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Rzeszow University of Technology

Poland

Project of a manned, Mars flyby mission in 2018

Team name: MARS IV

Authors:

eng. Lukasz Beres

eng. Maciej Piotrowski

eng. Filip Nycz

eng. Grzegorz Szpyra

Translator’s help:

mgr Tomasz Gajdek

RZESZOW 2014

TEAM: MARS IV

Table of contents

Introduction ............................................................................................................... 3

Schedule ..................................................................................................................... 4

Trajectory ................................................................................................................... 8

Power and Radiators ................................................................................................. 11

Controlling of the spacecraft ..................................................................................... 16

Navigation during the mission ................................................................................... 18

Environmental Control and Life Support System ........................................................ 19

Communication System ............................................................................................ 29

Daily Schedule .......................................................................................................... 30

Research to conduct in space during a mission .......................................................... 31

Inhibition of Atmospheric Landers ............................................................................ 33

Mass Analysis ........................................................................................................... 38

Rocket choice ........................................................................................................... 39

Cost estimation ......................................................................................................... 41

Summary .................................................................................................................. 43

Bibliography ............................................................................................................. 44

TEAM: MARS IV

Introduction

Sending people on the flyby Mars mission will be one of the greatest events in the

history of mankind. During the mission it will be proven that humans are a specie capable of

colonizing space. There will also be a possibility to conduct many experiments and to test the

most advanced machines so far. The experiments will further improve current technology,

expand knowledge and bring about new experiences. This will allow in the future to further

increase the safety of manned missions in space and in the near future to colonize Mars.

The paper presents a general diagram of how a cheap and safe mission should look.

The mission schedule is presented and the trajectory that will be used is briefly described. The

following matters have been analyzed and described: all the systems that will be needed to

accomplish this task, average day of men on the mission, a number of tests that can be

performed during the mission. The idea of how to bring the samples of the surface of Mars

and its moon Phobos, which will be extremely useful in the study of the red planet. A mass

analysis necessary to collect such samples is presented at the end.

All ideas contained in this project are supported by the literature and are possible to

achieve by 2018. To minimize costs of the project mainly focused on technologies that

already are or will be available in the coming months.

The main objectives of the project:

1. When possible technology that has already been used should be used.

2. Use existing equipment as much as possible.

3. The simplicity of each system, which results in reliability.

4. Each system must be duplicated in the event of failure.

5. In case of an emergency the design provides astronauts with at least two possible ways

to react.

6. The mission schedule is arranged so that at key moments there is a possibility to

change it in the event of a major accident.

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Schedule

Below there is a table that describes the most important tasks to be performed before

the start of the mission.

Tab. 1. Preparations, which have to be done before planned mission

Arrangements to mission

Date 2014 2015 2016 2017 2018

Action Description

Choosing crew

Accepting submissions of candidates

for the mission (man and woman). It

would be nice if at least one of them

was already in space.

Building the

ship and very

intensive

testing

Finding sponsors, raising money,

building the ship. Each element of the

mission must be tested. Develop

schedules and scenarios in the event of

failure.

First launch the

Falcon Heavy

The company Space X plans the first

launch Falcon IX Heavy in 2014 or

2015.

Crew training

Very intense training, service ship

repair devices, etc., survival training,

psychological training. Reserve crew

training.

Study navigation by the stars. The

study of atmospheric braking

performance in the event that had to

perform manual braking.

The following table shows the schedule of the mission. The table lists the key elements of the

mission and describes them richly.

During the mission, it must be possible to check every system - automatically and manually at

any phase of flight.

Tab. 2. Mars’s mission schedule

Mission

Lp. Action Description

1.

Start from the Earth

rockets with Deep Space

Habitat (DSH)

The Falcon IX Heavy rocket will be used to carry DSH.

Aerodynamic shields will be deployed after leaving the

atmosphere.

It will carry DSH off to the optimal LEO trajectory. This

will be the orbit of the ecliptic inclination.

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2. Start of a crew

The Falcon IX Heavy rocket will be used.

The rocket will carry Orion lander and Mars Sample

Recovery System (MSRS).

At the time when no longer needed LAS (Launch Abort

System) will be ejected from the rocket.

After leaving the atmosphere aerodynamic shields will be

ejected.

The Orion lander and MSRS will be placed in the same orbit

as DSH.

3. The docking of the DSH

and the Orion lander

DSH and Orion find themselves in the same orbit. This will

bring them closer and connect.

4. Testing of all systems

When raised into orbit, some systems may be damaged. At

this time, you will be able to test all the systems that are in

the ship and rectify any faults.

5. Putting the ship on a

trans-Mars trajectory

In the perihelion engines will be fired, which will enable

inclusion of the vessel on the trans-Mars trajectory. Then

any trajectory amendments will be made.

6.

Disconnecting landers,

collecting samples from

Mars and Phobos

Disconnecting the Mars Sample Recovery System (MSRS),

which will be placed on the elliptical orbit of Mars.

The next phase of MSRS:

- Leave the return ship in orbit,

- Dropping the landers to Mars and Phobos,

- Taking samples,

- Landers taking off from the surface of Mars and Phobos,

- A combination of vehicles,

- Ship take off with samples from of the orbit of Mars

(returning at the closest trajectory, which will allow the

return; orbit should be chosen so that it is the least energy-

intensive).

If something in the ship goes wrong, samples can return to

Earth in a different mission (in subsequent years), another

mission can intercept the cargo. It can be made with a

docking system that could take over valuable cargo

7. Mars proximity

trajectory

Implementation of EVA spacewalk Taking pictures of the

background of Mars that will be historical photographs.

8. Trans Mars Trajectory

Phase Beginning of going back in the direction of the Earth.

9. Getting closer to the

Earth Preparing to return to Earth phase.

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10. Disconnecting DSH

from the Orion lander.

Disconnecting the Orion lander from Deep Space Habitat

(DSH). DSH will perform atmospheric braking and stay on

LEO, to be catch up by ISS (using Lagrange point to change

inclination) and used in in-coming missions.

11.

Inhibition of Orion

lander’s atmospheric

braking

Placing the lander on the trajectory that allows the execution

of atmospheric braking. Implementation of atmospheric

braking (skip entry).

12. Braking by lander's

parachutes Implementation of parachutes braking (several phases).

13. Humans Landing on

Earth Astronauts landing on Earth and are taken by rescue teams.

Events presented above in Tab. 2 will follow each other in order shown in Fig. 1.

Fig. 1. Calendar

Below in Figure 2 and 3 simple diagrams are shown how the elements of the ship will

look, when placed on LEO. In the drawings there are visible connectors that allow to make a

combination of these two elements in one ship. Both elements have rocket engines that allows

spacecraft launching a trans-Mars trajectory. Drawings are made in the computer game

Kerbal Space Program.

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Fig. 2. The illustrated view of the lander Orion combined with MSRS, on the right the connector

that will enable docking to the DSH (this will carried by first rocket to LEO)

Fig. 3. The illustrated view of DSH in Earth orbit prior to the merger of the lander Orion (this

will be carried by a second rocket)

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Trajectory

It was decided to use existing trajectory according to [1] Moonish R. Patel, James M.

Longuski, Jon A. Sims, Mars Free Return Trajectories, presented in JOURNAL OF

SPACECRAFT AND ROCKETS, Vol. 35, No. 3, May–June 1998 (Fig.4). This same trajectory

was chosen by Inspiration Mars Foundation in Feasibility Analysis for a Manned Mars Free-

Return Mission in 2018.

Fig. 4. Mars free return [1]

The main characteristics of 501-day “free-return” trajectory:

501 days duration only (low weight of supply for astronauts)

Safe free – return trajectory (allow to a safe return in case of systems failure)

No entry into Mars atmosphere (simplicity, lower risk, lower mass of spaceship)

Needs only small correction maneuvers during transit (less fuel needed)

Rare trajectory (occurs only twice per fifteen years)

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Tab. 3. Depart, arrive and hyperbolic excess velocity [2]

Leg Depart Arrive

1 Earth Jan 5, 2018 V∞ 6,226 [km/s] Mars Aug 20, 2018 V∞ 5,425 [km/s]

2 Mars Aug 20, 2018 V∞ 5,425 [km/s] Earth May 21, 2019 V∞ 8,914 [km/s]

Figure below shows positions of planets in Solar System during mission.

Fig. 5. Positions of the Earth and Mars on Launch Day (1), Flyby (2) and Reentry (3)

Figure 6 shows sketch of trajectory that including characteristic points described below.

Calendar of events is described in chapter Schedule.

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Fig. 6. Sketch of a trajectory

1. Launch Space Habitat and supplies

2. Launch Orion with Astronauts and MSRS

3. Connection of Two Parts (complete spaceship on LEO)

4. Trans Mars injection burn at perihelion to maximize range of spaceship

5. Trans Mars Trajectory achievement

6. Mars Encounter Entrance. Mars Sample Recovery System (MSRS) release.

7. Mars Encounter Exit

8. Earth Return Sequence

Mission assumed to put a MSRS on orbit of the Mars (MSRS is described in Research

chapter). Elliptical orbit (Fig. 7) of MSRS is perfect to conduct experiments on Phobos too.

Fig. 5. Sketch of a trajectory of a probe Fig. 7. Sketch of a trajectory of a probe

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Power and Radiators

Power from photovoltaic panels

To supply all the systems on board the need for M = 18 kW of power. This includes

the power to Deep Space Habitat and Orion lander. DSH and Orion will have a shared and

independent power system.

The primary source of power is solar energy obtained with the help of photovoltaic

cells produced by Sharp company - photovoltaic (IMM, 302x). They are characterized by high

efficiency conversion of up to η = 0.444. They have been used in space satellites.

Calculations for surface panels of the spacecraft were performed at the time when the

space craft is a near Mars. So that when, all of the cells fail, it will be possible to ensure full

power solely from solar radiation in the vicinity of Mars. Near the Earth where the solar

constant is much higher than nearby Mars, the panels are not fully distributed. Exposure of

panels to solar radiation and not obtaining energy from them can lead to damage - therefore

panels must be obscured if they are not in use.

The solar constant for Mars and Earth.

Tab. 4. Solar radiation for Earth and Mars (on orbits) [3]

Planet Distance Solar radiation

Perihelion Aphelion Maximum Minimum

Earth 0,983 1,017 1,413 1,321

Mars 1,382 1,666 715,0 492,0

The solar constant used for calculation:

Surface of panels needed to power the ship near Mars:

A - surface of panels

Surface of panels needed to power the ship is:

This area will be spread over four photovoltaic panels:

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R - radius of the photovoltaic panel

The panels will have an automatic control system. Equipped with independent sensor

positions of the sun, and electric motors. It task will be to maintain the position of the panels

so that they always face the sun.

Due to the fact that the photovoltaic panels are not in any way protected against

meteorites, the surface of the panels to be selected should be slightly larger than shows the

calculation. So that in the event of damage to a number of elements it will be possible to

continue to provide adequate power.

The safest batteries that can be used for the storage of electricity from photovoltaic panels are

nickel-hydrogen batteries (ISS uses them, the Hubble Space Telescope and many space

probes). They are very safe. Unfortunately, their mass is very large.

Calculation of the weight of the battery [4]:

Busy voltage 120 VDC

Peak load 18 kW

Maximum load duration 1,2 h

Maximum DOD 75%

Battery Nickel – hydrogen

Battery energy density 65 (W*h)/kg

Average cell voltage 1,3 V

The number of cells:

From the total charge capacity and battery energy capacity are

And

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The battery mass is

Lithium batteries

Battery energy density 650 (W*h)/kg

Average cell voltage 3,4 V

The number of cells:

From the total charge capacity and battery energy capacity are

And

The battery mass is

Much better in terms of weight are lithium-ion batteries, which are very light so they will be

used for the mission. The batteries will be placed in the warehouse where it is cool and dry.

Securing power from fuel cells

To provide maximum safety of mission the back-up supply will be used in case of

failure of photovoltaic panels. The power obtained from the system in the event of an

emergency if the solar panels were severely damaged must have the ability to sustain, power-

core systems. Fuel cells must ensure the system power is enough to protect life in Orion, as

well as communication systems and RCS.

Fuel cells will be placed in the Deep Space Habitat. The combination of the Orion and

Deep Space Habitat allow the transfer to power fuel cells between vehicles. Even if it was a

meteorite puncture, depressurizing DSH without the possibility of patching the holes are links

to ensure the provision of power to the Orion and maintain the operation of life support

system, communication system and the RSC.

The most secure cells are Alkaline Fuel Cells (called Alkaline Fuels Cells, AFC). The

electrolyte in the cell is potassium hydroxide solution. Gemini and Apollo had it and each

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space shuttle has a link. [5] The fuel they use is hydrogen and oxygen. As a result, it is

possible to obtain additional water, which can be used in life-support system in the event of a

major accident. Hydrogen storage tanks have to be covered with a layer of high-porosity

ceramic to volatilization does not occur due to a long hydrogen storage.

Radiators

The spacecraft will be heated by solar radiation and the working equipment on board.

Therefore, it appears that the spacecraft was in thermal equilibrium should pay him about 13

[kW].

Area of the radiators in the mission of the Orion Multi - Purpose Crew Vehicle (OM - PVC):

- Surface radiators - 31 - Thermal power dissipation – 6,3

Calculation of the required heat sink surface

Due to the lack of material data it is difficult to calculate the theoretical surface of the

heat sinks. Therefore, the surface was calculated from the ratio of the heat sinks.

Tab. 5. Data requested in further calculations of radiators

Mission Surface of radiators Dissipated thermal power OM – PCV 31 6,3

Our mission 13

64 - the surface of radiators

To reduce the surface of the radiators, you can:

- Maintain the position of the radiators so that they are in the shade of the spacecraft,

- Use the DSH and the lander Orion multi-layer heat shield and a new type of insulation

MLI,

- Cover the outer layer of the vessel with material which causes large sunlight

reflection,

- Inspection cover polished titanium layer. It allows to easier belching of radiation and

easier transfer of heat from the interior of the heat sink.

A ship in space is significantly heated by solar radiation. This leads to thermal stresses

of the ship's structure. During the missions of Apollo the vessel was rotated at a speed of

1

in order to avoid heating of the skip. The Apollo missions used the power from of the

fuel cells. In this mission, turning the ship to be evenly heated will be difficult to implement

due to the fact that it will be of photovoltaic panels, the position of which would have to be

constantly changed. This can be a big problem.

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Our new ideas to reduce the surface area of the heat sinks and photovoltaic panels

We can not calculate which solution would be the best. I do not have sufficient data on

modern materials. Therefore, we present two solution: reducing the absorption of heat and the

use of heat as a heat source for the heat engine.

1. Photovoltaic panels can be placed to cover the vessel. As a result the amount of heat

absorbed by the ship will be reduced.

2. Use the Sterling engine that will use a temperature difference side by a heated sun's

rays and the very cold which do not reach them. The side you want to heat can be

covered with titanium oxide from the side of which is heated , resulting in a very good

absorption of radiation. The other side of the vehicle can be covered with a polished

titanium to reduce heat absorption. In addition, system controls the position of the

vessel so that part of the ship covered with titanium oxide is turned toward the sun. In

order to accumulate thermal energy at one point of the heat pump can be used . In a

place where heat will be collected heat and cooled on the other hand, we can place the

Sterling engine. In recent years, Poland has patented Sterling engine modification. It is

called WASE 2. The modification consists the fact that there are no rods, which

greatly simplifies construction. The motor can be connected to an electric generator.

With this solution, the problem of cooling will be reduced and there will be an

additional source of electricity.

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Controlling of the spacecraft

Primary control system in darkness of space will be Reaction Control System (RCS) –

system which uses small thrusters to provide rotation control and sometimes translation. In

microgravity conditions, with no air resistance, RCS is the best way to provide forces and

torque to rotate spacecraft. Every vehicle, travelling outside Earth’s atmosphere, needs that

system operational to complete its mission.

For the purpose of Inspiration Mars project, where simplicity and lowering costs are

critical, borrowing concepts from another projects is necessary. Control a spacecraft can be

realized by simply adopting Apollo Lunar Module and Service Module RCS, and make it

slightly more powerful. In that missions, spacecrafts had thrusters grouped, and combined

with another one on the opposite site of the vehicle. Such system allowed to make corrections

in spacecraft attitude without affecting accuracy of their trajectories.

Fig. 8. Group of RCS thrusters on Apollo Lunar Module [6]

The system was qualified for manned flight during the unmanned Apollo 5 mission on

January 22 and 23, 1968, and has operated successfully during all LM flights. As we can read

in the Apollo Experience Report [7]: „The experience gained from Gemini missions and the

command and service module reaction control systems in the areas of system fabrication,

checkout, and testing also was applied to the lunar module reaction control system. The

system reliability requirements were achieved through system and component redundancy.

Two independent operational lunar module reaction control systems were provided. (…) The

performance of the lunar module reaction control system on Apollo missions was satisfactory.

Several minor problems occurred, but solutions were found for all problems encountered.”

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Fig. 9. Reaction Control System schematic [8]

Main layout of that system can be the same as in previous spacecraft, but development

of steering, control and sensors, may lead to increase efficiency and accuracy of deep space

maneuvering. Although computers and microprocessors are very reliable and can react too

changes a lot faster than human, system must have an option of manual control.

Despite very high level of reliability and accuracy, back-up system must be provided, but

secondary system, treated as a back-up, can be identical as primary, described by another

quote from that document: “With the exception of the failure of a chamber pressure

transducer bracket, the cluster design withstood all the mission-level random and sinusoidal

vibration loads to which it was subjected. Overstress vibration levels of up to 200 percent of

specification requirements also were imposed on the cluster without causing any significant

structural failures.”

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Navigation during the mission

Deep space navigation will enable Inspiration Mars to precisely target distant its

spacecraft. Navigation must take place in real time for control and operation of the spacecraft,

but also has to include later highly accurate reconstruction of the trajectory for subsequent

corrections. Using Deep Space Network during a cruise part will allow spacecraft to calculate

it’s position and orientation, using precisely timed radio signals sent back and forth to Earth.

It requires a team of scientists and engineers using sophisticated tools to calculate trajectory

first, then advanced high-tech radios, large antennas, computers, and precise timing

equipment is needed to ensure, that astronauts are on correct trajectory.

Massive parabolic-dish antennas, located around the world, have ability to follow all

spacecraft, if their distance from Earth is greater than 30 000km, always at least one antenna

can establish contact. The whole system is called Deep Space Network (DSN), and it is the

best way to communicate outside our planet. On the Mars Inspiration spacecraft there will be

at least four antennas, two of them – weaker omnidirectional, one have to work combined

with stronger, two beam saucers. Such way of cooperation is necessary for stable contact,

because of Earth and spaceship movement.

Fig. 10. Range of the DSN Antennas [9]

Before Inspiration Mars reaches proper distance, mission must be serviced by another way of

communication, like Near Earth Network. During short period of time, just before reaching

Mars, small corrections can be made using signals from martian orbiters – MAVEN and

MRO. Although mission’s primary way of navigation is DSN, new experimental laser

communication can be used for maneuvering and changing position, with by-the-way mission

objective - examining its reliability over very big distances, precision and speed of the

connection.

Every system, even the most reliable, can make a negative surprise and notice a

malfunction. In the worst scenario, when all of the systems fail to work, astronauts with their

onboard computers can still navigate in space using modernized Inertial Guidance Computer,

which uses gyroscopes and accelerometers to measure changes in vehicle speed, position and

orientation.

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Environmental Control and Life Support System

Environmental Control and Life Support System in short ECLSS is one of the

most important components of every human spaceflight mission. It should provide all

necessary items and conditions for maintaining life or health.

In order to perform that task the ECLSS executes several different functions [10]:

Provides oxygen for metabolic consumption

Provides potable water for consumption, food preparation and hygiene uses

Removes carbon dioxide from the air in the cabin

Filters particulates and microorganisms from the cabin air

Removes volatile organic trace gases from the cabin air

Monitors and controls cabin air partial pressures of nitrogen, oxygen, carbon dioxide,

methane, hydrogen and water vapor

Maintains total cabin pressure

Maintains cabin temperature and humidity levels

Distributes cabin air between connected module

Shielding against harmful external influences: radiation and micro-meteorites

Components of the life support system should be designed and constructed using safety

engineering techniques, because it is life-critical issue. Besides, the whole system must

become self-sustaining for missions where resupply is not practical. The most important

systems and installations should be also duplicated.

In the process of designing ECLSS major efforts would be put into several areas: providing

clean water and air, waste management, anti-fire system, Extra Vehicular Activity (EVA)

support, crew’s accommodation, environmental protection.

1. Providing clean water and air

The idea of systems providing water and air is presented at figure 1:

Fig. 11. Water and air circulation [10]

http://en.wikipedia.org/wiki/Safety_engineering

http://en.wikipedia.org/wiki/Safety_engineering

http://en.wikipedia.org/wiki/Life-critical_system

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Two main components of the ECLSS, which are OGS (Oxygen Generation System)

and WRS (acronym of Water Recovery System) [10] will be used to meet life support

requirements.

a) Oxygen Generation System

It is well known fact that it is not practical to carry all of the essential oxygen for the

purpose of pressure control, metabolic consumption during the mission, extra vehicular

activity etc. That is way OGS has to be based on state-of-art solutions. Oxygen should be

generated in water electrolysis process rather than by using CO2 technologies, which are

regenerable by desorbing to space vacuum or are single-use. However it will require

recovering water in more efficient way than usual. Also proper power supply module will be

necessary to electrolyze the water in quite efficient way. OGS based on electrolyze process

will also produce hydrogen, which can be used in Carbon Dioxide Reduction Assembly

(CDRA) [10]. The idea of CDRA is very simple. Once deployed, the reduction assembly will

cause hydrogen to react with carbon dioxide removed from the cabin atmosphere to produce

water and methane. This water will be available for processing and reuse, thereby further

reducing the amount of water needed to be taken from earth.

b) Water Recovery System

The main purpose of WRS [10] is to provide clean water by reclaiming wastewater,

including water from crewmember urine; cabin humidity condensate; and Extra Vehicular

Activity (EVA) wastes. The recovered water must meet stringent purity standards before it

can be used to support crew, EVA, and others activities. The Water Recovery System consists

of a Urine Processor Assembly (UPA) and a Water Processor Assembly (WPA). Unlike the

ISS Urine Processing Assembly that uses Vapor Conpression Distillation, the ECLSS design

uses a modified Urine Processing Assembly (UPA) with Cascade Distillation System (CDS)

as the primary urine processor. The product of the UPA w/CDS is then filtered, oxidized, and

added to the waste water tank for final processing by the WPA. While the calcium in urine

limits distillation processes between 70 – 85% recovery, this system recycles all of the water

[11]. The Water Processor removes free gas and solid materials such as hair and lint, before

the water goes through a series of multifiltration beds for further purification. Any remaining

organic contaminants and microorganisms are removed by a high-temperature catalytic

reactor assembly. The purity of product water is checked by electrical conductivity sensors

(the conductivity of water is increased by the presence of typical contaminants). Unacceptable

water is reprocessed, and clean water is sent to a storage tank, ready for use by the crew.

2. Thrash and waste management

According to definitions [12], trash consists principally of used or defective hardware,

expired consumables, or payload generated items no longer required for use during the

mission and are not significant contributors to the decay of the habitable environment. By

contrast waste consists principally of chemicals, radioactive materials, batteries, sharps, and

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biologically/biomedically active products and consumables of no further use to the crew and

not required to be returned. In order to maintain a hygienic environment, waste and associated

by-products should not be left on-board longer than necessary. Waste shall not be stowed in

the principle crew living and working area. It will be preferable solution to equipped crew

with 3D printer. This device can be apply to transform used plastic containers or bags into

different items such as tools or machine parts. In order to recycle as much water as possible

the Waste Containment System should be installed in crew habitat. WCS collects and

disposes of wet and dry trash and fecal waste, as well as controls the odor of urine. This

system also reclaims the water (from the urine, fecal waste, and wet trash) which is later used

by WRS. Analysis show that the brine from trash and solid waste further converted can be

responsible for about 50% percent of daily water recovery [11].

Beneath is presented the NASA’s concept of design Waste Hygiene Compartment, which can

be used successfully in planned mission.

Fig. 12: Waste Hygiene Compartment [13]

3. Fire Detection and Response System (FDRS)

NASA’s fire expert David Urban has told once that fire is among the most catastrophic

scenarios that can possible happen aboard spacecraft. “You can’t go outside, you’re in a very

small volume, and your escape options are limited. Your survival options are limited,” he

said. “Space can tolerate a much smaller fire than you can tolerate in your home. The pressure

can’t escape easily, and the heat stays there, and the toxic products are there as well.”

The main task of FDRS is to detect, annunciate and if it necessary extinguish the fire aboard

designed spaceship. FDRS is divided into three groups: detection, suppression and recovery

The fire detection system should provide fault detection and thermal sensing circuitry to

detect any current spikes within hardware and if one occurs, that system has to shut down

power to the hardware automatically. Also It should allow to localize any source of smoke

onboard. The second line of defense is fire suppression system. It would be responsible for

cutting of ventilation to the area affected by fire and routing area to post-fire clean up devices,

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which will be part of recovery system. In addition to this, a portable fire extinguisher could be

placed one per floor.

4. Extra Vehicular Activity (EVA)

Astronauts should be provided with two spacesuits, which will allow them to perform

necessary operations outside habitat. If untethered spacewalks will be required, space suits

should be equipped with modern version of the Manned Maneuvering Unit (MMU) [14] or

Simplified Aid for EVA Rescue (SAFER – Fig. 13) [15]. Besides in tasks, which do not

require human’s assistance or are too risky robonaut like NASA’s R2 (Fig. 3) [16] would be

perfect solution. Generally speaking, R2 is a humanoid robotic torso. This device is also

capable to assist with crew EVA's and it do not need specialized tools, because it can use the

same ones as the astronauts.

Fig. 13 Astronaut working with a SAFER system [15] and R2 humanoid robot [16]

5. Crew’s accommodation

One of the most important part of spaceship, which will take people to mars orbit is

habitat. The concept of that crew’s module can be designed in two different ways. First

approach may assume that habitat should have cylindrical shape like tuna tin can, so it will be

short and wide. This idea is presented at Fig. 14.

That kind of design allows to put more equipment per floor and separation between interior

and exterior of habitat can be larger so protection against radiation would be better. However

wider structure can be troublesome when it comes to send it into space. For only 2 crew

members it is better to think of different approach. Narrow cylindrical design, based on

already built and tested structure would be the best idea. Fortunately, NASA has already

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proposed conceptual design called Deep Space Habitat (DSH) [13] to support a crew

exploration beyond LEO.

In that project the habitat construction is partially based on ISS Destinity Module,

which was sent into orbit in 2001, so many crucial technologies has been tested in harsh space

environment. DSH is originally planned to be used in 2 variants. One of them is basic 60 day

mission variant presented hereunder at Fig. 15.

Fig. 14: Conceptual DSH Layout [17]

It consist of a Cryogenic Propulsion Stage (1), ISS Destiny-derived lab module (2), an

airlock/tunnel (3), and Orion – Multipurpose Crew Vehicle (4). The 500 Day mission variant

is pretty similar except of Multi-Purpose Logistics Module (MPLM) which will provide

additional supply storage for the extended mission duration. For designed Mars’s mission

concept for 2 astronauts, first variant without MPLM would be sufficient, because less people

onboard means less provision and more space inside habitat to keep it.

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Fig. 15. DSH configuration for designed Mars mission [13]

Special efforts should be put to achieve optimal arrangement of habitat interior in order to

provide safe, comfortable living and working spaces. In that case it is strongly recommended

at conceptual stage to base on anecdotal evidence from astronauts collected during different

evaluations and ISS post-mission debriefs [17], which actually may be find very useful source

of information. The crew usually prefer a clear separation of work and leisure areas.

Accordingly, science stations, EVA operations (suits and airlock), maintenance etc. should be

separated from galley or sleeping areas. If it is possible, it is also advice to make distinct

demarcation between noisy – dirty areas (like exercise and waste containment system - WCS)

and quiet – clean ones (crew quarters). The habitat construction and equipment should

provide astronauts with personal control over temperature, air flow, lighting, data and power

access. Also proper science and flight operation workstation will be required to fulfill mission

aims. For example, it is strongly recommended to install standard 20” ISS window in habitat’s

galley. It will allows astronauts to make high quality photos of Mars’s surface and

atmosphere, which can be later use to study geology or meteorology of that planet in a way

never seen before. Most of the features presented above, has been implemented in NASA’s

DSH concept what confirms that it is well-thought-out project worth to be put into practice in

designed mission to Mars’s orbit. Below are shown additional imagery of DSH:

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Fig. 16. a) Dimension of habitat from DSH concept [13]

Fig. 16. b) Interior of habitat from DSH concept [13]

It has been already told that crew will consist of 2 people so, approximately half of

habitable volume intended for crew quarters (DSH was originally designed for 4 astronauts

onboard – Fig. 16. b) can be used as storage space.

DSH has also one powerful advantage. The avionics for the DSH has been based on the

MPCV crew vehicle avionics what is really practical solution. MPCV vehicle is largely a

habitat vehicle with all the electronics required to operate ECLSS systems and provides a

robust communications system with good ground link and local communications capabilities.

That approach significantly increase safety level. If any emergency situation occurs and

habitat will be damaged, crew can use MPCV as a shelter, which will provide all necessary

systems required to support life. When situation will stabilize astronauts should take steps to

repair damaged modules.

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6. Environmental protection

Every spacecraft is exposed for threats such as micrometeoroids impact or radiation.

Fortunately, there are already developed technologies, which allow reducing danger.

a) Protection against micrometeoroids

Engineers have protected spacecraft from micrometeoroids and space trash in a

number of ways. At ISS There are 3 primary shielding configurations [18]:

Whipple shield-is a two layer shield consisting of an outer bumper, usually aluminum,

spaced some distance from the module pressure shell wall; the bumper plate is

intended to break up, melt or vaporize a particle on impact.

Stuffed Whipple shield-consists of an outer bumper, an underlying blanket of Nextel

ceramic cloth and Kevlar fabric to further disrupt and disperse the impactor, spaced a

distance from the module pressure shell.

Multi-layer shields, consisting of multiple layers of either fabric and/or metallic panels

protecting the critical item

In DSH External Micrometeoroid Debris Protection Shield (MDPS) is based on system used

in Multipurpose Logistic Module (MPLM). The real photo of MDPS is presented below:

Fig. 17 Debris shield design [18]

Beside, during spacewalks spacesuits will provide impact protection through various

fabric-layer combinations and strategically placed rigid materials.

b) Radiation protection

In space astronauts are exposed to stronger radiation than on Earth due to a lack of the

positive influence of Earth's atmosphere and magnetosphere. It is vital issue to know what

level will reach radiation on the trip from Earth to Mars. Luckily, this problem has been

solved thanks to Radiation Assessment Detector (RAD) shielded inside NASA's Mars Science

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Laboratory, which was sent to Mars in 2011. This device has measured radiation dose during

180-days transit to Mars. It is worth to compare the data collected by RAD with radiation

dose associated with for instance a six-month stay on the International Space Station, several

Earth-based sources of radiation or 500-day stay on Mars.

This comparison is presented at Fig 18.

Fig 18. Level of natural radiation detected by the RAD compared to radiation in different

human environments [19, 20]

According to the Fig 18. 180-days transit to Mars would result in a radiation exposure

of about 1 sievert. That level of radiation could be acceptable and do not pose critical threat to

Mars’s mission. The more important problem is connected with the spikes in radiation levels

presented at second chart in Fig 8. There are effects of large solar energetic particle events

(Solar flare events) caused by solar activity. Though rare, can give a fatal radiation dose in

minutes [21]. It is thought that protective shielding and protective drugs may ultimately lower

the risks connected with solar flare to an acceptable level [22]. Fortunately, DSH concept has

also described the way to shield crew against harmful radiation influence.

The idea of DSH radiation protection system would base on several 0.55cm thick

polyethylene tanks filled with water, which will create 9.9cm thick water wall sheltering the

crew and vital supplies:

Fig 9. Water wall as a way to shelter against radiation during solar flare events [13]

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It is also worth to combine waste management system (WMS) with protection against

radiation. It can be achieved by gathering for instance dehydrated, decontaminated solid fecal

waste between inner and outer shell of habitat.

In summarize, ECLSS is a quiet complex state-of-art piece of technology construct from

elements, which interact with each other in many ways, what is shown hereunder.

Fig. 17: Interaction of ECLSS’s parts [23]

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Communication System

The most inexpensive way to keep contact between spaceship and Earth for this

mission is to use existing systems. Close to earth it could be used TDRSS (Tracking and Data

Relay Satellites System) or NEN (Near Earth Network). During Trans Mars and Earth

Trajectory it is necessary to use DSN (Deep Space Network). Close to the mars and especially

when earth will be hidden behind Mars it is need to use MRO (Mars Reconnaissance Orbiter)

or MAVEN (Mars Atmosphere and Volatile Evolution). Both MRO and MAVEN could

provide connection for probe too.

This mission it is a good opportunity to use Laser Communications. It has been tested

by LADEE (Lunar Atmosphere and Dust Environment Explorer) this year successfully. Laser

Communication Devices are lighter than conventional and their energy consumption is lower.

This is new technology relatively and it could not be used as a basic communication system

but it could support DSN.

Tab. 6. The transmission data rate

System Kilobits per second (estimated)

TDRSS 72

DSN 10 to 6000

LASER 250 000

Currently, there are the three networks that Space Communications and Navigation (SCaN)

uses to support missions in space: the Deep Space Network (DSN), the Near Earth Network (NEN)

and the Space Network (SN). Each of these networks operates distinctly and separately from the other.

New project assumed that the three networks will be moving towards an integrated network. The

SCaN Integrated Network (SCaNIN) will provide standard services and interfaces to all missions by

2018. It should reduce costs.

To tracking a spacecraft the transponder is needed. New generation like Small Deep Space

Transponder (SDST) designed by JPL it is a perfect solution for this mission. It is compatible with

DSN and it weighs only 3 kilograms without aerials. It unifies a number of communication functions -

receiver, command detector, telemetry modulator, exciters, beacon tone generator, and control

functions.

The aerials system should be doubled to provide maximum reliability. It should contain two

kinds of aerials – omnidirectional antennas and directional antennas. Analyzing difference of signals

between antennas (using positive feedback) the system could find direction that the signal is the most

powerful. This indicates the direction of signal source (e.g. Earth).

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Daily Schedule

The costs of a mission are high so astronauts have to accomplished a lot of work such

as conducting experiments, exercising, performing maintenance work. During over 501 days

in small space the astronauts cannot have time to be bored. Too much off – duty time could

have negative influence on mental condition.

It was proposed to keep a diary by crew. The diary should include feelings, worries

and suggestions for improvement. It could help in further missions.

Tab. 7. Daily schedule

Designation Activities

1. Post sleep period Eat, shower, prepare to work or sleep longer

2. Morning conference

The astronauts discuss with each other and

with ground controllers about tasks (reading

received messages)

3. Exercise Physical exercises

4. Morning work Perform morning tasks, conducting

experiments, perform maintenance work

5. Lunch Prepare meals, eat, clean up and a short break

6. Afternoon work Continue morning work, discuss about

progress of work

7. Exercise Physical exercises

8. Pre sleep period / off – duty

time

Eat dinner, personal off – duty time, prepare to

sleep

It is recommended to change the schedule during mission to stave off fall into a routine.

Also it is strongly recommended to provide an entertainment such as movies, music and chat

with family or friends.

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Research to conduct in space during a mission

When travelling along interplanetary trajectory, astronauts will have unique

opportunity to conduct experiments in conditions not affected by an Earth’s atmosphere.

Between Earth and Mars there is no magnetic field, and external layer of the spaceship will be

exposed to the Solar Wind. That phenomenon, although very dangerous for every form of life,

can be very interesting for scientists around the World. Capturing and returning samples of

the Solar Wind can bring answers to many questions connected to that topic. Onboard

protection for astronauts must have their own sensor of radiation, especially during increased

solar activity. Measurement of that radiation, in wide spectrum of frequency can be integral

part of next interplanetary mission development. Interesting data may be collected by few

separate sensors, one located behind stronger protective cover, another situated behind usual

layer of external material, on the solar panels, etc.. With examination of different radiation

forms, a small radiotelescope can be helpful, so astronauts will take one onboard. Lack of

magnetic field, which can affect many events, is in that case an advantage.

Second kind of experiment, connected with microgravity and absence of protective

magnetic cover has definitely huge impact at life in deep space. Unfortunately, astronauts

must act as guinea pigs in that kind of experiment, but they can bring, and take care of

laboratory animals, like rats or hamsters. Measurement of data like pace of metabolism,

influence of magnetic and gravity field on human brain or blood circulation can help us get

ready to the future potential deep space missions. Very interesting, although controversial can

be experiment with rat insemination, evolution and parturition in microgravity. Apart from

macroscopic forms of life, astronauts can also observe and examine microscopic life. Bacteria

organisms was often main topic of research on the ISS, but above Van Allen belts, conditions

are different, and interesting to check. People, as a life form was not exposed for this hostile

environment for a long time, it will be first long-lasting deep space laboratory with onboard

life and protection system. Not only animals can be observed, people can try to grow

experimental food for animals, in order to examine influence of radiation on edibility of

plants.

Another experiment, worth performing is analysis of space dust and micro meteors,

which will hit external surface of the vehicle. Chemical composition of space object can be

determined with acceptable accuracy onboard, or returned to the surface of the Earth.

When approaching Mars, our deep space laboratory can measure intensity of Martian gravity

and magnetic field. Pretty obvious is taking pictures of Mars surface and in-flight

environment, including Earth, getting smaller and smaller.

Vehicles needed to acquire samples from Mars’s and Phobos’s surface

Mars Sample Recovery System (MSRS) is a interplanetary device created to recover

samples from the surface of Red Planet, and one of Martian satellites – Phobos. Spacecraft

will start its mission as a part of the Deep Space Habitat Spacecraft – Inspiration Mars project.

Main objective of MSRS is landing on Mars and Phobos and collecting small samples of

rocks or soil. In order to ensure that whole spacecraft will be as light as possible, it is required

for the mission to carry no additional equipment.

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MSRS Vehicle is designed to split in five main parts:

- Earth Re-Entry Capsule – (ERC) – designed to safely transfer samples of rocks or soil

through re-entry phase. Equipped only with room for approximately 5kg of interplanetary

cargo and tiny radiolocation device, for transmitting signal after landing. Transmitter’s task is

providing back-up service in case of landing in different place than expected.

- Earth Return Module – (ERM) – the central part in the whole system and spine of MSRS.

Attached directly to the Deep Space Habitat Assembly, ERM will reach Mars, while being on

free-return trajectory. After detach, retro rockets are expected to fire, in order to slow the

vehicle down to reach Mars orbit. As an additional method of slowing the spacecraft down

system will use atmospheric braking. ERM, with propellant necessary to come back to Earth,

is going to stay, orbiting Red Planet, while two landers detach and attempt to land on their

target areas. Vehicle must have at least tripled systems for navigation, contact between

unmanned spacecrafts and roundez-vous maneuvering.

- Phobos Sample Return Vehicle (PSRV) - simple small rocket with sample collecting

device. Because the characteristics of Phobos soil are uncertain, the lander must include two

types of soil-extraction tool, one of them can be a pipe shape tool, with some kind of drill for

soft lunar-like regolith, but as a backup a Polish-built drill CHOMIK (Phobos-Ground

mission) must be used, in case the soil turn out to be too rocky for the main scooping device.

- Mars Sample Return Vehicle (MSRV) – vehicle consists of two main elements: descent

stage is responsible for safe landing on the surface of Mars and ascent stage, which has to

transport tubes with soil or rocks, from the ground to ERM, waiting on the orbit. For the

purpose of mass lowering, both stages must be as simple, as possible. Ascent stage assembly

will take from the ground only probes, containing samples. Equipment, used for drilling and

digging is expected to stay on the ground, capturing images until battery would be effective.

Descent stage of MSRV may include needle-shape tool, that can be rammed into the ground -

using mass of whole vehicle - for examining, or extracting samples from below the topsoil,

top of that tool can be equipped with measurement instruments, for defining physical and

chemical properties of the ground.

- External tank – a container for propellant, necessary for ERM to launch trans Earth

sequence and get to coming-home trajectory.

Value of samples, delivered to the surface of the Earth, is non-measurable, many

laboratories across the world will do anything to do experiments on the real samples of

another planet.

Approximated mass of elements:

- ERC < 10kg

- ERV – 300kg (with fuel for trans-earth injection and maneuvering)

- MSRV – 300kg (dry mass)

- PSRV – 150kg (dry mass)

- Propellant for vehicles – 1000kg (summary)

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Inhibition of Atmospheric Landers

Inhibition of precipitation will be used to:

- Slow the lander Orion with people returning to Earth,

- Slow the DSH,

- To put the MSRS for upholstery Mars,

- The return of the ERC with samples from Mars and Phobos to Earth.

Benefits of using atmospheric braking:

- A very large reduction in weight, which should take on a mission (engine weight and

the weight of fuel),

- Reduce the risk that would occurred in the event that only engine braking will be

available (the possibility of a damage).

To inhibit the lander Orion, MSRS, the ERC will be used skip entry. Skip Entry -

"This type of trajectory offers Considerable in the control of high - speed entry" [4]. This

method of braking is used when it is not possible to directly enter the atmosphere and makes it

possible to avoid the problem of thermal control. Phase skip entry shown in Figure x phase

Balistic Coast (Skip) it is possible to radiative cooling of the disc lander before the next

plunge into the atmosphere.

Fig. 18. Phase skip entry [26]

The lander is a solid axisymmetric. To land humans on Earth will be used lander Orion,

designed to current NASA projects.

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Fig. 19.Orion Lander [27]

Speed that will have a lander Orion when entering the Earth's atmosphere is 8,914 [km/s].

For the Orion at a speed of 8,914 [km/s], the density of heat flow will rise to little more than 2

[MW/m^2].

How to perform Orion lander atmospheric braking:

1. Entry into Earth orbit must be in an appropriate air corridor, ie 100-130 [km]. Too

high will cause reflection, experience unacceptable for low load (thermal, mechanical

- a very large load). Lander must have a device that enables to measure the height of

the earth's surface and the density of the atmosphere in which it is immersed

(thickness of the atmosphere changed for many of the solar constant parameters, e.g.,

weather, etc.).

2. Analysis of meteorological (weather on Earth) must be sent to the lander carefully

before landing. Landing in a storm is very dangerous.

3. By changing the angle of entry into the atmosphere computer can change the

aerodynamic characteristics of the lander. Figure (x) shows how to change the

characteristics of the lander, depending on the angle of entry. This makes it possible to

perform skip entry. If it falls, so that the direction of the Orion is parallel to its axis of

symmetry landers coefficient lift is cz = 0, the slope so that it entered the 35° angle

(the angle between the streams, and the axis of the lander) we have the maximum rate

and is on cz = 0.55.

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Fig. 20. Aerodynamics characteristics of Orion CEV [28]

Fig. 20 shows aerodynamic characteristics of Orion CEV [x]:

- cz - lift coefficient

- cd - coefficient of drag force

- d - the perfection of the lander

- a - angle of entry into the atmosphere

4. As a result of dissipation of kinetic energy during braking lander atmospheric shield is

heated to very high temperatures resulting in the shield layer is formed around the

plasma. This leads to the interruption of communication, in this phase of flight, control

system performs automatic navigation, guidance, and stabilization.

5. The whole process is controlled landing stabilized and controlled by the computer. As

a result of the lander impact on the atmosphere will act tilting moments. Maintaining

the correct position of the lander will be possible thanks to the control center of

gravity. Any change of position will be implemented using RCS (Reaction Control

System). The lander will be able to switch to manual control when a system had failed.

Will be placed on the window scale, which will identify the landing site LPD (Landing

Point Designator). To do this, compare the data from your computer to scale to the

window.

The crew during training on Earth must learn to manual control atmospheric braking in the

event of any failure.

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Requirements to the Orion :

1. The lander made of titanium, beryllium and nickel alloys.

2. Seats must be matched to the astronauts dressed in suits (good matching to a man sued

endure much greater load).

3. Phase of flight lander planned so that the direction of the overload was always directed

to cosmonaut were always pushed into the seat. Human strength load is about 15 g -

forced into an armchair, 5-8 g of the other directions.

4. The lander made so that in the event of a lightning strike current is not passed to the

crew.

5. Variable center of gravity to ensure overlap with the center of pressure (the center of

mass and the center of pressure) caused by pressure changes at a variable angle of

attack lander. This change will be automatically adjusted by changing the location of

the seats on which they sat astronauts.

6. The use of airbags inside the lander during landing on the water. At the moment of

impact of water 15 g of overload using the cushion, and 50 g in the case when it is

used.

7. The lander will have the right color for easy transfer of heat (matt black).

Orion landing phase after braking atmospheric:

1. Rejection of the front cover.

2. Parachutes inhibiting, stabilizing the ship and reduce its speed (2 bowls) - at a height

of 45 [km].

3. Rejection of braking parachutes - at 10 [km].

4. The release of the three main parachutes pulling out - at 10 [km].

5. Pulling three main parachutes - at a height of 9 [km].

6. Parachutes primary unfold in several stages.

7. Main parachutes fully open - at the height of 8.5 [m].

8. Rejection of the guards, running other equipment needed to land (e.g. external airbags

to keep the lander on the water).

9. Disconnection main parachutes after landing.

10. Measure the height will be implemented with the help of GPS and pressure

measurement.

Capture astronauts by ground crews. The crew will use a boat and a helicopter.

1. The lander will be equipped with a global positioning system GPS control points can

land. In the event of failure of the system, the lander will be equipped with a

transponder that can be traced by radar.

2. The release of the lander dye-containing substance that will help noticing the lander by

a team of astronauts intercept.

3. Alignment of the pressure inside the lander ambient pressure.

4. Acquisition by a team of astronauts moving.

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Various examples of data in the Apollo missions:

- Max acceleration in the Apollo missions - 12 [g].

- Mission Apollo 4 (AS-501) the speed of atmospheric braking start - 11.2 [km / s].

- Apollo 17 landing accuracy - 1 miles.

Placing the MSRS for upholstery Mars will be implemented in part using motors and

atmospheric braking. Please note that the atmosphere of Mars is much rarer. This results in a

significant prolongation of the deceleration time. MSRS will be placed in elliptical orbit to

significantly save energy, what was that needed to be placed on a circular orbit. The data on

the atmosphere to carry out the braking will be sent from the analyzes that will be conducted

by the probe MRO - 2005 and MAVEN - 2013.

Inhibition of the ERC return samples from Mars and Phobos to Earth, will run very

much like a lunar lander Orion. At the same time there will be far fewer safety requirements.

For this ERC will weigh much less than the lander Orion, which will reduce braking time and

reduce the binding requirements of parachutes.

TEAM: MARS IV

Mass Analysis

Mass of components based on [13] Deep Space Habitat Configurations by David

Smitherman (Tab. 8) but calculations of masses were adopted for two-person crew.

Tab. 8. Table of Estimated Mass for 501-days mission for 2 astronauts

Component

Predicted

Mass

[kg]

Structures 9002

Power 698

Avionics 1177

Thermal 2780

Environment Protection 4175

ECLSS 4379

Crew Systems 552

Astronauts 160

EVA 272

MSRS 1760

MPCV 11600

Dry Mass 36555

Stowage Provisions 1383

Water 1298

Food, package 1321

Atmosphere Regen 474

Non-propellant fluids 200

Mass Reserve (10%) 2989

Total 44220

Notes:

- It was assumed to provide 10% Mass Reserve

- Atmosphere Regen includes Oxygen and Nitrogen

- EVA includes two Extravehicular Mobility Units and Airlock Services

- Food mass was calculated with 35% average moisture content because it is strongly

recommended to provide variety of food for astronauts (Astronauts can not eat only

dehydrated meals). It is a good way to keep crew in good mental condition

- MPCV provides crew ascent, entry, and on-orbit support including aborts

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Rocket choice

It was assumed that transfer payload in to optimal LEO orbit will be realized by two

Falcon IX Heavy Rockets (Fig. 21). First of them will carry DSH with all necessary supplies

for project designed. The second one will start later in adequate time with crew and MPCV.

All required fuel should be provided by the same rocket launches. However, if there will be

need for extra fuel it should launched by third time (it is not recommended).

Tab. 9. The Division of Mass Transportation

Launch Number Equipment Predicted Mass [kg] Notes

1 DSH + supplies 24955 Remaining payload

capacity should be

used to provide fuel 2 MPCV + MSRS + Astronauts 19265

We have analyzed the use of almost all the missiles capable of payloads into space.

Currently there are no large rocket like the Saturn V rocket Ares V project was canceled.

Renewal projects Saturn V or Ares V rocket and execution of 2018 swallowed up by huge

amounts of money. Start one of the currently used missiles is impossible.

The need for a minimum of two. Currently, the most reasonable solution is to use a rocket.

We can thus calculate whether the two rockets are enough to put DSH and lander

Orion MSRS LEO on orbit and fuel inventories putting on trans-Mars trajectory, or perhaps

run a small amount of fuel.

If there were problems with the output of the LEO on trans-Mars trajectory (due to the

very small amount of fuel) is another solution. If the rocket Space Launch System (SLS) will

be tested according to the plans in 2017 and its price was that competitive, you could use it to

lift DSH. This rocket is expected to be 70 tons to LEO. [29] Orion lander was elevated to the

previously assumed a Falcon IX HEAVY rocket.

Falcon IX Heavy parameters [30]:

- 53,000 [kg] – LOE

- 21,200 [kg] – GTO

- 13,200 [kg] – to Mars

- Height – 68,4 [m]

- Diameter – 3,66 [m]

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Fig. 21. Falcon IX Heavy Rocket [31]

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Cost estimation

Designed mission should combine few key features. It has to be simple, safe and as

cheap as possible. These conditions as whole are quite contradictive. However at current

technological level it is possible to meet those requirements and send people to Mars orbit.

The mission concept, which was presented in details in previous chapters, is really

simply. In short, two astronauts will be send to Mars orbit in vehicles based on NASA’s DSH,

which will be first delivered to optimally chosen LEO by 2 (or unlikely 3) Falcon IX Heavy

Rocket (FH) and later on send to Mars’s orbit using free return trajectory. Besides manned

units, MSRS module will be attached to spacecraft, which will be used to collect samples

from surface of Mars and Phobos.

Beneath are presented advantages of proposed mission:

Proposed lift rocket is assumed to be capable to transfer about 53t [24] to LEO. It is

the newest rocket on market and it will be launched in heavy configuration in 2014.

The most important devices used in rockets from Falcon family has been tested and

are generally based on state-of-art solutions derived from already known and reliable

technologies.

One FH rocket costs about 80-125mln USD, and cargo costs are about 1502 – 2350

USD/kg to LEO. [25] Assuming that data is correct; to transfer 40 metric tons to LEO

it is required about 200mln USD. That makes this rocket one of the cheapest one in

history.

DSH concept will be developed by NASA and used in various mission. Its

components like habitat derived from ISS modules, so will be easy to construct and

are in many ways already tested. Besides when one type of design is predicted to be

used in different mission, production costs will be gradually lowered.

ECLSS is mainly based on technology used at ISS, so its structure will be modular,

reliable and potentially cheaper from completely new solutions.

MSRS devices allow obtaining priceless samples from the surface of Fobos and Mars.

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The following table shows simple calculation of estimated costs.

Tab. 10. Simple calculation of costs

What Cost Notes

2 x Falcon 9 Haevy, carry

DSH, Orion lander + MSRS

and fuel to orbit

400 000 000 USD Space X company

LAS Cost of material + man-hours Within NASA

DSH Cost of material + man-hours Within NASA

Orion lander Cost of material + man-hours Within NASA

MSRS 100 000 000 USD

NASA and Space Research

Centre Polish Academy of

Sciences (CHOMIK)

Photovoltaic cells No data Sharp company

Navigation Cost of material + man-hours Within NASA

Communication system Man-hours Within NASA

Control of the mission Man-hours Within NASA

Total estimated cost About 500 mln USD + cost

of material + man-hours

Man-hours are very

expensive so the total

estimated cost could be

about 1 mld USD

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Summary

1. Taking into account a number of analyzes have been carried out, sending people in

2018 is 100% feasible. Currently, there is available technology that allows you to

perform this task. All the solutions that have been described are already proven,

developed over many years and fine.

2. The most problematic thing is the choice of the rocket. Facon IX Heavy is the most

promising rocket, which will enable us to realize this mission.

3. Many of ideas were considered to put the spaceship on a trajectory leading to Mars:

- Direct start with two rockets and connection of the DSH and the Orion on the

trajectory leading to Mars. This embodiment is impossible to perform due to

limitations of mass. In addition, there will be no chance to testing the ship's systems as

it is possible when the vessels will be placed on the LEO. Staying on the LEO in case

of failure of any system makes it easy to interrupt the mission. Life of crew is

important and should make every effort to ensure that everything was checked.

- Dispatch DSH little earlier before the window opens trans-Mars trajectory and

docking it to the ISS. It would be able to carry out checks on the operation of all

systems. When approached by the window start date to DSH disconnected from the

ISS and sent to him on a trajectory leading to the Moon in point L1 virtually free to

change the inclinations of the ecliptic (correction maneuver). Then DSH back simply

into Earth orbit. In orbit ecliptic would connect to the lander Orion. Then, fired by the

engines in the perihelion and put the ship on trans Mars trajectory. In comparison with

the orbit of the ecliptic, the flight of ISS requires an increase in speed by 3% [32].

Despite the fact that this is possible, however, further complicates the use of the ISS

mission and increases the risk of failure. It is better to put DSH on ecliptic orbit at

once.

4. People will have to spend a long time in space. This can be dangerous, however, the

mission of similar duration were held as exemplified by the ships, Polkow W.W. -

437.7 days, which he was in space during the mission Soyuz TM-18.

TEAM: MARS IV

Bibliography

[1] Moonish R. Patel, James M. Longuski, Jon A. Sims, Mars Free Return Trajectories, Vol.

35, No. 3, May–June 1998

[2] Dennis Tito, Taber MacCallum, John Carrico, Mike Loucks, Feasibility Analysis for a

Manned Mars Free-Return Mission in 2018, Future In-Space Operations (FISO) telecon

colloquium, 2013

[3] http://en.wikipedia.org/wiki/Sunlight

[4] Griffin M.D., French J.R.: Space vehicle design, American Institue of Aeronautics and

Astronautics, 2004

[5] Czerwiński A.: Akumulatory, baterie, ogniwa, Wydawnictwa Komunikacji i Łączności,

Warszawa 2005

[6] http://www.hq.nasa.gov/office/pao/History/alsj/a14/AS14-66-9254HR.jpg

[7] http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19720014237.pdf


[9] http://en.wikipedia.org/wiki/File:DSNantenna.svg

[10] http://www.nasa.gov/sites/default/files/104840main_eclss.pdf


[12] http://www.spaceref.com/iss/ops/SSP50481.nonrec.cargo.plan.pdf

[13] http://spirit.as.utexas.edu/~fiso/telecon/Smitherman_3-14-12/Smitherman_3-14-12.pdf

[14] http://en.wikipedia.org/wiki/Manned_Maneuvering_Unit

[15] http://en.wikipedia.org/wiki/Simplified_Aid_for_EVA_Rescue

[16] http://en.wikipedia.org/wiki/Robonaut

[17] http://www.csc.caltech.edu/references/RuckerThompson_DeepSpaceHab.pdf

[18] http://www.nasa.gov/externalflash/ISSRG/pdfs/mmod.pdf

[19] http://mars.jpl.nasa.gov/msl/multimedia/images/?ImageID=5771

[20] http://photojournal.jpl.nasa.gov/catalog/PIA16939

[21] Jay Buckey, Space Physiology, Oxford University Press USA, 2006

[22] http://en.wikipedia.org/wiki/Effect_of_spaceflight_on_the_human_body

[23] http://www.aiaa.org/uploadedFiles/About-AIAA/Press-Room/Key_Speeches-Reports-

and-Presentations/2013_Key_Speeches/Inspiration-Mars-FISO-Presentation2013-04-03.pdf

[24] http://www.spacex.com/falcon-heavy

[25] http://pl.wikipedia.org/wiki/Lista_ci%C4%99%C5%BCkich_rakiet_no%C5%9Bnych

[26] http://pl.wikipedia.org/wiki/Plik:Skip_reentry_trajectory.svg

[27] http://bi.gazeta.pl/im/1/5584/z5584421Q,Pierwszy-lot-na-ISS-nowa-kapsula-Orion-

wykona-prawdopodobnie.jpg

[28] Królik T.: Wyznaczanie charakterystyk aerodynamicznych lądownika statku kosmicznego

w zakresie prędkości hipersonicznych, Praca dyplomowa, Rzeszów 2013

[29] http://en.wikipedia.org/wiki/Space_Launch_System

[30] http://en.wikipedia.org/wiki/Falcon_Heavy

[31] http://www.freedomsphoenix.com/Uploads/338/Graph/falcon_9_heavy.jpg

[32] http://www.jakubw.pl/faq/astro/atyka_topic_4.html # _4_19

http://www.hq.nasa.gov/office/pao/History/alsj/a14/AS14-66-9254HR.jpg

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19720014237.pdf

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19720014237.pdf

http://en.wikipedia.org/wiki/File:DSNantenna.svg

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