedical laboratory 500Plant and animal lab 500Traverse geophysics instruments 400Geophysics/meteorology instruments (8 sets) 2001 kilometer drill 20,00010-meter drill 260Meteorology balloons 200Discretionary PI science 600Total 23,000

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equipment that will be delivered as part ofthe cargo on Flight 11.

As with the first two crews, the thirdcrew will repeat those activities necessary toprepare themselves, the ascent vehicle, andthe surface habitat for a departure from Marsduring January 2016.

3.5.4.5 Mission Summary

This section has illustrated a feasiblesequence of missions that can satisfy theReference Mission goals and objectives. These

missions use assumed hardware systems andmission design principles to place the flightcrews in the martian environment for thelongest period of time at a satisfactory level ofrisk. The major distinguishing characteristicsof the Reference Mission, compared toprevious concepts, include:

•No extended LEO operations, assembly,or fueling

•No rendezvous in Mars orbit prior tolanding

Table 3-8 General Launch Manifest: 2014 Launch Opportunity

Flight 10: Cargo Flight 11: Cargo Flight 12: Third Crew

Surface Payload

• None • Ascent Capsule • Crew• Empty Ascent Stage • Surface Habitat• LOX/CH4 Production • Consumables Plant • Spares• LH2 Propellant Seed • EVA Equipment• Science Equipment • Science Equipment• Additional Payload/ Spares

Mars Orbit Payload

• Earth-Return Vehicle • None • None• Fueled (LOX/CH4) TEI Stage• Transit Habitat• Earth-Return Capsule

Space Transportation Vehicles

• NTR Transfer Stage • NTR Transfer Stage • NTR Transfer Stage• LOX/CH4 TEI Stage • LOX/CH4 Descent • LOX/CH4 Descent w/Mars Aerobrake Stage w/Mars Aerobrake Stage w/Mars Aerobrake

TEI: Trans Earth Injection LOX: liquid oxygen LH2: liquid hydrogenNTR: Nuclear Thermal Rocket CH4: methane

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•Short transit times to and from Mars (180days or less) and long surface stay-times(500 to 600 days) for the first and allsubsequent crews exploring Mars

•A heavy-lift launch vehicle (HLLV),capable of transporting either crew orcargo direct to Mars, and capable ofdelivering all needed payload with atotal of four launches for the first humanmission and three launches of cargo andcrew for each subsequent opportunity

•Exploitation of indigenous resourcesfrom the beginning of the program, withimportant performance benefits andreduction of mission risk

•Availability of abort-to-Mars-surfacestrategies, based on the robustness of theMars surface capabilities and the cost oftrajectory aborts

The characteristics of the hardwaresystems used in these missions are morecompletely discussed in the followingsections.

3.6 Systems

The following sections discuss thecharacteristics and performance capabilitiesof the various hardware elements needed forthe Reference Mission. The hardwareelements include a launch vehicle largeenough to place cargo bound for Mars into asuitable Earth parking orbit, theinterplanetary transportation elementsnecessary to move crew and equipment fromEarth to Mars and back, and the systemsneeded to sustain the crew and perform theproposed exploration activities on the martiansurface. Each section describes the principalcharacteristics of the hardware system asdeveloped by the Mars Study Team.

Payload Description Payload Mass (kg)Field Geology Package: geologic hand tools, cameras, 335 sample containers, documentation toolsGeoscience lab instruments: microscopes, 125 geochemical analysis equipment, cameraExobiology laboratory: enclosures, microscopes, 50 culture mediaPlant and animal lab 500Traverse geophysics instruments 400Geophysics/meteorology instruments (8 sets) 200Advanced Meteorology Laboratory 100010-meter drill 260Meteorology balloons 200Discretionary PI science 1000Total 4070

Table 3-9 Surface Science Payload for Third Flight Crew

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3.6.1 Operational DesignConsiderations

Several operational factors related toutilization, training, and repair influence thedesign of hardware and software systems forall vehicles. Early incorporation of thesefactors into the vehicle design process willenhance utility and functionality of thesystems, prevent costly workarounds late inthe development cycle, and maximize overallmission success.

This section discusses some of the designconsiderations identified as important in theeventual detailed design and construction ofsystems used for the Reference Mission.While the system descriptions in the sectionsthat follow may not reach a level of detail thatreflects the specific topics mentioned here, thedesign considerations should be consideredas guiding principles that should be used asmore detailed studies are performed.

A primary operational consideration insystem development is the subsequent easewith which users, specifically crew members,can become familiar with the system prior tothe mission. The more familiar crew membersare with vehicle hardware and software, theless time will be spent on systems operationsand the more time will be available forscience and exploration activities. By the sametoken, the more familiar technicians are withthe systems, the easier and less costlyproduction, maintenance, and repair will beduring the development process. To facilitatethis, all vehicles and systems need to use

common hardware and software whereapplicable. System commonality in powersources, interfaces, payload locker sizes, etc.,among all vehicles will ease nominaloperational activities such as replacements,reconfigurations, and hardware transfers.Commonality will also help maintaincorporate knowledge bases and simplify crewoperations and repair procedures asexperience with one system can be applied tomany. The cost savings associated with theuse of common hardware and softwareelements are obvious, and may be increasedby using as much off-the-shelf hardware aspossible. This, too, helps with familiarity ascrews and technicians may have previousexperience with similar systems. Repairoperations will also be simplified by requiringa smaller set of standard tools for use by thecrew during mission execution.

The need for training facilities will have asignificant impact on vehicle design. Due tothe extended duration of the mission, trainingfacilities will be required on board crewvehicles during various phases of the mission.Trainers on Earth will need to match trainerson vehicles which in turn will need to matchactual system performance. The requirementfor crew training facilities during variousmission phases will place additionalhardware and software design constraints onthe vehicles. Incorporation of trainingfacilities into appropriate vehicles is animportant operational factor influencing thedesign process.

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For both crew safety and operationalsimplicity, system designs will require somelevel of automatic fault detection for all life-critical, mission-critical, and mission-discretionary elements. For those elementspertaining to crew safety and mission-criticalobjectives, auto-fault detection and correctionshould be incorporated into the design. Crewaction should not be required for life-criticalsystems failures; backup system activationshould be automatic. Mission-critical systemfailures should be as automated as possible,leaving only the most complex tasks (such ascomplete hardware replacement or repair) tothe crew. In addition, many of the routine, yetimportant, system operations should beautomated to the greatest extent possible. Forexample, an often overlooked aspect ofoperations is consumables tracking andforecasting for all life-critical and mission-critical systems. Crew time is better spent onscience activities than on tracking andforecasting consumables such as propellant,water, and breathable air. Many of thesefunctions are currently done for Space Shuttlecrews by flight controllers on the ground. Dueto the long delay time in communicationsduring the Reference Mission, maintenance ofthis function by ground personnel isimpractical. Periodic verification ofconsumables tracking activities by groundpersonnel can validate the crew activities;however, means by which the crew canindependently monitor and forecastpropulsive and nonpropulsive consumableswhile not expending significant resources is anecessity. Where cost effective, mission-

discretionary system failures can requiresome crew response to enhance missionobjectives. A balance between the cost ofautomation and crew time and training forsuch activities will be needed. In general,maximizing crew science time andminimizing crew system maintenance andoperations throughout the mission willimprove overall mission success.

3.6.2 Launch Vehicles

The scale of the ETO launch capability isfundamentally determined by the mass of thepayload that will be landed on the martiansurface. The nominal design mass forindividual packages to be landed on Mars inthe Reference Mission is 50 tonnes for a crewhabitat (sized for six people) which must betransferred on a high-energy, fast-transit orbit.This in turn scaled the required mass in LEOto about 240 tonnes.

A number of different technologies couldbe used to construct a single launch vehiclecapable of placing 240 tonnes into a 220-nautical mile circular orbit. These launchvehicle concepts used various combinationsof past, present, and future U.S. expendablelaunch vehicle technology and existing launchvehicle technology from Russia and Ukraine.Table 3-10 summarizes some of the keyparameters for a representative set of thevehicle options examined (Huber, 1993). Eachoption is covered in more detail in thefollowing paragraphs.

Option 1 (Figure 3-13) illustrates thecapabilities possible through the use of

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Energia and Zenit launch vehicle technologycombined with STS technology. All of theengines used for this option are existing typesthat have flown numerous times. The corestage is assumed to be a modification of theexisting Energia stage. The modificationinvolves changing the vehicle from one thatuses a side-mounted payload container to anin-line configuration with strap-on boosterssurrounding the core. The upper stage is anew development using STS external tanktechnology combined with a single SSME.The shroud is entirely new and would besized for the largest of the Reference Missionpayloads. Note, however, that this

combination of largely existing componentsdoes not meet the desired payload launchmass.

Option 2 (Figure 3-14) illustrates what ispossible if a large launch vehicle makesextensive use of existing STS and Russiantechnology. The first stage core and upperstage use the SSME, and the propellant tankstructure is based on the STS external tank.Strap-on boosters for this vehicle use theRussian RD-170 engine and a newly designedpropellant tank structure. Note that thiscombination also does not meet the desiredpayload launch mass.

Option Payload Mass (tonnes) to 220 Key Technology Assumptionsn.mi. Circular Orbit

1 179 Modified Energia core with eight Zenit-type strap-on boosters. New upper stageusing a single Space Shuttle Main Engine(SSME).

2 209 New core stage based on SpaceTransportation System (STS) external tankand SSMEs. Seven new strap-on boosterseach use a single RD-170 engine. Newupper stage using a single SSME.

3 226 New core stage based on STS external tankand four of the new Space TransportationMain Engines. Four strap-on boosters eachwith a derivative of the F-1 engine used onthe first stage of the Saturn V. New upperstage using a single SSME.

4 289 New vehicle using technology derivedfrom the Saturn V launch vehicle. Boostersand first stage use a derivative of the F-1engine, and the second stage uses aderivative of the J-2 engine.

Table 3-10 Launch Vehicle Concepts for the Reference Mission

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Figure 3-13 Mars Energia-derived HLLV with eight Zenit-type boosters.

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Figure 3-14 STS External Tank-derived HLLV with seven LOX/RP boosters.

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Option 3 (Figure 3-15) uses new and oldas well as existing technology to create avehicle that can deliver a payload that isreasonably close to the desired value. The firststage core propellant tank structure is basedon the STS external tank but uses newlydesigned and as yet untested STME engines.The strap-on boosters use an updated versionof the F-1 engine that powered the first stageof the Saturn V in conjunction with newlydesigned propellant tanks. The upper stage iscomparable to those discussed for the firsttwo options, using STS external tanktechnology and a single SSME.

Option 4 (Figure 3-16) is indicative of alaunch vehicle that uses technology derivedfrom the Saturn V launch vehicle. The firststage core is virtually identical to the firststage of the Saturn V launch vehicle in itsbasic size and its use of five F-1A engines.Strapped to this stage are four boosters, eachwith two F-1A engines and roughly one-thirdof the propellant carried by the core stage.The second stage uses six of the J-2 enginesthat powered the second stage of the SaturnV. However, this upper stage is considerablylarger than the Saturn second stage.

This last option was the largest of afamily of launch vehicles derived usingSaturn V launch vehicle technology. Figure3-17 illustrates some of the other vehicleconfigurations examined and providesadditional information on their capabilities.All of these options can deliver a payloadalmost as large as the stated need for 240tonnes in a 220-nautical mile circular orbit.

Because a 240-ton-class launch vehiclewould be such a development cost issue,consideration was given to the option oflaunching several hardware elements to LEOusing smaller vehicles, assembling (attaching)them in space, and then launching on theoutbound trajectory to Mars. This smallerlaunch vehicle (with a 110- to 120-ton payloadcapability) would have the advantage of moremodest development costs and is in theenvelope of capability demonstrated by theunmodified U.S. Saturn V and RussianEnergia programs (Figure 3-18). However,this smaller launch vehicle introduces severalpotential difficulties to the Reference Missionscenario. The most desirable implementationusing this smaller launch vehicle is to simplydock the two elements in Earth orbit andimmediately depart for Mars. To avoid boilofflosses in the departure stages (assumed to useliquid hydrogen as the propellant), allelements must be launched from Earth inquick succession, placing a strain on existinglaunch facilities and ground operations crews.Assembling the Mars vehicles in orbit andloading them with propellants just prior todeparture may alleviate the strain on launchfacilities, but the best Earth orbit for Marsmissions is different for each launchopportunity, so a permanent constructionand/or propellant storage facility in a singleEarth orbit introduces additional constraints.

Several launch vehicle designs that couldprovide this smaller payload capability usingexisting or near-term technology wereexamined. Figure 3-19 illustrates one possible

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Figure 3-15 STS External Tank-derived HLLV with four strap-on boosters, eachhaving two F-1 engines.

3-68

Figure 3-16 Saturn V-derived Mars HLLV with F-1A/J-2S propulsion.

3-69

Figure 3-17 Saturn V-based Mars HLLV concepts.

2x2 F-1A Boost5 F-1A Core6 J-2S 2nd Stage

10 m

237 t

Veh

icle

Hei

ght (

ft.)

400

VAB Height Limit - 410'

300

200

100

0

2x2 F-1A Boost5 F-1A Core6 J-2S 2nd Stage

13 m

228 t

2x2 F-1A Boost5 F-1A Core6 J-2S 2nd Stage

16 m

219 t

2x2 F-1A Boost5 F-1A Core6 J-2S 2nd Stage

17 m

285 t

2x2 F-1A Boost5 F-1A Core6 J-2S 2nd Stage

14 m

289 t

Shroud Diameter (Usable)

Payload to 220 nm Circular*

(Kickstage performs circ.)

3-70

Figure 3-18 Energia launch vehicle adapted to Mars mission profile.

3-71

320 ft

172 ft

89 ft

27.6 ft D

Side View Base View

Figure 3-19 Mars mission launch vehicle with two external tank boosters andkick stage.

3-72

vehicle configuration and provides additionalinformation on its capabilities. This particularoption uses the STS external tank for itspropellant storage and main structure.Engines for the core stage and the two strap-on boosters were assumed to be the STMEengine that was under development at thetime of this study.

A 240-ton payload-class launch vehicle isassumed for the Reference Mission. However,it is beyond the experience base of anyspacefaring nation. While such a vehicle ispossible, it would require a significantdevelopment effort for the launch vehicle,launch facilities, and ground processingfacilities; and its cost represents aconsiderable fraction of the total mission cost.The choice of a launch vehicle remains anunresolved issue for any Mars mission.

3.6.3 Interplanetary Transportation

The interplanetary transportation systemassembled for the Reference Mission consistsof seven major systems: a TMI stage, abiconic aeroshell for Mars orbit capture andMars atmospheric entry, habitation systemsfor the crew (both outbound and return), adescent stage for landing on the surface, anascent stage for crew return to Mars orbit, anERV for departure from the Mars system, andan ECCV (comparable to Apollo) for Earthentry and landing. As mentioned earlier, theReference Mission splits the transportation ofpeople and equipment into cargo missionsand human missions, all of which are targetedto the same locale on the surface and must be

landed in close proximity to one another. Thetransportation strategy adopted in theReference Mission eliminates the need forassembly or rendezvous in LEO of vehicleelements and for rendezvous of a crewtransport vehicle with a Mars lander in Marsorbit, both features of many previous missiondesigns for Mars (NASA, 1989). But theReference Mission scenario does require arendezvous on the surface with previouslylanded hardware elements and a rendezvousin Mars orbit with the ERV as the crew leavesMars. The transportation strategy emphasizedthe use of common elements whereverpossible to avoid development costs and toprovide operational simplicity.

3.6.3.1 Trans-Mars Injection Stage

A single TMI stage was developed forboth piloted and human missions. The stageis designed for the more energeticallydemanding 2009 human mission and is thenused in the minimum energy cargo missionsto launch the maximum payload possible toMars. Because of the energetic trajectoriesused for human flights and the desire todeliver large payloads to the martian surface,nuclear thermal propulsion was selected forthis stage not only for its performanceadvantages but also because of its advanced,previously demonstrated state of technologydevelopment, its operational flexibility, andits inherent mission enhancements and crewrisk reduction (Borowski, et al., 1993).

After completion of two TMI burns(required by the selected thrust-to-weight

3-73

ratio), the stage is disposed of by allowing itto drift on a relatively stable interplanetarytrajectory. Calculations (Stancati and Collins,1992) using the Planetary EncounterProbability Analysis code indicate that theprobability of a collision of a nuclear engine-equipped vehicle and the Earth is quite low.The probabilities of a collision with Earth inone million years are 3.8 percent for thepiloted TMI stages and 12 percent for thecargo TMI stages.

The basic TMI stage is shown in Figure3-20. For piloted missions, the TMI stage usesfour 15,000 lb. thrust NERVA* derivative(ND) engines to deliver the crew and theirsurface habitat/descent stage onto the trans-Mars trajectory. Engines of this size are wellwithin the previous development history ofNERVA engines (Borowski, et al., 1993). Thisversion of the TMI stage incorporates ashadow shield between the ND engineassembly and the LH2 tank to protect the crewfrom radiation generated by the engines thatwill have built up during the TMI burns. Forcargo missions, this transportation system candeliver approximately 65 tonnes of usefulcargo to the surface of Mars or nearly 100tonnes to Mars orbit (250 I 33,793 km) on asingle launch from Earth. The TMI stage forcargo delivery requires only the use of three

ND engines. So for cost and performancereasons, one ND engine and the shadowshield are removed from this version of theTMI stage.

The TMI stage adopted for the ReferenceMission could be designed around any of fourreactor options studied by the Team: (1)Rocketdyne and Westinghouse NERVA-derivative reactor (ND), (2) Pratt and Whitneyand Babcock and Wilcox (B&W) CERMET fastreactor, (3) Aerojet and B&W particle bedreactor and (4) Russian Energopool and B&Wengine concept using the “twisted ribbon”ternary carbide fuel form. Work done inRussia is especially promising, with thepossibility of higher Isp (approximately 950seconds versus a 900-second demonstratedcapability by NERVA engines) at a thrust-to-weight ratio of about 3.0 (for a 15,000 poundthrust engine) being a possible developmenttarget. The Reference Mission adopts themore conservative ND engine concept, with aprojected Isp performance of 900 seconds.Table 3-11 lists the mass estimates for thevarious components of the TMI stage forpiloted and cargo versions. In both versions,this stage is assumed to have a maximumdiameter of 10 meters and an overall length of25.3 meters.

3.6.3.2 Biconic Aeroshell

On each cargo and piloted mission, Marsorbit capture and the majority of the Marsdescent maneuver are performed using asingle biconic aeroshell. The decision toperform the Mars orbit capture maneuver

From 1955 to 1973, the Nuclear Engine for RocketVehicle Application (NERVA) program designed, built,and tested a total of twenty rocket reactors. Thefeasibility of using low molecular weight LH2 as both areactor coolant and propellant was convincinglydemonstrated.

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Figure 3-20 Reference Mars cargo and piloted vehicles.

IMLEO Initial Mass to Low Earth OrbitTEIS Trans Earth Injection Stage

2007 Cargo Mission 1"Dry" Ascent Stage & Lander

2007 Cargo Mission 2Hab Module & Lander

2007 Cargo Mission 3LOX/CH4 TEIS & Hab

2009 Piloted Mission 1Surface Hab with Crew and Lander

IMLEO = 216.6 t 216.6 t 204.7 t 212.1 t

* Expendable TMI Stage LH2 Tank (@ 18.2 m length) sized by 2009 Mars Piloted Mission

20.6 m*

4.7 m

10 m 10 m 10 m 10 m

86.0 t LH2

(@ 100%)

86.0 t LH2

(@ 100%)

86.0 t LH2

(@ 91.9%)

86.0 t LH2

(@ 100%)

15.0 m

16.3 m

19.0 m 7.6 m

16.3 m

3-75

using an aeroshell (that is, aerocapture) wasbased on the fact that this option typicallyrequires less mass than an equivalentpropulsive capture stage (Cruz, 1979), andaerodynamic shielding of some sort will berequired to perform the Mars descentmaneuver no matter what method is used tocapture into Mars orbit. Previous Marsmission concepts employing aerocapture havetypically used more than one aeroshell todeliver the crew to the surface. The use of twoaeroshells was driven by one or both of thefollowing factors. First, Mars entry speedsmay have been higher than those proposedfor the Reference Mission and therefore moremaneuverability and thermal protection wererequired for this phase of the mission. Second,the mission profile may have required a post-aerocapture rendezvous in Mars orbit withanother space transportation element,possibly delivered during the same launchopportunity or during a previousopportunity. Neither of these features is in theReference Mission. Thus, the strategyemployed was to develop a single family of

biconic aeroshells that can be used for bothMars orbit capture and descent maneuvers.Given the demands on a descent aeroshell ofthe Mars entry and landing requirements, theadditional capability to permit aerocapture isconsidered modest.

The aerodynamic maneuvering andthermal protection requirements for theaeroshells used in the Reference Mission werestudied in some detail (Huber, 1993). Basedon the studies, it was determined that abiconic aeroshell with similar forward and aftconic sections provided sufficientmaneuverability for the aerocapture andentry phases of flight. Figure 3-21 illustratestwo of these aeroshells, one for the Marsascent vehicle and the other for the surfacehabitat. For this family of aeroshells, the nosesection is a 25° half-angle cone ending in aspherical cap. The skirt section is a 4° half-angle cone with a 10-meter diameter base.The skirt section consists of two parts: a fixedlength aft section and a variable length centersection (“center” indicating its locationbetween the aft skirt and the nose section).

Table 3-11 Mass Estimates for TMI Stage Alternatives

TMI Stage Element Piloted Version Cargo Version

ND Engines (4 for piloted, 3 for cargo)Radiation ShieldTankage and StructureLH2 Propellant (maximum)Control System Tankage and Propellant

9.80.9

18.486.03.1

7.40.018.486.03.0

Total (tonnes) 118.2 114.8

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Figure 3-21 Biconic aeroshell dimensions for Mars lander and surface habitatmodules.

Cg = center of gravity

Cp = center of pressure

14.9 (m)

6.0 (m)

8.9 (m)

7.7 (m)to Cg& Cp

Dia = 10.0 (m) Dia = 10.0 (m)

25 %

4 %

18 (m)

Reference Biconic: 10 (m) Dia by 15 (m)length. I/D = 0.65 At 25° Angle of Attack

Extended Center Section Biconic10 (m) Dia by 18 (m) length.

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The length of the skirt center section isdetermined by the size of the payload carriedwithin. Table 3-12 lists the overall lengths ofthe various aeroshells used in the ReferenceMission.

Table 3-12 also lists an estimated mass forthe various aeroshells. The Mars Study Teamdid not conduct a detailed study of the massof the various aeroshells used. Based onprevious studies of aerocapture vehicles, asimple scaling factor of 15 percent of the entrymass was used to determine the aeroshellmass (Scott, et al., 1985). As more detailregarding the aeroshell is developed,variations in aeroshell mass will result causedby differences in the amount of thermalprotection material used (some missions areflown on faster trajectories and will encounterhigher entry speeds with correspondinglyhigher heat loads) and in the size of theaeroshell structure. At the present level of thisstudy, the simple scaling factor is consideredsufficient to estimate the aeroshell mass.

3.6.3.3 Transit/Surface Habitat

The crew is transported to Mars in ahabitat that is identical to the surface habitat/

laboratory deployed robotically on a previousmission. Although a smaller habitat mightsuffice for a crew of six during theapproximately 6 months of transit time,designing the habitat so that it can be usedduring transit and on the surface results in anumber of advantages to the overall mission.Duplicating habitats on the surface providesredundancy during the longest phase of themission and reduces the risk to the crew. Bylanding in a fully functional habitat, the crewdoes not have to transfer from a “space-only”habitat to the surface habitat immediatelyafter landing, allowing them to re-adapt to agravity environment at their own pace. Thisapproach also allows the development of onlyone habitat system instead of two or moreunique, specialized systems (although somesubsystems will have to be tailored for zero-goperation). The performance of the transithabitat may be tested by attaching adevelopment unit to the International SpaceStation (Figure 3-22).

Each habitation element will consist of astructural cylinder 7.5 meters in diameter and4.6 meters long with two elliptical end caps(overall length of 7.5 meters). The internal

Table 3-12 Mass and Size Estimates for Biconic Aeroshell Family

Aeroshell Payload Mass Estimate

(tonnes) Overall Length

(meters)

Ascent Stage and LanderSurface Habitat and LanderTEI Stage and HabitatSurface Habitat with Crew and Lander

17.317.317.317.3

15.016.319.016.3

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Fig

ure

3-2

2 Tr

ans

it ha

bita

t atta

che

d to

Inte

rna

tiona

l Sp

ac

e S

tatio

n.

3-79

volume will be divided into two levelsoriented so that each “floor” will be a cylinder7.5 meters in diameter and approximately 3meters in height. The primary and secondarystructure, windows, hatches, dockingmechanisms, power distribution systems, lifesupport, environmental control, safetyfeatures, stowage, waste management,communications, airlock function and crewegress routes will be identical to the otherhabitation elements (the surface habitat/laboratory and the Earth-return habitat). Afterestablishing these basic design features, thereexists an endless array of feasible internalarchitecture designs. Deciding among feasibleinternal designs involves a trade of resourcesderived from a specific set of habitation goals.At this level of detail, habitation goals aresomewhat subjective and open for discussion.Figures 3-23, 3-24, and 3-25 illustrate oneinternal arrangement for the transit/surfacehabitat that was investigated for feasibilityand cost purposes.

The Mars transit/surface habitat willcontain the required consumables for theMars transit and surface duration ofapproximately 800 days (approximately 180days for transit and approximately 600 dayson the surface) as well as all the requiredsystems for the crew during the 180-daytransfer trip. Table 3-13 provides a breakdownof the estimated masses for this particularhabitat.

Once on the surface of Mars, this transit/surface habitat will be physically connectedwith the previously landed surface laboratory,

doubling the usable pressurized volume (toapproximately 1,000 cubic meters) availableto the crew for the 600-day surface mission.This configuration is illustrated in Figure 3-26with the first of the transit habitats joined tothe previously landed surface habitat/laboratory.

3.6.3.4 Mars Surface Lander

A single common descent stage wasdeveloped for delivery of all hardwaresystems (the habitats, ascent vehicle,propellant production plant, and othersurface cargo) to the surface of Mars. The roleof this stage is to complete the descent-to-landing maneuver once the biconic aeroshellceases to be effective and to maneuver thesurface systems into the appropriate relativeposition at the surface outpost.

The descent stage consists of foursubsystems: a basic structure to which allother elements (including payload) areattached, a parachute system to assist inslowing the stage, a propulsion system toslow the stage prior to landing, and a surfacemobility system.

The use of parachutes has been assumedto help reduce the descent vehicle’s speedafter the aeroshell has ceased to be effectiveand prior to the final propulsive maneuver(Figure 3-27). Sufficient atmosphere is presentfor parachutes to be more effective than anequivalent mass of propellant.

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Figure 3-24 EVA suit storage locations are critical in a robust crew safety system.

Figure 3-23 The crew exercise facility component of the countermeasuressystem designed to inhibit crew degradation from exposure to reduced gravity

environments.

3-81

Figure 3-25 Conceptual Mars habitation module - wardroom design.

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The propulsion system employs fourRL10-class engines modified to burn LOX/CH4 to perform the post-aerocapturecircularization burn and to perform the finalapproximately 500 meters per second ofdescent velocity change prior to landing onthe surface.

Once on the surface, the lander can movelimited distances to compensate for landingdispersion errors and to move surfaceelements into closer proximity. This allows,for example, the surface laboratory to beconnected to the transit/surface habitats.Mobility system power is provided by on-board regenerative fuel cells and from the

previously landed pressurized rover. Figure3-28 illustrates one possible configuration forthis lander with its mobility system.

The descent lander is capable of placingapproximately 65 tonnes of cargo on thesurface. The dry mass of this lander isapproximately 4.7 tonnes, and it can carryapproximately 30 tonnes of propellant to beused for orbital maneuvers and for the finaldescent maneuver.

3.6.3.5 Mars Ascent Vehicle

When the surface mission has beencompleted, the crew must rendezvous withthe orbiting ERV. This phase of the mission is

Table 3-13 Mars Transit/Surface Habitat Element

SubsystemSubsystem

Mass(tonnes)

ConsumablesSubtotal(tonnes)

Dry MassSubtotal(tonnes)

Physical/chemical life supportPlant growthCrew accommodationsHealth careStructuresEVAElectrical power distributionCommunications and information managementThermal controlPower generationAttitude controlSpares/growth/marginRadiation shieldingScienceCrew

6.000.00

22.502.50

10.004.000.501.50

2.000.000.003.500.000.900.50

3.000.00

17.500.500.003.000.000.00

0.000.000.000.000.000.000.50

3.000.005.002.00

10.001.000.501.50

2.000.000.003.500.000.900.00

Total estimate 53.90 24.50 29.40

3-83

Fig

ure

3-2

6 H

ab

itat a

nd s

urfa

ce

lab

ora

tory

join

ed

on

Ma

rs s

urfa

ce

.

3-84

Fig

ure

3-2

7 M

ars

sur

fac

e la

nde

r de

sce

ndin

g o

n p

ara

chu

tes.

3-85

Figure 3-28 Mars surface lander just prior to landing illustrating landing legs andsurface mobility system.

3-86

accomplished by the MAV which consists ofan ascent propulsion system and the crewascent capsule.

The MAV is delivered to the Mars surfaceatop a cargo descent stage (Figure 3-29illustrates the MAV inside the biconicaeroshell and deployed on the surface). Theascent propulsion system is delivered with itspropellant tanks empty. However, the samedescent stage also delivers a nuclear powersource, a propellant manufacturing plant(both discussed in later sections), and severaltanks of hydrogen to be used as feedstock formaking the required ascent propellant. Thisapproach was chosen because the mass of thepower source, manufacturing plant, and seedhydrogen is less than the mass of thepropellant required by the ascent stage toreach orbit (Stancati, et al., 1979; Jacobs, et al.,1991; Zubrin, et al., 1991). Not carrying thispropellant from Earth gave the ReferenceMission the flexibility to send more surfaceequipment to Mars or to use smaller launchvehicles or some combination of the twooptions.

The crew rides into orbit in the crewascent capsule (Figure 3-30). This pressurizedvehicle can accommodate the crew of six,their EVA suits, and the samples gatheredduring the expedition and from experimentsconducted in the surface habitat/laboratory.Life support systems are designed for therelatively short flight to the waiting ERV. Thisascent capsule does not have a heat shield, asit is not intended for reentering theatmosphere of Earth or Mars. Once the

rendezvous has been completed and all crew,equipment, and samples have beentransferred to the ERV, the MAV is jettisonedand remains in orbit around Mars.

The MAV is depicted in Figure 3-31showing basic dimensions for the vehicle. Theascent propulsion system will requireapproximately 26 tonnes of propellant toaccomplish the nearly 5,600 meters persecond of velocity change required for asingle-stage ascent to orbit and rendezvouswith the previously deployed ERV. Thestructure and tankage needed for thispropellant and the other attached hardwareelements have a mass of 2.6 tonnes, includingthe mass of the engines but not the crewcapsule. The ascent propulsion system usestwo RL10-class engines modified to burnLOX/CH

4. These engines perform with anaverage specific impulse of 379 secondsthroughout the MAV flight regime.

The ascent crew capsule has a maximumdiameter of 4 meters, a maximum height of2.5 meters, and a mass of 2.8 tonnes. Thiscapsule contains the basic crew life supportsystems and all guidance and navigationequipment for the rendezvous with the ERV.

3.6.3.6 Earth-Return Vehicle

Returning the crew from Mars orbit toEarth is accomplished by the ERV which iscomposed of the TEI stage, the Earth-returntransit habitat, and the ECCV. The ERV isdelivered to Mars orbit with the TEI stagefully fueled, and it loiters there for nearly 4years before being used by the crew returning

3-87

Figure 3-29 Mars surface lander and biconic aeroshell.

Figure 3-30 Crew ascent capsule just after launch from Mars surface.

3-88

Figure 3-31 Methane/LOX ascent stage configuration.

9 (m)

6 (m)

4 (m)

One center (core)3.6 (m) dia sphericalLO2 tanks

One center (core)3.3 (m) dia sphericalLOH4 tanks

3-89

to Earth. For the return to Earth, the crew willjettison the MAV and wait for the appropriatedeparture time to leave the parking orbit.During the 180-day return trip, the crew willrecondition themselves as much as possiblefor the return to an Earth gravityenvironment, train for those procedures theywill use during the entry phase, performscience experiments and maintenance tasks,and prepare reports. As they approach Earth,the crew will transfer to the ECCV, along withthe samples they are returning, and separatefrom the remainder of the ERV. The TEI stageand the transit habitat will fly by Earth andcontinue on into deep space. The crew in theECCV will deflect their trajectory slightly sothat they reenter the Earth’s atmosphere andland on the surface.

The propulsion system for the ERV issized for the velocity change needed to movethe Earth return habitat and the ECCV fromthe highly elliptical parking orbit at Mars tothe fast-transit return trajectory to Earth. Aswith the TMI stage, the energeticallydemanding 2011 return trajectory was used tosize this system for a 180-day return; lessenergetically demanding returns could beaccomplished faster or with larger returnpayloads.

Several propellant and enginecombinations were considered by the MarsStudy Team for the TEI propulsion system.The two options given the most considerationwere liquid hydrogen with a NERVAderivative engine comparable to the TMI

stage, and liquid oxygen/liquid methanewith the same engine used by the lander andthe MAV. With the 4-year loiter time in Marsorbit, propellant boiloff was the major designconsideration. Liquid hydrogen wouldrequire active refrigeration for this extendedperiod in orbit to avoid excessive boilofflosses. Liquid oxygen/liquid methane boilofflosses could be held to acceptable levels usingpassive insulation and appropriateorientation of the vehicle while in Mars orbit(to minimize radiative heat input from Mars,the largest source). The 30 kWe solar powersystem (used primarily for powering the ERVon the return to Earth) is also on board andcould be used for active cooling of thesepropellants. Based primarily on this trade-off,liquid oxygen and liquid methane werechosen as the TEI stage propellants.

With this selection, the TEI propulsionsystem uses two RL10-class engines modifiedto burn LOX/CH4. Again, these are the sameengines developed for the ascent and descentstages, thereby reducing engine developmentcosts and improving maintainability. Toachieve the velocity change for the 2011 fast-transit return requires approximately 52tonnes of liquid oxygen and liquid methane.The remainder of the TEI propulsion system,including tanks, structure, engines, andreaction control systems, has a dry mass ofapproximately 5.2 tonnes.

The return habitat is a duplicate of theoutbound transit/surface habitat used to goto Mars but without the stores of consumables

3-90

in the surface habitat. As with the surfacehabitats, the primary structure of this habitatconsists of a cylinder 7.5 meters in diameterand 4.6 meters long with two elliptical endcaps (overall length of 7.5 meters). Theinternal volume will be divided into twolevels, oriented so that each “floor” will be acylinder 7.5 meters in diameter andapproximately 3 meters in height. Theprimary and secondary structure, windows,hatches, docking mechanisms, powerdistribution systems, life support,environmental control, safety features,stowage, waste management,communications, airlock function and crewegress routes will be identical to the otherhabitation elements. Table 3-14 details themass estimate for this habitat module.

The ECCV is similar in concept to theApollo Command Module and is eventuallyused by the crew to enter the Earth’satmosphere and deliver the crew to a safelanding on land. The ECCV will have thenecessary heat shield for Earth reentry andwill be heavier than the ascent capsulespecialized only for that portion of themission. This vehicle has all of the lifesupport, guidance and navigation, andpropulsion systems to keep the crew alive forseveral days and to maneuver the vehicle intothe proper entry trajectory. Once the reentryphase has been completed, the ECCV will usea steerable parafoil to land at a designatedlocation on the surface (Figure 3-32). TheECCV has an estimated mass of 5.5 tonnes.

3.6.3.7 Interplanetary Transportation PowerSystems

A source of power will be required for allof the interplanetary transportation systemsduring the flight times to and, in the case ofthe ERV, from Mars. While several alternativesare available as a primary source of power forthese vehicles, solar energy is readilyavailable throughout these transit phases andphotovoltaic energy is a known technology.Thus, a basic photovoltaic power capability isassumed for those vehicles that are operatingin interplanetary space. A source of storedpower will also be needed for theinterplanetary vehicles during periods ofeclipse and of array retraction prior to captureinto Mars orbit, and for vehicles not typicallyoperating in interplanetary space (such as theMars surface lander, the MAV, and the ECCV).During the eclipse periods and for the othervehicles, a regenerative fuel cell (RFC) systemwill be used to provide necessary power.

The most significant power requirementsfor the interplanetary transportation systemcome from the transit/surface habitat and theERV. Table 3-15 shows the estimated powerrequirements to support the six-person crewfor both nominal and powerdown emergencymode. The life support system is a majorconstituent of the almost 30 kWe needed forthese two vehicles under nominal conditions.The life support system is based on a partiallyclosed air and water system design that per-forms CO2 reduction, O2 and N2 generation,urine processing, and water processing(potable and hygiene). The emergency mode

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Figure 3-32 ECCV returning to Earth on a steerable parafoil.

3-92

value is based on the life support systemoperating in an open loop mode withreductions in noncritical operations.

The solar array as it would appear on theERV (Figure 3-33) is designed to produce therequired 30 kWe in Mars orbit at the worst-case distance from the Sun, 1.67 AU. Theenergy storage system is sized to providepower before and after Mars orbit capture aswell as during attitude control, arrayretraction, orbit capture, array extensionmaneuvers, and orbit eclipse. A nominalpower profile for these activities is shown inFigure 3-34. It is currently assumed that the

outbound transit/surface habitat can besafely powered down to 20 kWe during thesemission phases to save RFC mass andvolume, and that the RFC and solar array willremain with the transit/surface habitat to beused on the surface as a backup system.

Based on the size of the energy storagesystem, eclipse power requirement, andavailable power from the array, it will takeseven orbits of Mars to fully charge the RFC.The RFC delivers power when the solar arrayis retracted during entry, descent, and landingof the transit/surface habitat. The RFC canalso deliver 20 kWe for 24 hours after landing,

Table 3-14 Earth-Return Habitat Element Mass Breakdown

SubsystemSubsystem

Mass(tonnes)

ConsumablesSubtotal(tonnes)

Dry MassSubtotal(tonnes)

Physical/chemical life supportPlant growthCrew accommodationsHealth careStructuresEVAElectrical power distributionCommunications and information managementThermal controlPower generationAttitude controlSpares/growth/marginRadiation shieldingScienceCrew

6.000.00

22.502.50

10.004.000.501.50

2.000.000.003.500.000.900.50

3.000.00

17.500.500.003.000.000.00

0.000.000.000.000.000.000.50

3.000.005.002.00

10.001.000.501.50

2.000.000.003.500.000.900.00

Total estimate 53.90 24.50 29.40

3-93

and it will be the prime power source for thetransit/surface habitat and crew until thehabitat is moved to its final location andconnected to the main power grid. The RFCcould also provide power for moving thehabitat from the landing site to its finalemplacement location, assuming no solararray deployment.

A duplicate of the solar array and RFCsystem will be used on the ERV, savingdevelopment costs for a unique system. Allother spacecraft discussed will use a subset ofthe RFC system (assumed to be modular or atleast manufactured in smaller units) used inthe transit/surface habitat. The base powerload for vehicle avionics, communications,and the propulsion system (noted as “S/C

Utility Power” in Table 3-15) is estimated at 5kWe. This value is assumed as the powerrequirement for the unmanned cargo-onlyvehicles during the outbound transit.

Tables 3-16 and 3-17 show the massestimates for the two power systemsdiscussed: the 30 kWe system used for thehabitats and the 5 kWe system used for thecargo flights. Both tables show the resultingsystem characteristics if the RFCs must berecharged over the course of one orbit versusrecharging them over seven orbits. Thesavings in mass, volume, and array area areobvious and support the choice to stay inorbit for a longer period of time.

Table 3-15 Estimated Power Profile for Outbound and Return Transits

Element Mode Notes

Nominal Emergency

Life Support System (LSS) 12.00 8.00 Open Loop in EmergencyThermal Contract System (TCS) 2.20 2.20 ModeGalley 1.00 0.50 Emergency valuesLogistic Module 1.80 1.80 Derated from nominal whereAirlock 0.60 0.10 appropriateCommunications 0.50 0.50Personal Quarters 0.40 0.00Command Center 0.50 0.50 Values adapted from NAS8-Health Maintenance Facility (HMF) 1.70 0.00 37126, “Manned Mars SystemData Management System 1.90 0.80 StudyAudio/Video 0.40 0.10Lab 0.70 0.00Hygiene 0.70 0.00SC/Utility Power 5.00 5.00Total 29.40 19.50

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3.6.4 Surface Systems

The surface systems assembled tosupport the long-duration science andexploration activities of the Reference Missionconsist of six major systems: a surfacelaboratory and habitat module, abioregenerative life support system, ISRUequipment, surface mobility systems (rovers),extravehicular mobility systems (EVA suits orspace suits), and power systems. All of thesesystems, with the possible exception of theEVA suits, are sent to Mars, landed on thesurface, deployed, and determined to befunctioning before departure of the flightcrew. This requires that each system bedeveloped with a high degree of built-in

autonomy and require support from the flightcrew or Earth-based supervisors only inextreme situations where built-in capabilitiescannot cope.

3.6.4.1 Surface Habitat/Laboratory

The primary function of the Mars surfacehabitat/laboratory is to support the scientificand research activities of the surface crews.The same structural cylinder (7.5 meters indiameter, bi-level, and vertically oriented)used for the other habitat elements was usedhere, but it is more specialized for theresearch activities. It will operate only in 3/8gravity.

Figure 3-34 Nominal power profile for the transit/surface habitat.

NOTES:Time axis was not drawn to scaleMO = Mars Orbit, period is 1 sol (Martian day = 25 hrs)AD = Array Deployment (4 hr)AR = Array Retraction (4 hr)

Descent (2hr)

Time

Po

wer

Lev

el (

kWe)

20

30

0 8 hr

180 days

Solar arrays

Batteries or RFC

Solar arrays and batteries

Transit from Earth Orbit to Mars Orbit

10 hr

1st Sol 2nd Sol

Max. orbit eclipse, 4.2 hr

AD

7th Sol

10.6 hr

AR

10.6 hr

6th Sol

MO

10

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Table 3-16 30 kWe Power System With Fuel Cells and Solar Arrays

PowerSystem Type

1-OrbitRecharge

7-OrbitRecharge

Mass(kg)

Volume(m3)

Array Area(m2)

Mass(kg) Volume (m3) Array Area

(m2)

Fuel CellRadiatorArray

1481259

2971

0.1943.260N/A

N/A47

918

1102190

1682

3.831.5

N/A

N/A35

520

Total 4711 3.454 965 2974 5.38 555

Table 3-17 5 kWe Power System With Fuel Cells and Solar Arrays

PowerSystem Type

1-OrbitRecharge

7-OrbitRecharge

Mass(kg)

Volume(m3)

Array Area(m2)

Mass(kg) Volume (m3) Array Area

(m2)

Fuel CellRadiatorArray

39876

795

9.4980.971

N/A

N/A14

246

34749

431

0.4560.653

N/A

N/A9

138

Total 1269 1.469 260 827 1.109 147

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This surface habitat/laboratory will beone of the first elements landed on the surfaceof Mars. Once moved to a suitable location(should the actual landing site proveunsuitable or to accommodate otheroperational needs), this facility will beconnected to the surface power systems andall internal subsystems will be activated. Onlyafter these internal subsystems and otherlanded surface systems have been verified tobe operating satisfactorily will the first crewbe launched from Earth.

The surface habitat/laboratory contains alarge stowage area on the first level and thesecond level is devoted entirely to theprimary science and research laboratory. Thestowage area will initially containnonperishable consumables that can be sentto the surface prior to the arrival of the firstcrew. As these consumables are used, thisspace will become available for other uses—likely to be plant growth and greenhouse-type experiments. The other subsystems ofthis module, such as the primary andsecondary structure, windows, hatches,docking mechanisms, power distributionsystems, life support, environmental control,safety features, stowage, waste management,communications, airlock function, and crewegress routes, will be identical to the otherhabitats with a few exceptions. No crewquarters or accommodations will be includedin this module except for a minimal galleyand minimal waste management facility.However, the life support subsystem will becapable of supporting the entire crew shouldit become necessary for the crew to spend

extended periods of time in the habitat/laboratory. The primary airlock for EVAactivities will be located in this module (withbackup capability in one of the other habitatmodules) with an EVA suit maintenance andcharging station located near the airlock.Table 3-18 details the estimated mass for thismodule.

3.6.4.2 Life Support System

An important reason for sending humansto live on and explore Mars is to determinewhether human life is capable of survivingand working productively there. The lifesupport system (LSS) for a Mars surfacemission will be an integral part of the missionarchitecture, and must be viewed in terms ofits requirements to maintain the health andsafety of the crew and its capability tominimize the dependence of a Mars outposton materials supplied from Earth. Provingthat human, and by extension animal andplant, life can inhabit another world andbecome self-sufficient and productive will bea major objective of this LSS.

Four options were examined for use asthe LSS for the Mars surface facilities: openloop, physical/chemical, bioregenerative, andcached stocks of consumable materials.

•The open loop option is the simplest toimplement but typically the most expensivein terms of the mass required. For this option,life support materials are constantlyreplenished from stored supplies as they areused (for example, as air is breathed by thecrew, it is dumped overboard and replaced

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with “new” air). While not seriouslyconsidered, this option was carried forcomparison purposes.

•The physical/chemical option is typicalof the systems used in current spacecraftand relies on a combination of physicalprocesses and chemical reactions toscrub impurities from the air and water.

•The bioregenerative option uses higherplant life species to provide food,revitalize air, and purify water. This typeof approach is technically embodied inthe concept of a Controlled Ecological

Life Support System, although it is oftendescribed colloquially as a “greenhousesystem.”

•The cached stocks option makes use ofthe ISRU equipment already in place formanufacturing propellants to also makeusable air and water for the crew. Traceamounts of the constituents of usable airand water will be by-products (in factimpurities that must be removed) of thepropellant manufacturing process.Capturing and storing these impuritiesas well as oversizing some of the

Table 3-18 Mars Surface Habitat/Laboratory Mass Breakdown

SubsystemSubsystem

Mass(tonnes)

ConsumablesSubtotal(tonnes)

Dry MassSubtotal(tonnes)

Physical/chemical life supportPlant growthCrew accommodationsHealth careStructuresEVAElectrical power distributionCommunications and information managementThermal controlPower generationAttitude controlSpares/growth/marginRadiation shieldingScienceCrew

4.003.007.500.00

10.001.500.501.50

2.000.000.005.500.003.000.00

2.001.007.500.000.001.000.000.00

0.000.000.000.000.00

Uncertain0.00

2.002.000.000.00

10.000.500.501.50

2.000.000.005.000.003.000.00

Total estimate 38.50 11.50 27.00

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production processes can allow the crewto at least augment other elements of theLSS.

Combinations and hybrids of theseoptions are also possible and were alsoexamined for this report. Using a combinationof systems or a hybrid system would providemore levels of functional redundancy andthus provide an attractive option forenhancing the viability of the Mars surfacefacilities as a safe haven. Figure 3-35illustrates a hybrid system using physical/chemical and bioregenerative elements.

In this example, certain life supportfunctions, such as CO2 reduction and waterpurification, can be shared by both elements,while other functions, such as fresh foodproduction, can only come from thegreenhouse. As an integrated system, neitherelement needs to provide 100 percent of thefull life support demand on a continuousbasis. Both elements however, should becapable of being periodically throttled tosatisfy from 0 percent to 100 percent of theLSS load.

The Reference Mission adopted thephilosophy that life-critical systems (thosesystems absolutely essential to ensure thecrew’s survival) should have two backuplevels of functional redundancy. That is, if thefirst two levels fail, the crew will not be injeopardy, but will not be able to complete allmission objectives. As previously discussed,each habitat is equipped with a physical/chemical LSS capable of providing for theentire crew for the duration of their surface

stay. A physical/chemical system was chosendue to the mature nature of the technology.Thus, the first habitat and the surfacelaboratory constitute the primary and firstbackup (although not strictly a functional butrather a redundant backup) for the crew lifesupport.

It is highly desirable for the secondbackup to use indigenous resources so thatthe backup life support objective and the liveoff the land objective are both met. Table 3-19compares the various options for thecombined LSSs with an open system. Each ofthese options was sized for a crew of sixspending 600 days on the martian surface.

Because of the life-critical nature of thepropellant manufacturing facility and thehigh level of reliability that must be designedinto this system, the cached stocks option waschosen as the second backup. However,demonstrating the capability to producefoodstuffs and revitalize air and water usingbioregenerative processes is considered amission-critical objective for the ReferenceMission. For that reason, an experimentalbioregenerative life support system capable ofproducing a small amount of food is includedas a science payload to be delivered for use bythe second crew.

Several options exist for the location ofthe experimental bioregenerative LSS. One isto use the storage space in the surfacehabitat/laboratory that will become availableas consumables are used. This is the simplestto implement but would require artificiallighting and would be restricted to the

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Figure 3-35 Hybrid LSS process distribution.

SUPPLYHIGHWAY

LSS

WASTEPRODUCTHIGHWAY

DISPOSALPATH

RECYCLEPATH

PHYS. / CHEM. BIO-REGEN.

MASS CO2 H2O CO2

H2O O2O2

ELECT.POWERHIGHWAY

EFFL.BUS

INFL.BUS

H2O FOOD

H2O

H2O

O2

CO2

Table 3-19 LSS Mass, Volume, Power Comparison.

ArchitectureFunctionalRedundant

Levels

Mass(mt)

Volume(m^3)

Maximum ∆Power Over

Open Loop (kW)

Open Loop 1 180 290 0

Physical/Chemical with CachedStocks 2 60 470 7

Bioregenerative with CachedStocks 2 60 410 60

Hybrid Physical/Chemical andBioregenerative with CachedStocks

3 80 600 60

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volume available in the storage area. Twoother options involve attaching an externalpressurized structure to one of the habitatmodules. One external option would use ahard opaque structure for the external shelland would also require artificial lighting. Theother external option would use an inflatabletransparent structure for the external shell.Natural sunlight would be used to illuminatethe plants which would reduce the powerneeded by the system; however, the potentialrisk of a puncture due to natural or human-derived events would be increased.

In either external scheme, the greenhouseatmospheric volumes would normallycommunicate directly with the atmosphericvolume of the habitat without furtherprocessing, but could be sealed off incontingencies. The greenhouse(s) could beerected or inflated at the convenience of thecrew. The loss of a greenhouse module forany reason, such as puncture, mechanical orelectrical failure, or loss of shielding integrity,would not seriously impact overall missionsuccess.

3.6.4.3 In Situ Resource Utilization

ISRU for the Reference Mission providestwo basic resources: propellants for the MAVand cached reserves for the LSSs. Usingindigenous resources to satisfy these needsinstead of transporting resources from Earthreduces launch mass and thus mission cost.ISRU production for the Reference Missionincludes two virtually redundant ISRU plants,the first delivered before the initial pilotedmission and the second delivered prior to the

first follow-up mission. Each ISRU plant willproduce propellants for at least two MAVmissions. However, only the first plant isrequired to produce life support caches.

For each MAV mission, a plant isrequired to produce 20 tonnes of oxygen andmethane propellants at a 3.5 to 1 ratio: Eachplant must produce 5.8 tonnes of methaneand 20.2 tonnes of oxygen. Further, the firstISRU system is required to produce 23.2tonnes of water, 4.5 tonnes of breathingoxygen, and 3.9 tonnes of nitrogen/argoninert buffer gasses for use by any of the threeMars crews. The system liquefies and storesall of these materials as redundant lifesupport reserves or for later use by the MAV.

The approach to ISRU production usesthe martian atmosphere for feedstock andimports hydrogen from Earth. The mainprocesses used are common to both ISRUplants. The significant difference between thetwo is that the second plant is smaller andexcludes equipment for buffer gas extraction.Should sources of indigenous and readilyavailable water be found, this system could besimplified.

3.6.4.3.1 Processes

The Mars atmosphere, which is used as afeedstock resource, is composed primarily ofcarbon dioxide with just over 3 percentnitrogen and argon. The ISRU plants must becapable of converting the carbon dioxide tomethane, oxygen, and water. Since hydrogenis not substantially present in the atmospherein gaseous form and indigenous sources of

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water are uncertain, hydrogen must beimported from Earth. The first plant must alsobe capable of extracting the nitrogen andargon for buffer gas reserves. The referenceISRU system uses Sabatier, water electrolysis,carbon dioxide electrolysis, and buffer gasabsorption processes to achieve these ends.

•Methane production - The Sabatierreaction was discovered by Frenchchemist P. Sabatier in the nineteenthcentury and is one of the most oftencited for ISRU on Mars (Sullivan, et al.,1995). The reaction converts carbon tomethane and water by reacting it withimported hydrogen at elevatedtemperatures. This process is alsocommonly used in closed physical/chemical LSSs for reduction of metaboliccarbon dioxide. It results in a water tomethane mass ratio of 2.25:1 andrequires 0.5 tonnes of hydrogen for eachtonne of methane produced. Theresultant methane is stored cryogenicallyas fuel. The water can either be useddirectly as cached life support reservesor can be broken down into oxygen andhydrogen to be recycled.

•Oxygen production - Oxygen productionis accomplished with two differentprocesses. The Reference Mission usesboth water electrolysis to produceoxygen from water produced in theplant and carbon dioxide electrolysis todirectly convert the Mars atmosphere tooxygen.

Water electrolysis is well known and hasbeen used for numerous terrestrialapplications for many years. The combinedSabatier and electrolysis processes generateoxygen and methane for use as propellants ata mass ratio of 2:1. In this combined processcase, the hydrogen is recycled into theSabatier process so that 0.25 tonnes ofhydrogen are needed for each tonne ofmethane. The engines selected for theReference Mission use oxygen and methane ata mass ratio of 3.5 to 1. Therefore, anadditional source of oxygen is needed toavoid overproduction of methane.

The carbon dioxide electrolysis process isused in the Reference Mission to provide theneeded additional oxygen. The processconverts the atmospheric carbon dioxidedirectly into oxygen and carbon monoxideusing zirconia cells at high temperature. Thezirconia cell system is not as well developedas the Sabatier process but is underdevelopment (Sridhar, et al., 1991; Ramohalli,et al., 1989; and Colvin, et al., 1991). Thisprocess eliminates the overproduction ofmethane during propellant production exceptduring the first mission when the Sabatier-produced water is also needed.

The two strong alternatives to carbondioxide electrolysis—methane pyrolysis andreverse water gas shift—were not studied in-depth for the Reference Mission report, butthey should be considered seriously in furtherstudies of manned Mars missions.

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•Buffer gas extraction - The buffer gasextraction process has not beenexamined in detail during this study. Itwill most likely be a nitrogen and argonabsorption process in which compressedatmosphere is passed over a bed ofmaterial which absorbs the nitrogen andargon. The gases are then released byheating the bed and the products arepassed on to the cooling and storagesystem. Parallel chambers are used sothat one bed is absorbing in the presenceof atmosphere while the other isreleasing its captured gases.

•Ancillary Systems - Systems foratmosphere intake, product liquefaction,and product storage and transfer will beneeded. These systems have not beendetailed for the Reference Mission at thisstage of study but their necessaryfunctions can be described. The filterand compressor equipment cleans themartian atmosphere of dust andcompresses it to a pressure usable by therest of the ISRU plant. Productliquefaction must include cryogenicliquefaction of oxygen, methane andnitrogen as well as condensation of thewater stored as cached reserves. Storagesystems will include cryogenic tanks forcached oxygen and buffer gasses. Anexpandable bladder-type tank isanticipated for cached water. Propellantstorage will be accomplished in the MAVtanks and so is not considered part of theISRU system.

3.6.4.3.2 Initial ISRU Plant

The first ISRU plant is delivered to Marsover a year prior to the first departure ofhumans from Earth, and during that year theplant produces all the propellants and lifesupport caches that will be needed. Thus,humans do not even leave Earth untilreserves and return propellants are available.This plant also produces propellants for theMAV mission of the third crew in the overallReference Mission scenario.

A schematic of this initial plant is shownin Figure 3-36. The plant integrates all theprocesses needed for both propellant and lifesupport products. The water electrolyzer isnot used in the plant during the first period ofoperation. Because of the total mass of thewater cache, all of the water produced by theSabatier reactor is stored and the carbondioxide electrolysis reactor is responsible forproducing all the oxygen needed. In addition,over 10 tonnes of excess methane areproduced as a by-product of the waterproduction process for the LSS cache.

When the plant is operated for the thirdMAV launch propellants, the waterelectrolyzer is brought on-line. Instead ofbeing condensed, the water from the Sabatierreactor is split by the electrolyzer intohydrogen (which is recycled to the Sabatierreactor) and oxygen (which is liquefied andsent to the MAV tanks). For this operation ofthe plant, no methane overproduction isneeded.

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The size of the ISRU plant has only beenestimated parametrically. These estimates arebased on some previous work on the optionsfor ISRU and on the rates needed to producerequisite materials over a 15-month period.The mass and power requirements for thisplant are given in Table 3-20. The powerrequirements represent those of the plant’sinitial period of operation.

3.6.4.3.3 Second ISRU Plant

The second ISRU plant is delivered atessentially the same time as the arrival of thefirst crew on Mars. This allows time forpropellant production prior to the Earthdeparture of the second crew. The secondplant is only charged with production ofpropellants since, the life support reserves arepresumably still present.

H2O (trace)

H20

Filter/Compressor

Buffer Gas Extraction

Sabatier

Buffer gasstorage cache

O2O2

CH4

Water StorageCache

CO2 Electrolysis

WaterCondenser

CO2

CH4

O2

BreathingO2 Storage

Cache

H2

MarsAtmosphere

N2/Ar

H2

NC

NC

NC

Water Electrolysis

O2(trace)

Buffer GasCryo Cooler

CH4Vent

CH4

COVent

MAVFirst

Stage

MAVSecondStage

Cryo Cooler

Figure 3-36 Schematic of the first ISRU plant.

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The plant schematic is essentially thesame as that shown in Figure 3-36. Thesecond plant does not include the buffer gasextraction, liquefaction, and storageequipment or the water condensation andstorage equipment. Further, the size of thereactors is reduced because of the lowerproduction rates needed. Table 3-21 shows theestimated mass and power requirements forthis plant. Plant operations are the same asthose of the first plant during its secondperiod: All Sabatier-produced water iselectrolyzed, and the extra oxygen needed isproduced by the carbon dioxide electrolyzer.

3.6.4.4 Surface Mobility

Mobility on a local scale and regionalscale will be required during all phases of thesurface exploration of the Reference Mission.The basic objectives for the Reference Missionrequire that a variety of mobility systems be

provided for basic maintenance andoperations activities as well as for explorationof the surface. Prior to the first crew’s arrivaland during all subsequent periods whether acrew is present or not, exploration at shortand long ranges will be performed byautomated rovers. Surface facility setupactivities will require rovers acting under thesupervision of Earth-based operators.Maintenance and operations by the surfacecrews can be more productive with theavailability of mobile utility systems. Andfinally, long-range, long-duration explorationby the surface crews will be possible onlywith the use of pressurized, autonomousrovers.

The Reference Mission identifies threeclasses of mobility systems, based on the timeand distance to be spent away from thesurface habitats.

Table 3-20 Mass and Power Estimates for the First ISRU Plant

Plant Component Production Rate(per day)

Component Mass(kg)

Component Power(kWe)

Compressor 269.7 kg 716 4.09

CO2 Electrolysis 53.2 kg 2128 63.31

Sabatier 22.9 kg 504 1.15

H2O Electrolysis 27.8 kg 778 0.00

Buffer Gas Extraction 8.7 kg 23 0.13

Cryogenic Coolers 84.8 kg 653 3.59

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•Immediate vicinity of the surface basefacilities: hundreds of meters and the 6-to 8-hour limit of the EVA portable LSS

•Local vicinity of the surface base facility:several kilometers and the 6- to 8-hourlimit of the EVA portable LSS

•Regional distances: a radius of up to 500km in exploration sorties that allow 10workdays to be spent at a particularremote site, and with a transit speedsuch that less than half of the excursiontime is used for travel (for example, for10 workdays, no more than 5 days toreach the site and 5 days to return).

These divisions resulted in three basicrover types and a number of other mobilitysystems to support the kinds of activities atthese ranges and for these amounts of time.

On the local scale, any time the crew isoutside of the habitat(s) they will be in EVAsuits and will be able to operate at somedistance from the habitat. The maximum

distance will be determined by theircapability to walk back to the outpost withinthe time set by the recharge limits of theportable LSS. During these activities, the EVAcrew will have a variety of tools, includingrovers, carts, and wagons, available for use.

For distances perhaps beyond a kilometerfrom the habitats but less than 10 kilometersdistant, exploration will be assisted byunpressurized self-propelled rovers. Thisrover is functionally the same as the LunarRover Vehicle used in the Apollo Programand is meant to assist the EVA crews bytransporting them and their equipment overrelatively short distances. Figure 3-37illustrates one concept for this rover (partiallyhidden behind one of the teleoperated long-range rovers) with a gabled radiator abovethe aft end. This rover is driven by six cone-shaped wheels and has an estimated mass of4.4 tonnes. Three of these vehicles will be partof the cargo carried to the surface for use inand around the surface facilities.

Plant Component Production Rate(per day)

Component Mass(kg)

Component Power(kWe)

Compressor 87.8 kg atm 233 1.33

CO2 Electrolysis 18.5 kg O2 740 22.00

Sabatier 12.4 kg CH4

272 0.62

H2O Electrolysis 27.8 kg H2O 778 5.79

Cryogenic Coolers 30.8 kg 238 2.3

Table 3-21 Mass and Power Estimates for the Second ISRU Plant

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On the regional scale, beyond the saferange for exploration on foot or inunpressurized rovers, crews will explore inpressurized rovers, allowing them to operatefor the most part in a shirtsleeveenvironment. Figure 3-38 illustrates onepossible concept for this rover. The rover isassumed to have a nominal crew of twopeople, but can carry four in an emergency.Normally, the rover would be maneuveredand EVAs would be conducted only duringdaylight hours, but sufficient power will beavailable to conduct selected investigations atnight. Crew accommodations inside the roverwill be relatively simple: a drive station, awork station, hygiene facilities, a galley, andsleep facilities. An airlock on this rover will becapable of allowing not only surface accessfor an EVA crew, but also direct connection tothe habitat, thus precluding the need for anEVA to transfer either to or from the rover.Each day on an excursion away from themain surface facilities, the rover has thecapability of supporting up to 16 person-hours of EVAs. Facilities for recharging theportable LSSs and for making minor repairsto the EVA suits are also included. The workstation will be used, in part, to operate twomechanical arms that can be used tomanipulate objects outside the rover withoutleaving the pressurized environment. Thesearms, along with other mobility subsystems,can also be operated remotely by Earth-basedpersonnel. This feature is required to allowmany of the deployment, setup, andmonitoring activities to be carried out prior tothe arrival of the first crew. A final feature of

this rover is the power system. The choice ofthe specific power system is discussed in alater section. However, this system will bemounted on a separate trailer to be towed bythe rover whenever it is in operation. At timeswhen the rover is dormant, the power trailercan be used for other purposes, including itsuse as a backup power source for any of thesurface facilities. Two pressurized rovers willbe carried to the surface. This allows forredundancy in this function, including thepossibility of rescuing the crew from adisabled rover located at a distance from thehabitats. Each rover is driven by four cone-shaped wheels and is estimated to have amass of 16.5 tonnes.

Exploration at a regional scale will alsobe undertaken by small teleoperated rovers.The foreground of Figure 3-38 illustrates onepossible concept for this rover. The mainpurpose for these rovers is to explore themartian surface at long distances, hundreds tothousands of kilometers, from the habitats.The activities carried out by this type of roverwill be to conduct scientific investigations,collect and return samples to the habitats, andscout possible locations for human crews toinvestigate in more detail. Three of theserovers will be delivered as part of the firstcargo mission and will be supervised fromEarth during the time between landing andthe arrival of the first crew. Determining sitesfor the crews to investigate and safe routes tothe sites will be the primary activity beforethe first crew arrives and during thoseperiods when no crew is at the surface base.When a crew is on the martian surface, these

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Figure 3-37 Concepts for the unpressurized and automated surface rovers.

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Figure 3-38 Concept for the large pressurized surface rover.

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rovers will be available for teleoperation bythe crews. Focused exploration, samplecollection, and scientific measurements willbe the main tasks for these rovers while underthe control of the surface crew, who will beable to operate these rovers from theshirtsleeve environment of the surfacehabitat/laboratory. Each rover is estimated tohave a mass of 440 kilograms.

This range of mobility systems will allowexploration activities to be carried outcontinuously once the first cargo mission hasdelivered its payload to the martian surface.The variety of range requirements and surfaceactivities leads to a suite of mobility systemsthat have overlapping capabilities.

3.6.4.5 EVA Systems

The ability for individual crew membersto move around and conduct useful tasksoutside the pressurized habitats will be anecessary capability for the ReferenceMission. EVA tasks will consist ofconstructing and maintaining the surfacefacilities, and conducting a scientificexploration program encompassing geologicfield work, sample collection, anddeployment, operation, and maintenance ofinstruments. EVA systems provide a primaryoperational element and a critical componentof the crew safety system and must beintegrated into the design of a habitationsystem during the very early stages. Twosystems will make EVA possible for the crews:an EVA suit designed for use in the martianenvironment and an airlock system that will

allow the crew to safely exit and enter thepressurized habitats.

The EVA system will have the criticalfunctional elements of a pressure shell,atmospheric and thermal control,communications, monitoring and display, andnourishment and hygiene. Balancing thedesire for high mobility and dexterity againstaccumulated risk to the explorer will be amajor design requirement on a Mars EVAsystem. Lightweight and ease of maintenancewill also contribute to the design. Specificconcepts for an EVA suit that will satisfy theserequirements were not investigated in thisstudy. Further effort will be required totranslate these general needs into specificrequirements and an actual implementation.

The airlock system, although integralwith the habitation system, was developed asan independent element capable of being“plugged” or relocated as the missionrequires. Because EVA will be a substantialelement of any planetary surface mission, thedesign and location of the associated airlockfacilities will have a major impact on theinternal architecture of each pressurizedelement.

A conceptual airlock configuration wasprepared (Figure 3-39). In the foreground ofthis conceptual design is an airlock sized fortwo suited crew members. In the rear of theillustration is a facility for EVA suitmaintenance and consumables servicing.Each habitat will have an airlock locatedwithin it. The maintenance and consumables

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servicing facility will be located in the surfacehabitat/laboratory.

3.6.4.6 Surface Power Systems

A source of power will be required for anumber of diverse systems operating on thesurface of Mars. A large fixed power source isrequired to support the propellantmanufacturing facility and the surfacehabitats. A mobile source of power is requiredto support the three categories of rovers thatwill move crew and scientific instrumentsacross the martian surface. Various powersystem options were reviewed for theirappropriateness to meet missionrequirements and guidelines for these surfacesystems. Contending power systemtechnologies include solar, nuclear, isotopic,electrochemical, and chemical for both thefixed and mobile power source.

While all surface element power systemrequirements were assessed for application

synergies that would suggest commonhardware (duplicates of the same or similardesign) or multiuse (reuse system in adifferent application or location) whereverprudent, the specific requirements for thefixed and mobile power sources wereexamined individually.

3.6.4.6.1 Fixed Surface Power Systems

To best determine the type and design ofthe fixed power system, an estimated powerprofile was developed and is shown in Figure3-40.

The power system must be one of thefirst elements deployed because it providespower to produce the life support cache andascent vehicle propellants prior to the launchof the first crew. Approximately 370 days willbe available to produce the required lifesupport cache and ascent propellant.However, this will be reduced by the time todeploy the power system. With an estimatedpower system deployment time of 30 to 60days, about 320 days remain for producingthese products. An initial 60 kWe power levelwas determined by this required deploymenttime and the energy required to produce thelife support cache and ascent vehiclepropellants during the time remaining. As theoutpost reaches full maturity, power levelsapproach 160 kWe due to increased habitationvolumes and life support capability.

Significant design requirements are alsoplaced on all the surface equipment deliveredon the initial cargo flights. Each system mustbe deployed to its respective locations and

Figure 3-39 Conceptual airlock andEVA suit maintenance facility.

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Figure 3-40 Mars surface power profile.

function autonomously for almost 2 years.Crew safety and well-being demandsreliability and robustness in all surfaceelements. (Part of this risk is mitigated bybackup and redundant systems or systemsthat can perform multiple functions.) Theserequirements all impact the design andselection of the power system for the centralbase.

To meet the evolutionary powerrequirements of the base, two types of powersystems were evaluated: nuclear and solar.Table 3-22 shows estimated mass, volume,and area for each of these options.

The power management, transmission,and distribution system masses (at 95 percentefficiency) have been included in each of thesystem sizing estimates. Transmission cablemasses were calculated using 500 volts due tothe Paschen breakdown limit associated withMars’ atmospheric pressure. (For a widerange of conditions, exposed conductors at anelectrical potential greater than 500 voltscould experience large power drains due toatmospheric discharges.)

Due to the potential radiation hazard of anuclear power source, the nuclear powersystem is configured with a completely

175

150

125

100

75

50

25

Power

kWe

1 2 3 4 5 6 7

Years After First Cargo Landing

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enveloping shield for remote deployment andis integrated with a mobile platform. Theentire system is deployed from the landingsite (trailing distribution cables) to a site atleast 1 kilometer from the base. It is plannedto use one of the rovers for this task. Powerfrom the rover will be used to start up thepower system, deploy radiators, and obtainoperating conditions. All of these activitieswill be supervised remotely by personnel onEarth and will be performed in a manner thatwill minimize the risk to this critical piece ofequipment. The first nuclear power systemwill be capable of delivering the full baseneeds of 160 kWe. A second system isdelivered during the first opportunity and isdeployed to satisfy the fail-operational

mission requirement, but it will not be turnedon unless required.

The second option, a solar power system,requires array panels to supply the main baseload and recharge the energy storage fornighttime operations. The primary 120 kWesystem was sized to produce required powerduring winter diurnal cycles at the equator.The backup habitat power system wasdesigned to operate at worst-case global duststorm conditions, characterized by an opticaldepth (O.D.) equal to 6.0, since theseconditions could be present at the base whenan emergency power situation arose. Undernominal conditions, these two systems wereassumed to be operating in unison to providethe maximum 160 kWe required for the

Table 3-22 Characteristics for Fixed Surface Power System Options

O.D. - optical depth

Main PowerSystem (kWe)

Type Mass(MT)

Volume(m3)

Area (m2)

160

NUCLEAR-SP-100 type, low-temp, stainlesssteel, dynamic conversion, 4-Pishielding

14 42

321 radiator area

120 SOLAR - tracking,O.D. = 0.4 19.6 341 6,400 array area

45,000 field area

SOLAR - nontracking,O.D. = 0.4

33.5 686 13,000 array area39,000 field area

Backup 40 SOLAR - tracking,O.D. = 6.0 14 390 7,600 array area

53,000 field area

SOLAR - nontracking,O.D. = 6.0

26 816 16,000 array area48,000 field area

Emergency Use Pressurized Rover Power System (See Table 3-21)

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mature base. The ISRU plant was notconsidered a life-critical function so thepower system was designed to produce fullpower at an O.D. of 0.4 or a clear Mars sky.Both sun tracking and nontracking arrayswere evaluated. The solar tracking array totalland area is greater that the nontrackingbecause of the required panel spacing neededto eliminate shadows from one panel uponthe other.

O.D., or the intensity of the solarradiation reaching the surface of Mars, has asignificant impact on system size and mass.For example, if the entire 160 kWe were solargenerated, the array field would encompassabout 11 (O.D. = 0.4) to 40 (O.D. = 6.0) footballfields. In addition, the need for prompttelerobotic emplacement of the array panelsand interconnecting cables would present asignificant challenge. Dust erosion, dustaccumulation, and wind stresses on the arraypanels raise power system lifetime issues. Forthese reasons, nuclear power was deemed themost appropriate primary power source forthe fixed surface power system. However, useof the “in-space” solar array and fuel cellpower system is assumed as the habitatemergency/backup power systems, whichcould be stowed until needed. The MAVs willalso be provided with this same solar arraybackup system to ensure that themanufactured propellants are maintained intheir cryogenic state should power from thenuclear system be lost (Withraw, et al., 1993).

3.6.4.6.2 Mobile Surface Power Systems

The other major category of surfacesystems needing a power source will be therovers. The three types of rovers identified,long-range pressurized, local unpressurized,and long-range robotics, each have powerrequirements driven by their range and thesystems they must support. Several powersource options were evaluated for the rovers,including solar arrays/RFCs, combustionengines, and isotopes. Solar array systemswere not considered due to the large size ofthe array needed to support each vehicle.

The long-range pressurized rover mustbe able to support a crew of 2 to 4, with a 500-km range sortie (5 days out, 10 days at site, 5days back). The power estimate for this roveris 10 kWe continuous. It is anticipated that thepressurized, regional rover or its powersystem would be used to assist in thedeployment of the main power system,situate future habitat modules, and serve asbackup emergency power when required. Adesirable feature for the rover power systemis that it be mounted on its own cart. Thiswould add considerable versatility to its usewhen the rover is not on a sortie.

The local unpressurized rover isconceptually the same as the Apollo lunarrover. It would function to transport the crew10's of kilometers, 3 hours out and back, and 4hours at the site.

Table 3-23 shows the estimated mass,volume, and array or radiator area for thefour power system options listed.

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The Dynamic Isotope Power System(DIPS) was considered primarily for its lowmass and significantly lower radiator sizecompared to the photovoltaic array (PVA)area. The 238Pu isotope has a half life of 88years and can be the same design as the flightproven radioisotope thermoelectric generator(RTG). The isotope fuel would be reloadableinto other power units in the event of afailure, thus preserving its utility. Anotherfeature of isotope fuel is that it does not needto be recharged and is always ready as abackup, emergency power sourceindependent of solar availability oratmospheric conditions. However, the 238Puisotope availability, quantity, and cost areissues to be addressed.

The PV/RFC power option seemsimpractical for the regional rover due to thelarge array area. The arrays would have to besized to provide required power outputduring a local dust storm, the worst-case

scenario, anticipating suspended operationsduring potential global dust storm season.

Methane is a possible fuel for the roversince the propellant plant could produceadditional fuel, given that extra hydrogen isbrought from Earth. Methane could be usedin an appropriately designed fuel cell. Thereactant water would be returned and fedthrough an electrolyzer to capture thehydrogen. However, once the water has beenelectrolyzed into H2 and O2, which the fuelcell actually uses to operate, it is not prudentfrom an energy utilization standpoint to makemethane again. Storing and maintainingreactants on the rover also needs furtherstudy.

A methane-burning internal combustionengine could be used to operate either rover.However, combustion materials would needto be collected to reclaim the H2.

Table 3-23 Rover Power System Characteristics

Power SystemMass(MT)

Volume (m3)Area(m2)

Mass(MT)

Volume (m3)Area(m2)

Regional Rover Local Rover

Dynamic isotope 1.1 10 33 0.5 4 16

Photovoltaic (PV) RFC 2.8 66(RFC-4)PV-62)

1,275recharge by fueling

Primary Fuel Cell 6.5 29 13 0.160 1 6

Methane/Oxygen InternalCombustion Engine 12 36 n/a 0.160 0.4 n/a

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Given these system characteristics, theDIPS system was selected for the long-rangepressurized rover, and the primary fuel cellwas selected for the local rover. The DIPSsystem can be another level of functionalredundancy for the base systems, and thesmall amounts of radiation emitted can bemitigated by a small shield and distance tothe rover crew. The primary fuel cell wouldmeet the local rover requirements at less massthan other options. However, this powersystem design assumes refueling after everysortie. The power system for the long-rangerobotic rover was not specifically addressedin this analysis. However, the long range overrugged terrain and long duration of thisrover’s missions will likely drive the selectionto an RTG- or DIPS-type system.

3.7 Robotic Precursors

Robotic precursor missions will play asignificant role in two important facets of theReference Mission. The first will be to gatherinformation about Mars that will be used todetermine specific activities the crew willperform and where they will perform them.The second will be to land, deploy, operate,and maintain a significant portion of thesurface systems prior to the arrival of thecrew.

3.7.1 Current Robotic Program Plans

In November and December 1996, NASAlaunched two missions to Mars: the MarsGlobal Surveyor (MGS) and the MarsPathfinder lander. MGS will monitor global

weather and provide global maps of martiansurface topography and mineral distribution.The Mars Pathfinder will validate entry,descent, and landing technologies and willalso deploy a microrover on the surface toanalyze the elemental composition of martianrocks and soil.

NASA’s Mars Surveyor Program willcontinue the robotic exploration of Mars withtwo spacecraft launches planned during eachof the 1998, 2001, and 2003 opportunities. AMars sample return mission is scheduled for2005. The goals of the Mars Surveyor Programare to expand our knowledge of the geologyand resources on Mars, to understand themeteorology and climate history, and tocontinue the search for evidence of past life.

3.7.2 Mars Sample Return With ISRU

Detailed laboratory analyses of martianrock, soil, and atmosphere samples at Earthwill provide essential information neededbefore sending humans to Mars. In additionto an understanding of the martianenvironment, a sample return mission willafford the opportunity to validate thetechnology of ISRU for propellant production.As discussed in Section 3.6.4.3, ISRU is acritical technology for the Reference Mission.To ensure that this technology is available forthe human missions, it should bedemonstrated on the Mars sample return in2005.

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3.7.3 Human Exploration PrecursorNeeds

Robotic precursor missions offer thecapability to demonstrate and validate theperformance of key technologies that areessential to the Reference Mission (such asISRU, aerobraking and aerocapture at Mars)and to provide information needed for siteselection.

Critical to selection of the landing site forthe humans will be the availability ofindigenous resources, and of paramountimportance is water. Precursor missionswhich can identify the location andaccessibility of water will be invaluable in theMars exploration program. To satisfy thehuman habitation objectives in particular, itwould be highly desirable to locate anoutpost site where water can be readilyextracted from minerals or from subsurfacedeposits. Such a determination may only bepossible from data collected by a surfacemission.

With the three human missions alllanding at the same site, selection of thatlanding site is very important. The locationchosen must permit the objectives of theReference Mission to be achieved.Consequently, the site will be chosen on thebasis of proximity to a region of high scienceyield, availability of water or otherindigenous resources, and operationsconsiderations such as a hazard-free terrainfor safe landing and surface mobility. Finalsite selection may require several robotic sitereconnaissance landers to be sent to survey

various candidate sites. Detailed maps ofcandidate landing sites built from datagathered by these precursor missions willdefine the safety and operational hazards ofthe sites, as well as confirm access toscientifically interesting locations andresources.

In summary, then, the Reference Missionassumes a set of robotic precursor missionswhich includes:

•The Mars Surveyor Program

•A Mars sample return mission in 2005which also demonstrates in situpropellant production

•Other sample return missions to variousinteresting regions

•A demonstration of aerobraking/aerocapture

•Mission(s) to search for resources,particularly water

•Site reconnaissance landers to aid in theselection of the human landing site

The last two mission types may havetheir objectives incorporated into the MarsSurveyor Program or the Mars sample returnmission; or a separate set of missions may berequired.

3.7.4 Autonomous Deployment ofSurface and Orbital Elements

As described in Section 3.5.3.2, a keystrategy of the Reference Mission is to use asplit mission concept that will allow

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unmanned cargo to be sent to Mars on lowenergy, longer-transit-time trajectories. Theseunmanned elements must arrive at Mars andbe verified to be operating properly before thehuman crew is launched from Earth. Thearrival, precision landing, deployment, andoperation of these surface or orbital elementswill be performed using robotic systems. Thedetailed nature of these robotic systems wasnot examined as part of this study; however,the discussion of the surface facilities and thenature of the operations involved to set up,maintain, and, if necessary, repair thesefacilities can well be imagined. This area oftechnology development will be a very activeone to meet the needs of the ReferenceMission.

3.8 Ground Support and FacilitiesOperations

The overall goal of mission operations isto provide a framework for planning,managing, and conducting activities whichachieve mission objectives. (In general,mission objectives can be considered allactivities which maintain and support humanpresence and support scientific researchduring the mission.) Achieving thisoperational goal requires successfulaccomplishment of the following functions.

•Safe and efficient operation of allresources (includes, but is not limited to,vehicles, support facilities, trainingfacilities, scientific and systems data, andpersonnel knowledge and experiencebases).

•Provision of the facilities and anenvironment which allow users (such asscientists, payload specialists, and to anextent crew members) to conductactivities that will enhance the missionobjectives.

•Successful management and operation ofthe overall program and supportingorganizations. This requires definingroles and responsibilities andestablishing a path of authority. Programand mission goals and objectives mustbe outlined so that managementresponsibilities are clear and direct.Confusing or conflicting objectives canresult in loss of resources, the mostimportant of which are time and money.In addition, minimizing layers ofauthority will help avoid prolongedoperational decision-making activities.This is key when considering large,complex programs such as the ReferenceMission.

As with the discussion of crew operations(Section 3.4), specific hardware, software, andsystem recommendations will not be made inthis section. Guidelines for the organizationand management of operations are putforward as foundation on which an actualoperations philosophy and detailed planshould be built.

The organization of supporting facilitiesmust follow the lower costing and innovativeapproaches being taken by other areas of theReference Mission. One way of achieving this

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is to use the related expertise andfunctionality of existing facilities to keep to aminimum the layers of authority andoverhead in the program and take advantageof the existing knowledge bases at eachfacility. Proper and efficient organization ofmission operations and support facilities isrequired for any program to be successful.

The Reference Mission has the addedcomplication of being a program with phasesthat cannot be supported with near real-timeoperations. Planetary surface operations poseunique operational considerations on theorganization of ground support and facilities.Near real-time ground support, as providedfor current manned space programs, is notpossible. A move toward autonomy in vehicleoperations, failure recognition and resolution,and mission planning is needed; and groundsupport must be structured to support theseneeds. Some of the specific criteria requiredfor allocating functions between groundsupport and the Mars surface base will be theavailable resources at the remote site versuson Earth, criticality of functions for crewsafety and mission success, and desired timeand resources available for achievingscientific mission objectives.

In general, due to the uniqueness ofplanetary surface operations, Earth-basedsupport should manage and monitoroperations planning and execution, and crewmembers should be responsible for operationsplanning and execution. Crew members willbe told what tasks to do or what objectives toaccomplish, but not how to do it. This has the

benefit of involving system and payloadsexperts in the overall planning, yet givingcrews the flexibility to execute the tasks. Thisapproach differs from current Space Shuttleoperations where detailed plans are preparedby ground personnel, crew members executethe plans, and ground personnel monitor innear real-time. The crew members are fullyinvolved in execution but do little in terms ofplanning. The proposed method for theReference Mission would take advantage ofthe unique perspective of crew members in anew environment but would not restrict theiractivities because of the mission’s remotenature. Additionally, it places theresponsibility of mission success with thecrew, while the overall responsibility forprioritizing activities in support of missionobjectives resides with Earth-based support.

After dividing functional responsibilitiesbetween Earth-based support and crew, thesupport may be structured to manage theappropriate functions. To accomplish missionobjectives while maintaining the firstoperational objective of safe and efficientoperation of all resources, Earth-basedsupport can be organizationally separatedinto systems operations and scienceoperations, provided a well-defined interfaceexists between the two. The systemsoperations team would be responsible forconducting the safe and efficient operation ofall resources, while the science operationsteam would be responsible for conductingactivities which support scientific research.Such an organizational structure would

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dictate two separate operations teams withdistinct priorities and responsibilities yet thesame operational goal.

Crew and vehicle safety are always ofprimary concern. When those are ensured,science activities become the highest priority.To accommodate this hierarchy of prioritieswithin the operations management structure,the overall operations manager should residewithin systems operations. A scienceoperations manager, who heads the scienceoperations team, should organizationally bein support of the operations manager. Variouslevels of interfaces between systems engineersand science team members must exist tomaximize the amount of science and missionobjectives that can be accomplished. Forexample, a proposed science activity mayneed systems information for its planning andfeasibility studies, and such information,including providing access to the systems’experts, must be made available. There maybe a few overlapping areas of responsibilitybetween the systems and science teams. (Inthe area of crew health and safety, forexample, scientific investigators doingbiomedical research on the crews will have tointerface with the systems medical teamresponsible for maintaining crew health.)Avenues for such interaction and exchangemust be provided to ensure mission success.

3.8.1 Systems Operations

Systems operations are those tasks whichkeep elements of the program in operationalcondition and support productive utilization

of program resources. Thus, the systemsoperations team has the responsibility forconducting the safe and efficient operation ofall such resources and consists ofrepresentatives from each of the primarysystems (power, propulsion, environmental,electrical, etc.) used throughout the variousmission phases. This organizational structureis similar to current flight vehicle operationswhere representatives for each system areresponsible for verifying the system’soperational functionality. Each systemrepresentative will have an appropriatesupport team of personnel familiar with thehardware and software of that system.

Real-time operational support will beapplicable only during launch, Earth orbit (forvehicle and crew checkout), and Earth entryphases. As a result, the systems operationsteam will function in a response, tracking,and planning mode throughout most of theother mission phases. Thus, Earth-basedoperations will be a checks and balancesfunction analogous to the missionengineering functions executed during SpaceShuttle missions. Hardware and softwaredocumentation will be available to the crewon board for real-time systems operations andfailure response. However, Earth-basedsupport must be provided for instances wheredocumentation is limited or does not cover aparticular situation.

Except for the above mentioned nearreal-time mission phases, data monitoring byEarth-based personnel must be limited toperiodic evaluations. Data and

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communication constraints will make real-time system monitoring by Earth-basedpersonnel impractical and unfeasible. Failuresand other systems issues will be worked byEarth-based personnel on an as needed basisand in support of long-term trend analysis.Vehicle and system maintenance andcheckout will be evaluated by the Earth-basedsystems experts to assist in crew monitoringand verification. Consumables managementsuch as usage planning and tracking will bedone by the crew (with some degree ofautomation) with Earth-based personneldoing verification only.

3.8.2 Science Operations

The science operations team’s solefunction is to recommend, organize, and aidin conducting all activities which supportscientific research within the guidelines of themission objectives. The team will consist ofrepresentatives from the various sciencedisciplines (biology, medicine, astronomy,geology, atmospherics, etc.) which supportthe science and mission objectives. Eachscientific discipline will have an appropriatesupport team of personnel from government,industry, and academia who have expertise inthat field. The science operations team will actas the decision-making body for all scienceactivities from determining which activitieshave highest priority to handling anddisseminating scientific data. The scienceoperations team will be coordinated andmanaged by the science operations manager,who will be the ultimate decision maker and

the primary interface between the scienceteam and the operations manager.

As science activities (such as initialinvestigations, clarification of previousresearch, and follow-up investigations) areproposed by various principle investigators,the science team will evaluate the proposedresearch, determine feasibility andappropriateness of the study, and selectappropriate crew activities based on availabletime and personnel. This process is similar tothe process used by the National ScienceFoundation for the U.S. Antarctic Programwhich has successfully operated remotescientific bases in Antarctica since 1970(Buoni, 1990). Selected science proposals willbe presented to the systems operations teamfor evaluation of feasibility and resources. Forexample, appropriate members of the systemsoperations team will determine if there areenough consumables to support the requiredactivities and if all of the desired activity isoperationally feasible from a systemsstandpoint. Upon verification, the proposedresearch activity will be submitted to the crewfor execution.

An initial set of science activities will beplanned before each crew departs Earth. Thisis especially true of the scientificinvestigations which support not only crewhealth and safety but also the primarymission objectives. As new discoveries aremade and new avenues for research areopened, an iterative science planning processwill become essential for the success andeffectiveness of all scientific activities.

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Successful scientific operations will alsorequire, when needed, crew access to theprincipal investigators for a given researchavenue. Such access must be made feasiblewithin the structure of mission operations.

3.9 Programmatic Issues

Three significant programmatic issuesmust be considered in an undertaking of thismagnitude, if the undertaking is to besuccessfully achieved: cost, management,and technology development. Each of thesefactors was examined to determine how theyshould be incorporated into this and furtherstudies of the Reference Mission orcomparable endeavors.

3.9.1 Cost Analysis

Cost analysis is an important element inassessing the value of a program such as thisand should be used from the very beginning.But at the beginning of a program and, inmany cases, up to the time that specificationsare written and contracts are let, it is notpossible to analytically determine the cost of aprogram. If new systems need to bedeveloped for programs, it is not possible toknow at the outset what the total cost will bebecause hardware is not on the shelf. Forthese reasons, cost models are used that aretypically based on historical data for similarprograms.

•The total program cost will be importantto the beneficiaries and resourceproviders, who will be interested inwhether to invest current and future

resources in this program or somealternative program. As many of thebenefits of an exploration program areintangible and long term, reducing theprogram costs to an understandable andsupportable level is of primeimportance.

•Whatever the total cost, the program willnot be undertaken if resources are notavailable. Thus, cost estimates can be thebasis for apportionment of resourcerequirements between participants,phasing of resource provisions, orphasing of mission elements to avoidpeak-year funding issues that couldstymie the program. Little has been donein the Reference Mission costing toaddress this question; however, thedatabase is available to analyze cost-phasing strategies.

•The cost of mission elements andcapabilities needs to be understood inorder to prioritize early investments intechnology and initiate other cost-reduction strategies. The estimated costof each element (for example, ETOlaunch) is related to the program risk,with higher relative costs associatedwith larger perceived risks ofdevelopment or operation. Thus,understanding the cost can be a first stepin designing program risk-reductionstrategies. As part of this process,estimates were also made of the costuncertainty for each of the technicalelements of the mission, which are also

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useful in understanding the appropriatecapability development strategies. In thepast, technology development effortshave focused primarily on improvingperformance. Now, it is important toaddress reduction of cost as a goal of thetechnology development program.

The cost of a program such as theReference Mission is a function of two majorvariables: the manner in which it is organizedand managed and the technical content of theprogram.

3.9.1.1 Organizational Culture and Cost

Management systems and theorganization under which programs areconducted are a major factor in the cost of aprogram. Basing costs simply on historicaldata implies that the management systemunder which the historical programs werecarried out will be assumed for the newprogram. This is a particularly seriousproblem in estimating the Reference Missioncosts, as the environment in which futurespace exploration will be carried out will bemuch more cost-conscious than in the past.Changes in management, for which nocomparative costs are available, will have tooccur. Because management style and cultureare introduced at each level of design andproduction, the leverage of managementchanges in making cost reductions can bequite high. However, such changes aredifficult to estimate. This is a major reasonwhy cost analysis should be considered adesign tool to be used at all stages of a

program. It is also a major reason to seekexamples or benchmarks in other programs todetermine the best possible managementapproaches to design and development, or toconduct specific programs under newmanagement rules as prototypes for theapproach that will be used in the actualprogram.

The cost of doing space missions lies atthe extreme edge of costliness in comparisonto other high technology systems. Thetechnical reasons for this appear to be thatspace missions:

•Are usually one of a kind or are projectswith small numbers of production units

•Are typically aimed at expandingcapability and technology, so aredesigned with small margins of mass,power, volume, etc.

•Have high transportation costs, so highreliability in the spacecraft is important

•Are expected to operate for extendedperiods of time in difficult environmentsand, in the case of crewed vehicles, theymust meet high standards of safety

The engineering and managementculture that has been built up around thesecharacteristics has stressed excellence ofperformance, safety, and high reliability. Costhas typically been a secondary criterion. It isnot clear that high quality performance andhigh reliability always require thecorresponding costly culture.

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To illustrate the effect of culture on cost,consider Figure 3-41 which shows the relativecost of programs developed using differentmanagement approaches. Point 0 is therelative cost for human spacecraft, point 1 isfor robotic spacecraft, point 2 for missiles, andpoint 3 for military aircraft. Differences inmanagement styles develop as a result of thedifferent environments in which programs arecarried out.

Table 3-24 depicts the differencesbetween a “Skunk Works” managementenvironment, such as might be used on amilitary aircraft development program (point2 in Figure 3-41) and the environment forNASA’s human programs. Some of thesedifferences will have to be addressed if thecost of human space exploration is to bereduced. To further illustrate differences,Table 3-25 compares the parameters of thedevelopment culture for commercial aircraftand NASA human programs. These arestarting points that indicate the changes thatwill be necessary.

The cost model used for the ReferenceMission (see next section) takes thesevariables into account in a “culture” variable,which can be characterized in more detail bysuch attributes as organizational structure,procurement approach, and the degree ofprogram office involvement in production.

3.9.1.2 The Cost Model

The cost model used for the technicalcontent of the Reference Mission is theAdvanced Missions Cost Model (AMCM)

(Cyr, 1988). This model considers the scale(particularly mass), the scope (number ofproduction and test articles) of thedevelopment of each of the systems requiredto undertake the program, the complexity ortechnical readiness for each of the systemsand their subsystems, the schedule underwhich the program will be carried out, andthe production generation in which the itemis produced. To the extent that experienceexists or off-the-shelf hardware can beprocured, more precise numbers can beestimated. The newer or more untried atechnology is, the greater will be its cost in themodel.

Input for the AMCM model was derivedfrom previous experience and informationprovided by members of the Study Team.Included in the estimate were thedevelopment and production costs for all ofthe systems needed to support three humancrews as they explore Mars. In addition,ground rules and assumptions were adoptedthat incorporated some new managementparadigms, as discussed later in the ProgramManagement and Organization section. Themanagement costs captured program levelmanagement, integration, and a Level IIfunction. Typical pre-production costs, suchas Phase A and B studies, were also included.

Not included in the cost estimate wereselected hardware elements, operations, andmanagement reserve. Hardware costs notestimated include science equipment and EVAsystems, for which data were not available atthe time estimates were prepared; however,

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Figure 3-41 The relative cost of programs using different managementapproaches.

these are not expected to add significantly tothe total. No robotic precursor missions areincluded in the cost estimate although theirneed is acknowledged as part of the overallapproach to the Reference Mission.Operations costs have historically been ashigh as 20 percent of the development cost.However, due to the extended operationalperiod of the Reference Mission and therecognized need for new approaches tomanaging and running this type of program,estimating the cost for this phase of theprogam was deferred until an approach isbetter defined. Similarly, the issue ofmanagement reserve was not addressed untila better understanding of the managementapproach and controls has been developed.

When compared to earlier estimates of asimilar scale (NASA, 1989), the cost for theReference Mission is approximately an orderof magnitude lower. A distribution of thesecosts is shown in Figure 3-42. It can be seenfrom this figure that the major cost drivers arethose associated with the transportationelements: the ETO launch vehicles, the TMIstages, and the Earth-return systems. Inaddition, the organization mechanismschosen have significantly reduced the cost forthese elements of cost, when compared totraditional programs of this type, creating asignificant challenge for those who wouldmanage this program.

The Mars Study Team recognizes that,even with a significant reduction in theprogram cost achieved by this team, the

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Table 3-24 Program Environment Effects on Program Management Style

Environment Factor "Skunk Works" ManagementNASA Human Program

Management

Political Environment - Major threat perceived by all involved

- Non-urgent- Threat not perceived as critical

Cost of Failure - Hidden - Public- Potentially catastrophic to Agency

Products - High technology- Prototypes- Experimental

- High technology- High quality "mature" designs

Risk to Life - Acceptable, but- Worthy of spending major resources to avoid

- Unacceptable- Worthy of spending major resources to avoid

Public Perception - Secret- Defense- Urgent- Unaware of existence until after deployment

- Public- Science, exploration- Discretionary- Every detail open to public scrutiny and criticism

Schedule - Typically 2 years - Typically 8 to 10 years

Quantities - Small to moderate - Small to moderate

Management Teams• Contractor• Government

- Very small (under 10)- Very small (3 to 10 typically)

- Moderate to large (dozens)- Large (hundreds)

Political Support - High - High

Cost - Small portion of parent agency budget- Low specific cost (e.g., $/1b)

- High percentage of parent agency budget- High specific cost

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Table 3-25 A Comparison of Development Culture Parameters for Commercial Aircraft andNASA Manned Programs

Parameter Commercial Aircraft Program NASA Human ProgramManagement

Customer Role Requirements definition, armslength

Highly interactive

Type of Requirements Performance of the product Detailed build specifications, some topiece part level

Program Office Size andType of Interactions

Small (tens or less)Interaction for clarification ofdetails

Large (hundreds)Interaction to lowest WBS levels

Proximity of Program OfficeRelative to Customer

Geographic separation, frequenttravel by very small groups

Geographic separation, with frequenttravel for face-to-face meetings bylarge numbers of project people

Competition Through Commitment to fixed price bysupplier

Three phases: end of preliminarydesign, program definition, start ofdetailed design and development

Technology Status at FullScale Development Start

Totally demonstrated flightsystems

Proof of concept

Management Systems Supplier's systems only:occasional tailored reports to thecustomer

Customer imposed, often duplicativewith contractor systems

Length of Full ScaleDevelopment

2 to 3 years 6 to 15 years

Budget Strategy Full commitment with guaranteesby both parties

Annual, incremental, high risk

Changes None to very few Thousands per year

Fee Type Included in fixed price Fixed, and/or award, based onsupplier performance

Contract Type Fixed price with incentives Cost plus fixed, award fee

SR&QA Industry and supplier standards Customer specified

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magnitude is probably still too high in today’sfiscal environment. More work to furtherreduce these costs is needed.

The largest cost element of the ReferenceMission is the ETO transportation systemwhich makes up approximately 32 percent ofthe total program cost. This element wasassumed to be a new HLLV capable of lifting220 tonnes of payload to LEO. Although thisis a launch vehicle larger than any previouslydeveloped, its design was assumed to bebased on the Saturn V technology, andengines were selected from existing designs.The costs of development were approximately20 percent of the total ETO Line Item, andproduction costs (assuming that 12 HLLVswould be produced to support the program,using 3 HLLVs for the first opportunity and 3HLLV launches at each of the remaining 3launch opportunities) were 80 percent of theETO Line Item.

To reduce the cost of the HLLVcomponent, several possible strategies couldbe used.

•Reduce the mass of systems,infrastructure, and payloads that need tobe launched into Earth orbit fortransport to Mars to support the surfacemission (assume that mission capabilityis not going to be reduced, which is alsopossible but not desirable). This couldreduce the total number of HLLVlaunches and the assumed productioncost. For example, Robert Zubrinbelieves that the program could be

carried out using two HLLV launchesper opportunity (requires somereduction of capability) (Zubrin, et al.,1991). Reducing the number of launchesfrom 12 to 8 would reduce theproduction costs by one-third and wouldreduce total costs of this element by 26percent. Developments in new materials,which are rapidly occurring, couldimprove systems performance andreduce the mass of the protective shellsand vehicle systems.

•Reduce the size of the HLLV (alsoproposed by Zubrin). This might ormight not reduce total costs, becauseadditional costs for on-orbit operationsmight be required. Reducing the cost oflaunch to LEO using reusable vehiclescurrently under consideration in thereusable launch vehicle program wouldrequire very large investments in LEOassembly. The trade-off might befavorable, but may or may not make asignificant reduction in total cost. Theavailability and use of an in-orbitassembly capability like the InternationalSpace Station could make this aneffective strategy.

•Improve the production efficiency forHLLVs. The AMCM model includes alearning curve assumption that eachtime the number of items produceddoubles, the cost per item is 78 percentof the previous production cost. Moreproduction learning could be very

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Figure 3-42 A comparison of the relative costs for Reference Mission elements.

significant. For example, if 12 HLLVs ofequal capability had been produced foranother program, the cost of HLLVs forthe Mars program could be cut by 22percent. To achieve these cost reductionswould require that no specialmodifications be necessary for the ETOvehicles used by the Mars program.

•A significant reduction in HLLV costmight be designed in at the start if newtechniques for manufacturing andtesting were introduced. However, thelearning curve benefits of massproduction might be less.

•The HLLV development was assumed tobe purchased by the government in a

conventional manner; however, someprocurement aspects were assumed to benew, and credit was taken in theestimates for these new ways of doingbusiness. The HLLV might be developedby industry at lower cost, to meetperformance specifications rather thangovernment technical specifications. Theassured sale of 12 vehicles may be largeenough to achieve some amount of costreduction to LEO, but is not likely tolead to major cost reductions. However,industry might be able to consider thegovernment an “anchor tenant” forHLLV production, develop additionalmarkets for their technology, andamortize the investment over a larger

TMI Stage

16%

Habitation

14%R&D

2%

ETO

32%CoF

1%

Surface Systems

11%

Space Transport

22%

Resources

2%

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number of vehicles. This would imply anassumption that the space frontier isexpanding significantly.

•The HLLV could be supplied by theRussians or as a joint effort by multipleinternational partners. This might be acontribution to an international programwhere it would be an example of cost-sharing between partners. At the presenttime, this does not appear to be a feasiblesolution; however, it may be reasonablein 15 years. If the U. S. or other partnerswere expected to pay the Russians fortheir participation, it would require theappropriate political rationale. If theRussians were to contribute the HLLVwithout payment, it would be theequivalent of one-fourth of the totalprogram cost, though it might not costthe Russians as much as it would costthe U. S. in absolute dollars.

•Finally, innovative advances inpropulsion could result in thedevelopment of new propulsiontechniques; for example, electromagneticpropulsion for ETO could substantiallydecrease the transportation cost for somematerials (propellant).

The Earth-Mars vehicle (the TMI stage)and the Mars-Earth vehicle (the ERV)elements provide for the delivery of humansand payloads to Mars and the return ofhumans to Earth. The costs are for thetransportation elements alone (theinterplanetary habitat elements are not

included). The TMI stage was costedseparately because it was assumed to requireseparate development of a nuclear thermalpropulsion system. The TMI stage wasassumed to be jettisoned before reachingMars. Conventional space storable chemicalpropellants were assumed to be used in theERV stage to return to Earth. The nuclearthermal stage assumed considerableinheritance from the U. S. nuclear propulsionprogram that produced the NERVA engines inthe 1960s; development costs for the TMIstage were projected to be 16 percent of thetotal cost. The space transportation vehiclesare all new and include several vehicles(ascent vehicle, crew capsule, and the TEIstage). The cost of the space transportationvehicles comprises 22 percent of the total.

The ratio of development cost toproduction cost for these vehicles is ratherhigh, partly because of the smaller number ofvehicles produced for the return home.Various ways of reducing the costs of theseelements might be considered.

•Development of nuclear electric or solarelectric propulsion vehicles that are moreefficient could lower transportation costsfor cargo but might not reduce costs ofhuman flights and might increase costs ifparallel development of twotransportation systems was necessary. Ifa single technology with higherefficiency than chemical rockets could beused to go to Mars and return, much ofthe cost associated with developing thespace transportation stages might be

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saved because the number of separatedevelopments would be minimized.

•Systematic application of newtechniques of automated design to thedevelopment process and use ofconcurrent engineering could reduce lifecycle costs of the systems.

•General improvements in methods ofprocurement and program managementcould have significant returns in theseareas. Reduction of integration costs canbe accomplished by centrally locatingdesign and development teams andkeeping simple interfaces betweensystems manufactured by differentproviders.

•Several vehicle elements could beprovided by international partners. Eachof the vehicles provided without cost tothe program could reduce total programcosts by several percent.

Habitats are an essential part of theReference Mission scenario. They represent 14percent of total mission cost and are assumedto have inheritance from the InternationalSpace Station program. The ReferenceMission has made the assumption that allhabitats required by the program areessentially identical, which is probably anoversimplification. To the extent the design ofspace habitats and surface habitats diverges,the cost could rise. Eight production habitatsare required. Modest learning curve costreductions are assumed for the productionline. About one-third of the estimated cost of

habitats is development, production is theremaining two-thirds. Thus, cost reductionsinvolving the improvement of design andprocurement processes are potentially themost important objectives. Note, however,that the habitats are also a significant masselement; therefore, technology that reducestheir mass will also have a significant effecton the transportation system.

Surface systems, including mobilitysystems and resource utilization systems,surface power, and other nonhabitat systems,constitute about 11 percent of the totalmission cost. Because these surface systemsare rather complex, critically determinemission productivity, and are a small fractionof the total, this area does not appear to be ahigh-priority source of major additional costreductions. However, mass reductions in thehardware will have high leverage in the spacetransportation cost elements, if the size of thetransportation vehicles or the number oflaunches can be reduced. Surface systemscosts are probably underestimated in thecurrent model, because no data for a closedLSS, EVA hardware, and science hardwarewere included in this estimate. Developmentof a suitable EVA suit will be a significanttechnology challenge and potentiallyexpensive. The closed environment LSShardware probably is not extraordinarilyexpensive. However, testing anddemonstrating it will only partially occur inthe International Space Station program, soadditional cost and risk are involved in itsdevelopment. Science equipment is not a

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major cost item, in comparison with the largecosts ascribed to the transportation system.

Operations was not included as part ofthe cost analysis, but has been previouslyestimated as a proportion (historically as highas 20 percent) of the total development costs.The operations costs are incurred primarily inthe 11 years of the operational missions. Theallocation of budget that would be associatedwith this estimate is equivalent toapproximately 20,000 people per year for thatperiod of time. This is definitely an old way ofdoing business which must change for theMars missions. A reasonable target would bean operational team of approximately l,000persons. This is likely to be attainable in partbecause automation and autonomy will be anecessary characteristic of the Mars missions.A principal mechanism for reducing thesecosts may be a directed program to reduce theoperational costs of the International SpaceStation as an analog to Mars missions.

The number and type of systemsrepresented in the Reference Mission is nearminimal considering the desired surfacemission capability. It is always possible toreduce costs by reducing the requiredperformance. For example, using the sameassumptions used for this model if only asingle landing were carried out, the totalprogram costs would be reduced by about 30percent in comparison to the full three pilotedmission program. Reducing the scope of thesurface activity will not have a big effect oncost, as it is already a relatively smallproportion of total mission costs, confirming

the expectation that optimizing the surfacemission for its benefit is also the way toimprove the benefit/cost ratio for the humanexploration of Mars.

The question of management style mustnow be addressed. Particular attention needsto be paid to the process by which theproduction elements are procured. Thecurrent estimates probably are still influencedby current ways of doing business. If totalReference Mission costs are to be reduced, it isat this level of effort that the most effectivechanges can be made. Focusing on the wrapfactors may not accomplish significantadditional reductions, although reducing theproduction costs will also reduce the amountthat must be spent in these areas.

3.9.2 Management and OrganizationalStructure

Organization and management is one ofthe principal determinants of program cost.This is a rather wide-ranging topic, which isnot entirely divisible from the technicalcontent of the program, because it includesprogram level decision making that isintimately tied to the system engineeringdecision-making process.

The magnitude of the Reference Mission,once it has been initiated, is enormous. Manygood examples exist of smaller programs thathave failed or have not performed well due tomanagement deficiencies. Thus, as theReference Mission is examined and improved,continued consideration should be given tostreamlining its management; assigning

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authority, responsibility, and accountability atthe right levels; and developing processes thatare simple, with clear-cut interfaces andmeasurable performance standards.

The relationship between cost andmanagement style and organizational cultureis rather well-known in a general manner,through a large number of lessons learnedanalyses made postprogram. The list of keyelements of lower-cost programs is shown inTable 3-26. These have been pointed out in aseries of analyses, but have not commonlybeen applied at the critical stage ofdeveloping program organization andmanagement approaches. Rather, theorganizational and management style hasbeen determined rather late in the program,generally because the program content andfinal design were typically delayed throughredesign, changing requirements, andfunding irregularities.

To manage a Mars program to a lowestpossible cost, a number of considerationshave been identified.

•The design of the organization andmanagement system should be an areaof investigation in subsequent studies ofthe Reference Mission. The relationshipbetween program cost and programculture is illustrated in Figure 3-46.Although several factors are involved,this figure indicates that significant costimpacts are tied to the organizationalculture and the management system.

•The human exploration of Mars will behighly visible to the world, will be a toolof international policy in manycountries, will be complex andexpensive, and will take several years todevelop. Under these conditions, it isessential that a philosophical andbudgetary agreement be reached prior toinitiating development. A formalagreement should be reached betweenall parties as to the objectives andrequirements that are imposed on themission before development is initiated,and an agreement to fund the project toits completion should be reached prior todevelopment. In the U. S., this wouldinclude multiyear budgetary authority.This should be accompanied by amanagement process that would protectagainst program overruns throughappropriate incentives.

•The human exploration of Mars willhave quite different risks than any spacemission which will have beenundertaken at its time. These includerisks to the safety of the crew andaccomplishment of the mission(primarily technical risks) and risks ofmeeting cost and schedule objectives.Maintaining launch schedule isexceedingly important, due to thedependency on several successfullaunches for mission success and thehigh cost of missed launch windows(missed launch windows imply 2-yearprogram delays at potentially high

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Table 3-26 Key Elements of Lower-Cost Programs

• Use government to define only requirements• Keep requirements fixed; once requirements are stated, only relax them; never add new

ones• Place product responsibility in a competitive private sector• Specify end results (performance) of products, not how to achieve the results• Minimize government involvement (small program office)• Ensure that all technologies are proven prior to the end of competition• Use the private sector reporting reporting system: reduce or eliminate specific

government reports• Don't start a program until cost estimate and budget availability match• Reduce development time: any program development can be accomplished in 3 to 4

years once uncertainties are resolved• Force people off development programs when development is complete• Incentivize the contractor to keep costs low (as opposed to CPAF, CPFF, or NASA)• Use goegraphic proximity of contractor organizations when possible• Use the major prime contractor as the integrating contractor

program cost). Thus a risk managementplan can help identify the risks andformulate a mitigation strategy.

•The Reference Mission requires anumber of elements, many of which aretechnically alike but serve somewhatdifferent functions over the duration ofthe program. For example, the surfacehabitat may be the basis for the transithabitat, and each habitat delivered to thesurface will have a different complementof equipment and supplies, according toits position in the delivery sequence. Theelements will be developed over aperiod of several years, and there will bea temptation to improve the equipmentand supply manifest. It will be importantfor requirements to be fixed at the timeof initial development to maintain cost

control for the program. To accomplishthis:

-There should be a clear demarcationbetween the design phase and thedevelopment/production phase of theproject, and development should notbegin before the design phase is ended.

-All technologies should be proved priorto initiation of production of programelements.

-Once the requirements have beenestablished, they should not be changedunless they can be relaxed.

-A system should be developed thatdocuments the relationship andinteraction of all requirements andshould be available for use prior to thebeginning of production.

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•The design phase of the program iscritical to successful cost control. Thedesign should be based on a set offunctional requirements established by aProgram Office, which may well be amultinational activity. The ProgramOffice should be in place to managetechnical requirements, providedecisions that require consultation andtrade-offs (technical and political), andmanage development contracts. TheProgram Office should also establishfunctional requirements for the designphase and conduct a competitiveprocurement for the design phase withthe selection of a prime contractor. Toaccomplish this:

-Requirements should be provided for thedesign phase, describing theperformance expected, and a clear set ofcriteria for completeness of design as afunction of resources expended indesign.

-A significant design cost margin shouldbe used to manage the design resources.

-The successful prime contractor shouldbe selected as integration contractor forthe development phase.

•Once committed to development, thedevelopment time should be strictlylimited if costs are to be contained. Thiswill be difficult in the Mars program,where it probably will be effective toproduce common elements sequentiallyrather than all at one time, although

there may be a high enough productionrate that costs will drop as experience isgained. A new approach will be neededto ensure that the development time foreach individual element is strictlylimited.

•The program will require two levels ofintegration, similar to that of theInternational Space Station program: aprogram level which ensures that overallmission requirements will be met at eachstage of the mission, and a launchpackage level integration in which allrequired elements of each launch toMars are packaged and theirperformance ensured. To accomplishthis, both aspects of integration shouldbe the responsibility of a singleorganization, a prime contractor to theProgram Office.

•The operational phase of the Marsprogram must be represented in thedesign and development phase. This willrequire a concurrent engineeringapproach which considers theoperational costs as well as thedevelopment costs in a life cycle costapproach to the program. To accomplishthis, operational considerations must beincluded in the design and developmentphases of the program, and life cyclecosts should be used as the determinantfor program design and developmentdecisions.

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•Finally, at all stages of design,development, production, andoperations, all program office officialsand contractor organizations must beincentivized to maintain program costswithin approved levels, and positiveincentives must be put into place toreduce costs of each phase of theprogram.

3.9.3 Technology Development

The Reference Mission was developedwith advances assumed in certain technologyareas known to be necessary to send people toMars for a reasonable investment in time andresources. The same objective could besatisfied using other technologies in somecases, making it necessary to identifyselection criteria for the set of technologies theReference Mission should favor. A reasonableinvestment also implies that there must besome reliance on technologies developed forother uses or simply discovered during someother development activity.

Dual-use technologies are those whichare deliberately developed with more thanone application in mind and which carryrequirements for these various uses throughthe development period. Spin off or spin intechnologies are those which are developedwith a specific application in mind but whichfind other uses with little or no additionaldevelopment work. Spill over technologiesare those which grow to include entirely new,unplanned technologies as a by-product of

the effort to bring the original technology toits desired state.

At this particular stage in developinghuman exploration missions to Mars, it isdifficult to do more than speculate about spinoff and spill over technologies that couldresult from, or be useful to, this endeavor.However, identifying dual uses for some ofthe assumed technologies can be started nowand, to a certain degree, will be required forsuch a program to progress. In the currentpolitical environment, investment intechnology is seen as a means of improvingthe general quality of life, and multiple use oftechnologies is emphasized to obtain the bestreturn on the resources invested in theirdevelopment. Space programs are not sparedthis requirement. A program strategy thatemphasizes dual-use technologies, besidesbeing consistent with this current trend could:

•More easily generate funds throughincreased cooperation and joint ventureswith other U.S. federal agencies,international partners, and commercialconcerns

•Provide smaller projects which could bemore easily funded

•Provide a step-by-step approach to theReference Mission

•Provide a stimulus to local and nationaleconomies

•Foster an increase in advocacy for spaceprograms

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To this end, the Reference Mission studyidentified and worked with 10 Mars mission-related technology categories: propulsion,communications and information systems,ISRU, surface mobility - suits, surfacemobility - vehicles, human support, power,structures and materials, science and scienceequipment, and operations and maintenance.These categories were then associated with atotal of 54 technology areas along with theirapplications. Tables 3-27 through 3-36document these various technologyapplications. In addition, the tables indicatewhere these technologies may spin off intoother applications and where developmentsin other areas may, in fact, benefit or spin intothe Mars program.

Not all of the advantageous technologyfor the Reference Mission must be developedby the program organization. Internationalcooperation can benefit from the technologyadvancements needed for this class of spacemission. Two obvious examples includeheavy lift launch technology and space-basednuclear power. The relatively heavy liftlaunch capabilities either developed ornearing completion for the Russian Energiaand the European Ariane V could form thebasis for at least part of a cooperativetechnology development program. Theformer Soviet Union had also developed arelatively sophisticated operational space-based nuclear power capability.

U.S. federal agencies can also cooperateto develop mutually beneficial technologies.The long-standing cooperation between

NASA and the Department of Energy todevelop small nuclear power sources forrobotic spacecraft could be expanded toinclude the development of larger powersources (perhaps as part of a cooperativeendeavor with the Russian government) orfor the propulsion system technologiesassumed for the Reference Mission. TheDepartment of Defense is currently studyingan integrated propulsion and electrical powersystem driven by the heat of the Sun(Reference: Anon., 1995). This could be atechnology useful to the Reference Mission asan alternative to the nuclear system assumedand form the basis for a cooperativedevelopment program.

Several specific examples may helpillustrate how technology development forthe Reference Mission will benefit from spillover, spin off, and dual-usage.

One of the precursor activities to theReference Mission that has a high priority willbe the characterization of the martian surfacein great detail by orbiting robotic spacecraft.Data collected by this vehicle or vehicles willbe needed in many areas to prepare for thisReference Mission. One of the mostsignificant areas will be the choice of alanding site at which the outpost will beestablished. This selection will be based inpart on information ranging from hazards inthe proposed landing zone to the proximity ofthe site to a variety of surface features, theinvestigation of which will contribute tomeeting the overall Reference Missionobjectives. Technology to obtain this remote

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sensing data could be available from the U.S.,Russia, Japan, and the Europeans, based ontheir previous Earth-orbiting, remote-sensingmissions and other planetary explorations.But due to the high cost of transporting thesesensors to the vicinity of Mars, furtherdevelopment or enhancement of thesetechnologies could reduce their size, mass,and need for supporting resources (power,communications band width, etc.).Advancements in other areas, such as the Kaband utilization, data compression, andinformation processing technologiesmentioned in the Communication andInformation Systems category or fromtechnology developed as part of the explosivegrowth in the PC marketplace, can also serveto improve performance and reduce costs forthese systems and the data they return. Anytechnology enhancement developed tosupport the Reference Mission will then beavailable for use in Earth-orbitingapplications.

The single largest cost of a human Marsexploration program may be the cost of ETOtransportation. The development of a newHLLV solely for the Mars program couldrequire up to 30 percent of the total resourcesfor the program. However, approaches thatcan launch the appropriate payloads to Marsusing smaller launch vehicles have notappeared to be viable in the past. This is aconundrum which has and may still stymiehuman exploration of Mars. Other avenuesexist:

•The Russian Energia heavy lift launchsystem can be maintained and upgradeduntil human missions to Mars can begin.A variation of this would be to evolve ahigher capacity launch vehicle usingtechnologies developed for Energia,Ariane V, and the Space Shuttle. Either ofthese options would offer anopportunity for internationalcooperation that would not only benefitthe Reference Mission but also allow forheavier, more sophisticated payloads tobe launched into Earth orbit or used forlunar missions.

•The mass of hardware required tosupport humans in Mars journeys can bereduced. Few concepts now exist forthis, but advancements in the technologyoptions mentioned in most, if not all, ofthe 10 categories identified by the MarsStudy Team will lead to a reduction inthe hardware mass that must be sent toMars. Each of the 10 categories alsoidentified Earth-bound applications thatmay also benefit from theseadvancements.

A third example involves the significantlevel of automation assumed for theReference Mission. The program assumesinfrastructure elements (including a system toproduce propellant and life supportconsumables, the first of two habitats, powersystems, and surface transportation elements)will robotically land on the surface at adesignated location. All of these systems willbe delivered, set up, and checked out using

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Table 3-28 Dual-Use Technologies: Communications/Information Systems

spin-inspin-offBoth

Terrestrial Application Technology Space Application

• Communications High-Definition TV Broadcast

• Ka Band or Higher • Telepresence: Vision and Video Data• Interferometers: Raw Data Transmission

• Entertainment Industry• Commercial Aviation

• Machine-Human Interface • Control Stations• System Management

• Communications• Archiving

• Data Compression Information Processing• Large Scale Data Management Systems

• Interferometers: Raw Data Transmission Information Processing• System Management, Expert Data• Archiving/Neural Nets

Terrestrial Application Technology Space Application

• Nuclear Reactors• Weapons and Nuclear Waste Disposal• High-Efficiency Heat Engines (Turbines, Thermostructural Integrity)

• High-Temp Materials • NTR• Aerobraking

• Clean-Burning Engines (H2/O2)• High Efficiency Cryo-Refrigeration

• Propellant Maintenance

• Higher Performance Commercial Launches • Methane/O2 Rocket Engines

• ISRU-Based Space Transportation

Table 3-27 Dual-Use Technologies: Propulsion

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spin-inspin-offBoth

Terrestrial Application Technology Space Application

• Mineral Analysis, Yield Estimation- Deep Mine Vein Location and Tracking• Wall and Ceiling Integrity

• Advanced Sensors • Mineral Analysis, Yield Estimation Surface Mineral Analysis, and Resource Location

• Deep Mine Robotic Operations • Mining • Beneficiating • Removal

• Advanced Robotic Mining

• Surface Mining Operations • Mining • Beneficiating • Removal

• Improved Automated Processing; Increased efficiency

• Automated Processing: Advanced FDIR

• Remote, Low- Maintenance, Processing

• Reliable, Low-Pollution Personal Transmission• Regenerable Energy Economies• Small, Decentralized Power Systems for Remote or Third World Applications

• Alternative, Regenerable Energy Economies • Methane/O

2

• H2/O2

• ISRU-Based Engines• Regenerable Energies• High-Density Energy Storage

• Environmentally Safe Energy Production • Space-Based Energy Generation and Transmission

• Surface Power Generation and Beaming

Table 3-29 Dual-Use Technologies: In Situ Resource Utilization

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Terrestrial Application Technology Space Application

• Hazardous Materials Cleanup• Fire Fighting Protection and Underwater Equipment

• Lightweight, Superinsulation Materials

• Surface Suits: Thermal Protection

• Robotic Assisted Systems• Orthopedic Devices for Mobility Impaired Persons

• Robotics• Mobility Enhancement Devices and Manipulators

•Robotic Assisted Suit Systems

• Hazardous Materials Cleanup• Fire Fighting Protection and Underwater Equipment

• Dust Protection, Seals, Abrasive Resistant Materials

• Surface Suits: Outer Garment

• Hazardous Materials Cleanup, Underwater Breathing Gear

• Lightweight Hi-Rel, Life Support • Portable Life Support for Surface Suits

• Remote Health Monitoring • Portable Biomedical Sensors and Health Evaluation Systems

• Surface EVA Crew Member Health Monitoring

• Hypo-Hyper Thermal Treatments• Fire Fighting Protection and Underwater Equipment• Artic/Antartic Undergarments

• Small, Efficient, Portable, Cooling/Heating Systems

• Surface Suits: Thermal Control Systems

Table 3-30 Dual-Use Technologies: Surface Mobility - Suits

Table 3-31 Dual-Use Technologies: Surface Mobility - Vehicles

spin-inspin-offBoth

Terrestrial Application Technology Space Application

• All-Terrain Vehicles • Research (Volcanoes) • Oil Exploration

• Mobility • Surface Transportation • Humans • Science Equipment • Maintenance and Inspection

• Reactor Servicing/Hazardous Applications

• Robotics and Vision Systems • Teleoperated Robotic Systems

• Earth Observation, Weather, Research • Super-Pressure Balloons (110,000 ft - Earth Equiv)

• Mars Global Explorations

• Efficient, Long-Term Operations Low-Maintenance• Machines in Artic/Antaric Environments

• Tribology • Surface Vehicles • Drive Mechanisms • Robotic Arms • Mechanisms

• Helicopers, Autos • Variable Speed Transmissions • Surface Vehicles

• Automated, Efficient Construction Equipment

• Multipurpose Construction Vehicle Systems and Mechanisms

• Robotic Construction and Set-up Equipment

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Table 3-33 Dual-Use Technologies: Power

Table 3-32 Dual-Use Technologies: Human Support

spin-inspin-offBoth

Terrestrial Application Technology Space Application

• Stored Food • US Army • NSF Polar Programs

• Long-Life Food Systems • With High Nutrition • Efficient Packaging

• Efficient Logistics • Planetary Bases • Long Spaceflights • Space Stations

• Improved Health Care• Sports Medicine - Cardiovascular• Osteoporesis - Immune Systems• Isolated Confined Environments/Polar Operations• Noninvasive Health Assessments

• Physiological Understanding of the Human/Chronobiology• Understanding of Psychosocial Issues• Instrumentation Miniaturization

• Countermeasures for Long-Duration and/or Micro-g Space Missions• Health Management and Care

• Health Care• Disaster Response• US Army

• Long-Term Blood Storage • Health Care for Long-Duration Space Missions

• Office Buildings("Sick Building" Syndrome)

• Manufacturing Plants

• Environmental Monitoring and Management

• Environmental Control for • Spacecraft Cabins • Planetary Habitats • Pressurized Rovers

• Contamination Cleanup• Waste Processing

• Waste Processing/SCWO• Water Purification

• Closed Water Cycles for • Spacecraft Cabins • Planetary Habitats • Pressurized Rovers

• Long-Life Clothes • Work Clothes in Hazardous Environments • US Army

• Advanced Materials/Fabrics • Reduced Logistics Through Long-Life, Easy-Care Clothes, Wipes, Etc.• Fire Proof/Low-Out-gassing Clothes

• Efficient Food Production • Advanced Understanding of Food Production/Hydroponics

• Reduced Logistics Through Local Food Production for • Spacecraft Cabins • Planetary Habitats

Terrestrial Application Technology Space Application

• Batteries/RFCs for • Autos • Remote Operations • DOD • NSF Polar Programs

• High-Density Energy Storage• Alternate Energy Storage (Flywheels)

• Reduced Logistics for Planetary Bases• High-Rel, Low-Maintenance Power Systems

• Clean Energy From Space • Beamed Power Transmission • Orbital Power to Surface Base• Surface Power Transmission to Remote Assets

• Remote Operations • DOD • NSF Polar Programs

• Small Nuclear Power Systems • Surface Base Power•Pressurized Surface Rover• Interplanetary Transfer Vehicle

• Remote Operations • DOD • NSF Poloar Programs• High-Efficiency Auto Engines

• High-Efficiency, High-Rel, Low-Maintenance Heat-to- Electric Conversion Engines

• Energy Conversion for Planetary Bases • Low Servicing Hours • Little or no Logistics

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Table 3-34 Dual-Use Technologies: Structures and Materials

Table 3-35 Dual-Use Technologies: Science and Science Equipment

spin-inspin-offBoth

Terrestrial Application Technology Space Application

• Vehicles• Fuel-Efficient Aircraft• Modular Construction (Homes, etc.)

• Composite Materials • Hard • Soft• Advanced Alloys, High- Temperature

• Cryo Tanks• Habitat Enclosures• Pressurized Rover Enclosures• Space Transit Vehicle Structures

TBD • Superinsulation• Coatings

• Cryo Tanks• Habitable Volumes

• Large Structures, High-Rises, Bridges• Commercial Aircraft • Improved Safety • Lower Maintenance

• Smart Structures• Imbedded Sensors

• Space Transit Vehicle Structures• Planetary Habitat Enclosures• Surface Power Systems• Rover Suspensions

Terrestrial Application Technology Space Application

• Energy Resource Exploration• Environmental Monitoring, Policing

• Spectroscopy • Gamma Ray • Laser • Other

• Geo-chem Mapping• Resource Yield Estimating• Planetary Mining Operation Planning

• Undersea Exploration• Hazardous Environment Assessments, Remediation

• Telescience • Remote Planetary Exploration

• Environmental Monitoring• Medicine

• Image Processing • Compression Technique • Storage • Transmission • Image Enhancements

• Communication of Science Data• Correlation of Interferometer Data

• Improved Health Care• Sports Medicine - Cardiovascular• Osteoporesis - Immune Systems• Isolated Confined Environments/Polar Operations• Noninvasive Health Assessments

• Physiological Understanding of the Human• Instrumentation Miniaturization

• Countermeasures for Long- Duration and/or Micro-g Space Missions• Health Management and Care

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robotic systems perhaps operated from or,more likely, merely supervised from Earth.Due to the communications time delay andthe absence of any local human operator orrepair personnel, these systems must becapable of performing normal operations,sense system failures or imminent failures,and, if necessary, safely shut down or repairfailed items. Chemical processing plants andmanufacturing plants on Earth areapproaching this level of sophistication and itmay be possible to adapt some of thetechnologies from these plants, as well asfrom technology that will exist in the future,to the Reference Mission. But as with theremote sensing example, the ReferenceMission will enhance the automation andmaintenance technologies used which willthen be available to Earth-bound users for avariety of applications.

3.10 References

Anon., “Air Force Looks to the Sun forNew Space Propulsion/Power System,”Defence Daily, McGraw Hill, December 7,1995.

Ash, R.L., W.L. Dowler, and G. Varsi,“Feasibility of Rocket PropellantProduction on Mars,” Acta Astronautica,Vol. 5, pp. 705-764, 1978.

Badhwar, G.D., F.A. Cuccinotta, and P.M.O’Neill, “An Analysis of InterplanetarySpace Radiation Exposure for VariousSolar Cycles,” Radiation Research, Vol. 138,pp. 201-208, 1994.

Barton, G., S. Shepperd, and T. Brand,“Autonomous Lunar LandingNavigation,” AAS 94-120, Advances in theAstronautical Sciences, Vol. 87, pp. 695-713,1992.

Table 3-36 Dual-Use Technologies: Operations and Maintenance

Terrestrial Application Technology Space Application

• Task Partitioning• R & QA in Long-Term, Hazardous Environments• System Health Management and Failure Prevention Through A1 and Expert Systems, Neural Nets

We mentioned this area as important, but did not complete. Recommend that we work with Jon Ericson and bobSavely to get ir right.

spin-inspin-offBoth

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Borowski, S.K., R.R. Corban, M.L.McGuire, and E.G. Beke, “NuclearThermal Rocket/Vehicle Design Optionsfor Future NASA Missions to the Moonand Mars,” NASA TM-107071, 1993.

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