The Design Report - The Mars...

The Design Report

Mars is not our limit Page 1

TABLE OF CONTENTS

1. Introduction……………………………………………………………………. 2

2. Goals and Requirements………………………………………………………... 2

3. Mission Operation…………………………………………………………….... 3

4. Launch vehicle………………………………………………………………...... 5

4.1 Descent Module………………………………………………………… 6

4.2 Instrumentation and Propulsion Module……………………………….. 6

4.3 Habitat Module…………………………………………………………. 7

5. Trajectory……………………………………………………………………….. 10

6. Flight system……………………………………………………………………. 11

7. Program timeline……………………………………………………………....... 12

8. Cost Estimation…………………………………………………………………. 13

9. Risk……………………………………………………………………………… 13

10. Conclusion………………………………………………………………………. 14

11. Acknowledgement………………………………………………………………. 15

The Design Report


INTRODUCTION:

It has been decades since man landed on moon. Moon was set as their target during the 20th century but now due to the development of various technologies, the target of human over the Solar System has increased, which also tend to increase his dominance over the Solar System for the betterment of the human race. Mars was just known as a red planet for a common man, but a giant resource for the scientists to increase their knowledge over the existence of other planets and other living being in the Solar System. Scientists have been doing research on mars for decades, but close flyby missions over Mars will increase their knowledge and further help in the future Mars Missions. The success of the Curiosity has increased the interest of the scientists, which has also led other countries to establish their dominance over Mars. But a human being to close to the planet’s surface will not only establish the dominance, but also be useful for studying the surface of the planet. In this report, we are honored to present our vision for the Mars Mission as asked by The Mars Society for a close flyby mission.

GOALS AND REQUIREMENTS:

In pursuing the mission described in the study report, we started by setting top level goals for the project. The goals for the project include,

� Demonstrate the feasibility of human mission to Mars.

� Foster knowledge, experience and momentum for space exploration.

� Address technical risks in human deep space exploration.

� Conduct research on the human physiology of deep space travel.

� Inspire youth through science, technology, engineering and maths education and motivation.

� Enable in-deep public participation.

In order to achieve the above goals, there are top level requirements to make the mission a successful one, namely

� Early development of Space Launch System (SLS) as designed by NASA.

� Two crew members, one man and one woman.

� Descent and Instrumentation/Propulsion Module of Soyuz spacecraft.

� Development of Habitat Module as per the design, within the schedule.

The Design Report


MISSION OPERATION:

Figure 1-1 shows the concept of operation to make a flyby mission over Mars. The designed Vehicle Stack would be lifted into Lower Earth Orbit (LEO) by the SLS rocket with the Dual-Use Upper Stage (DUUS), the only launch vehicle with enough throw mass for this job. Afterwards, the DUUS would perform the Trans – Mars injection burn to send the spacecraft and crew on their way to Mars.

The thrusters in the vehicle alter the trajectory of the Vehicle Stack sending it on a path to intercept Earth. Just prior to entry interface the crew would transfer over to the Descent Module and separate from the Habitat Module. The Descent Module would then carry out the Entry, Descent and Landing portion of the mission resulting in the safe return of the astronaut.

Figure 1-1 Concept of Operation

The Design Report


The mission uses the SLS rocket to launch the Vehicle Stack to the Lower Earth Orbit, the only launch vehicle with enough throw mass for this job. The SLS rocket plays a vital role in the success of the mission. The construction of the SLS rocket within the schedule is a necessary factor for the success of the mission. Figure 1-2 shows the SLS rocket used in the mission and the position of the Vehicle Stack in the SLS rocket.

Figure 1-2 SLS Rocket

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LAUNCH VEHICLE:

Figure 1-3 shows the structure of the Vehicle Stack used in the flyby mission over Mars. The Vehicle Stack comprises of the Descent Module, Instrumentation and Propulsion Module and the Habitat Module used in the mission.

Figure 1-3 Vehicle Stack

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1. INSTRUMENTATION AND PROPULSION MODULE:

Also known as the Service Module is similar to that of the Service Module used in the Soyuz missions for the transport of astronauts to International Space Station (ISS).

At the back of the vehicle is the Service Module. It is a pressurized container shaped like a bulging can that contains systems for temperature control, electric power supply, long-range radio communications, radio telemetry, and instruments for orientation and control. A non-pressurized part of the service module (Propulsion compartment) contains the main engine and a liquid-fuelled propulsion system for maneuvering in orbit and initiating the descent back to Earth. The ship also has a system of low-thrust engines for orientation, attached to the Intermediate compartment. Outside the service module are the sensors for the orientation system and the solar array, which is oriented towards the sun by rotating the ship.

With reference from the various sources, the dimensions of the Service Module is given as 2.72 meter in diameter, 2.26 meter in length and the maximum wing span of the solar array is 10.6 meter as that in the Soyuz missions.

2. DESCENT MODULE:

Also known as the Reentry Module is similar to that of the Reentry Module used in the Soyuz missions for the transport of astronauts to International Space Station (ISS) with a slight modification. The original module contains three seats, but the aim of the mission is to carry two people to Mars, so the Descent Module must be modified with two seats as shown in the figure 1-4.

The Reentry Module is used for launch and the journey back to Earth. Half of the reentry module is covered by a heat-resistant covering to protect it during re-entry; this half faces the Earth during re-entry. It is slowed initially by the atmosphere, then by a braking parachute, followed by the main parachute which slows the craft for landing. At one meter above the ground, solid-fuel braking engines mounted behind the heat shield are fired to give a soft landing.

With reference from the various sources, the dimension of the Reentry Module is given as 2.17 meter in diameter and 2.24 meter in length.

The Design Report


Figure 1-4 Modified Descent Module

3. HABITAT MODULE:

Figure 1-5 shows the Habitat Module designed by us for the flyby mission over Mars. The Habitat module provides the necessary conditions namely suitable temperature, pressure and oxygen to breath as in Earth, thus providing an artificial environment for the astronauts to survive during their trip to Mars and a safe return to Earth. The Habitat Module also provide the necessary tool and accessories for the astronauts to conduct their exprements during their journey. The Habitat Module also provide the comfort necessary for the astronauts to enjoy their trip to Mars.

The Habitat Module is 7 meter long and has a maximum diameter of 3 meter. The Habitat Module is provided with a Cupola as in International Space Station (ISS), which provides a 360º view for the astronauts. The Cupola provides an observation and work area for the crew and enjoy their journey through the Solar System, it also provides them a close look over Mars.

The Design Report


Figure 1-5 Habitat module

The Design Report


With reference to the figure 1-5,

1 � Cupola

2 � Refrigerator

3 � Oven

4 � Foldable beds

5 � Toilet

6 � Cargo setion [ Food & Accessories]

The designed Habitat Module consist of the above comforts for the astronauts. As stated above, the Cupola provides an observation and work area for the crew. The refrigerator and the oven provided in the design help the crew to store and heat their food in their journey. It also helps them to store important materials to conduct experiments in their journey through the Solar System.

The beds provided in the Vehicle are foldable, this help to increase the volume inside the Vehicle. They can be closed when not in use, thus increasing the volume inside the Vehicle. The beds can be designed is such a way to provide a maximum comfort for the astronauts during their journey through the Solar System.

The toilet in the Vehicle can be designed in the same way as in the International Space Station (ISS). This toilet can be used to for the collection and retention of liquid and solid wastes by using a flow of air.

The cargo section is located at the bottom of the Habitat Module, as shown in the figure 1-5. The cargo section contains the food for the astronauts. It also contains the tools and accessories for the astronauts to conduct experiments during their journey. It is designed in such a way to contain enough cargo for the astronauts.

aaaaaaaaaaaaaaaaaaaaaaa qqqqqqqqqqqqqqqqqFigure 1-6 Cross sectional view of HabitatModule

The Design Report


TRAJECTORY:

The trajectory is similar to that proposed by the Inspiration Mars’s Architecture Study Report, which is in the late 2017. This trajectory makes the journey quite faster and reduces the journey time of the crew.

Figure 1-7 Trajectory

This mission utilizes what is known as a “fast, free return trajectory.” This particular trajectory, shown in Figure 1-7, occurs only once every 15 years with the next opportunity arising in late 2017. The total travel time is 501days during which the crew will become the first people to leave the Earth-Moon system, to travel furthest from the Sun and to travel closest to the Sun. While this is still a long time compared to our spaceflight experience to date, it is quite fast compared to standard Mars mission concepts with durations of two to three years. The faster mission and small crew size reduces the amount of food, water and living space that will be required, allowing for the use of a smaller spaceship. The faster mission also reduces the radiation exposure to the crew. The smaller spaceship means that the rockets needed to carry out this mission are within the realm of today’s technology. The two person crew requires a relatively small re-entry capsule, which can be made using state-of-the-art technology.

The Design Report


The Inspiration Mars study Report shows that the re-entry speed of the Descent Module may exceed the speed limit of 14.2 km/second. Our study shows that the re-entry speed of the Descent Module can be reduced by following a series of step. Before the direct entry into the Earth’s orbit, the Vehicle can be made to orbit around the Earth, with the help of the thrusters place in the Service Module; the speed of the Vehicle can be reduced to a suitable speed for the re-entry of the Descent Module, thus ensuring the safe return of the Crew.

Figure 1-8 Approach near Mars FLIGHT SYSTEM: Flight system design includes environmental control and life support systems, solar flare protection, attitude control, navigation, communication, and reentry and landing technology. The life supporting system used in the vehicle is similar to that proposed by the Inspiration Mars report. Figure 1-9 shows the state of the Art System for Life Support, Thermal Control and Crew Health as per the Inspiration Mars report. The attitude controller is located in the Service Module. The attitude of the vehicle is maintained with the help of the thrusters located in the Service Module. The Service Module also has thermal sensors, command antennas, infra-red sensors and radio communication antennas for the purpose of navigation and communication. The reentry and landing technology is similar to that of a Soyuz landing. During the reentry, the Service and the Habitat Module detaches simultaneously from the Descent Module. The Descent Module enters the Earth’s atmosphere, where it is slowed initially by the atmosphere, then by a braking parachute, followed by the main parachute which slows the craft for landing. At one meter above the Surface, solid-fuel braking engines mounted behind the heat shield are fired to give a soft landing. Thus leads to a “splashed down" in the ocean.

The Design Report


Figure 1-9 Life Support System PROGRAM TIMELINE: This mission utilizes what is known as a “fast, free return trajectory.” This particular trajectory, shown in Figure 1-7, occurs only once in every 15 years with the next opportunity arising in late 2017. The total travel time is 501days during which the crew will become the first people to leave the Earth-Moon system, to travel furthest from the Sun and to travel closest to the Sun. The mission uses a 501 day journey through the solar system. The launch of the Vehicle must be between December 24, 2017 and January 4, 2018 which leads to a successful Trans Mars Injection, as given by the Inspiration Mars report.

The Design Report


The main requirements to meet the timeline of the mission are the development of the SLS rocket and the completion of the Vehicle Stack. The selection of the crew also plays a vital role in the mission. The fast return of the crew is a necessary factor to reduce the radiation effect on the crew, which helps in providing a safe journey to Mars. COST ESTIMATION: The cost of the mission mainly depends on to the Vehicle Stack. The Service Module of the vehicle must be bought from the Russian company (Korolev), the Descent Module must be bought and has to be modif ied for a crew of two members. The Habitat Module must be constructed within the schedule with all the necessary comforts and accessories as per the report which increases the development cost. The cost for the launch vehicle is less because in this mission we use only the SLS rocket which is developed by NASA, and hence the cost for the mission is reduced. According to various sources, we have found that the development cost of a Soyuz spacecraft is nearly $20 mil lion USD, but with an exclusion of the Orbital Module its development cost gets even reduced. The development of the Habitat Module with a cupola as in ISS might cost another $50 mill ion USD. The development cost might increase in the future days. RISK: The aim of the mission is to provide a safe and successful flyby mission over Mars. To satisfy the above conditions, we have to get rid of the following risks to make a successful mission.

� Schedule

� Radiation

� Development of SLS rocket

� Development of Vehicle Stack

SCHEDULE – This mission utilizes what is known as a “f ast, free return trajectory.” This particular trajectory, shown in Figure 1-7, occurs only once in every 15 years with the next opportunity arising in late 2017. Once we miss this opportunity we have to wait for next 15 years. To meet this schedule we have establish leadership commitments and organizational priorities that will promote the “can- do” environment needed to meet the January 2018 fixed launch date within expected budgets.

The Design Report


RADIATION – Radiation has always been a main risk for any space mission. Especially for such a deep space mission, radiation influences the health of the crew. To overcome this risk, the Vehicle Stack is coated with a layer of lead, thus protecting the crew from minor radiation risk from the Van Allen Radiation Belt. This can even be reduced by travelling through the weaker spots on the Van Allen Radiation Belt, where the effects of the radiation are less. DEVELOPMENT OF SLS ROCKET – SLS rocket plays a predominant role in the success of the mission, which is only under the development stage. SLS rocket is the only launch vehicle capable of carrying the Vehicle Stack for a successful Trans Mars Injection. The development of the SLS rocket leads to the Success of the mission. DEVELOPMENT OF THE VEHICLE STACK – The Vehicle Stack consist of the Habitat Module, Descent Module and the Service Module. Since the Service Module and the Descent Module are similar to that of the Soyuz spacecraft, the development of these Module are quite easier. But the development of the Habitat Module at right time to meet the schedule is necessary to make the mission a successful one. CONCLUSION: With reference from various information stated above, there is clear evidence that the mission can be a successful one. We agree that we have to work together for the remaining day to meet the schedule of late 2017. There are definitely challenges in developing the flight hardware and accomplishing the mission within the time constraint. However, there is an overwhelming belief that this mission is not only technically feasible, but programmatically achievable in the short time frame remaining. We believe that it is well-worth the commitment, resources and hard work to take advantage of this truly unique opportunity. In conclusion, we are proud to present this report to member of Mars Society, and we are proud of our report and our vision for the future of the human exploration through the universe. We have so much belief in our report that if our views through the report are executed in a proper manner the success of the mission is a guarantee. By the end of the May 2019 the crew would have reached the Earth safely and will become the first people to leave the Earth-Moon system, to travel furthest from the Sun and to travel closest to the Sun. By the success of this mission, the dominance of the human over the Solar System can be established. The success of this mission will be an initial step for the future space explorations.

The Design Report


ACKNOWLEDGEMENTS: We take this opportunity to express our profound gratitude and deep regards to those people and various sources both in internet and books which helped us complete this report a successful one. We would like to thank the Inspiration Mars report which helped us with the trajectory and the fli ght system in this report. The various internet sources provided us with necessary information for the construction of the Vehicle Stack and to make this report a successful one. Lastly, we thank almighty, my parents, brother, sisters and friends for their constant encouragement without which this report would not be possible. The blessing, help and guidance given by them time to time shall carry us a long way in the journey of life on which we are about to embark.

DREAM BIGGER MARS IS NOT OUR LIMIT

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