project ares: creating a feasible habitat for astronauts ......april 21th, 2012 abstract project...

2012 COSGC Space Research Symposium

Project Ares: Creating a Feasible Habitat for Astronauts on Mars

Stephanie Bonucci [email protected]

Jeremy Fenn

[email protected]

Marshal Kelley [email protected]

Geoffrey Gordon Sowash III

[email protected]

Colorado School of Mines Dr. Robert Knecht

[email protected]

Colorado Space Grant Consortium April 21th, 2012

Abstract

Project Ares is a Mars mission architecture based upon the concept of smaller launch vehicles which are used in conjunction with modular mission elements in order to allow for a lower cost manned mars expedition with a shorter developmental time frame. As such it is based upon non-theoretical technologies that could be deployed in a short term time span. Unlike many existing architectures involve sending several large units to the Martian surface, based on currently non-existing rocket designs. Project ARES implements a multi-stage landing system, where modules of the supplies are pre-deployed and land individually on the surface. Then automated vehicles will transport them to them to the proposed landing site. Once the astronauts have landed they will have access to large amounts of supplies without the need for designing large, expensive new rocket systems. Once all the mission elements are joined together they will form a fully operational, long-term habitat. Through these techniques we accomplish, the overall project goal of safely landing three astronauts on Mars where they will live for four hundred and fifty days before returning to Earth.


1. Introduction .............................................................................................................................................................. 3

1.1 Background ........................................................................................................................................ 3

1.2 Stage Description ................................................................................................................................ 3

2. Stage 1 MSL Based Pre-‐deployment .......................................................................................................................... 3

2.1 Stage 1 Launch Vehicle (LV) ................................................................................................................. 3

2.3 Stage 1 Modules ................................................................................................................................. 3 2.3.1 Storage Unit Module ............................................................................................................................................ 3 2.3.2 Expanding Module ............................................................................................................................................... 3

2.3.3 Active Radiation Shielding Module .................................................................................................. 4 2.3.4 Ares Unification System (AUS) ............................................................................................................................. 4

3. Stage 2 Manned Transfer Vehicles ............................................................................................................................ 4

3.1 Stage 2 Launch Vehicle (LV) ................................................................................................................. 4

3.2 Stage 2 Transfer Elements .................................................................................................................. 5 3.2.1 Transfer Habitat Vehicle ....................................................................................................................................... 5 3.2.2 Trans-‐Hab Expansion Module .............................................................................................................................. 5 3.2.3 Mars Modular Ascent Stage ................................................................................................................................. 5 3.2.4 Mars Modular Descent Stage .............................................................................................................................. 5 3.2.5 Modular Fuel Stage .............................................................................................................................................. 5

3.3 Stage 2 Transfer Mission Assemblies ................................................................................................... 5 3.3.1 Transfer Habitat Assembly .................................................................................................................................. 5 3.3.2 Mars Descent Stage Assembly ............................................................................................................................ 6 3.3.3 Mars Ascent Stage Assembly ............................................................................................................................... 6

4. Stage 3 Landing and Habitat Assembly ..................................................................................................................... 6

4.1 Landing Challenges ............................................................................................................................. 6 4.1.1 Stage 1 Landing Mechanism ................................................................................................................................. 6 4.2.1 Stage 2 Landing Mechanism ................................................................................................................................. 6

4.3 Supply Retrieval .................................................................................................................................. 6

4.4 Expansion of Habitat ........................................................................................................................... 6

4.5 ASRV Assembly ................................................................................................................................... 7

4.6 Final Assembly .................................................................................................................................... 7

5. Conclusion ................................................................................................................................................................. 7

6. References ................................................................................................................................................................ 7

Appendix A: Figures ...................................................................................................................................................... 9

Appendix B: Weights ................................................................................................................................................... 12

Appendix C: Specifications .......................................................................................................................................... 13


1. Introduction

1.1 Background

The inherent curiosity of human beings has led us to continually push our limits in space exploration. A manned mission to Mars has been presented as the next step forward in exploration. Such a mission would require astronauts to live on the surface of Mars for 450 days. These astronauts will face many challenges, primarily shielding from cosmic radiation, as well as a lack of food, water, and oxygen sources on the Martian surface. However, the greatest problem lies in safely landing a habitat that provides such resources on Mars. Project Ares implements a multi-stage landing system, different from existing designs, in order to overcome the challenge of landing on the Martian surface.

1.2 Stage Description

Project Ares is broken into three unique stages, with the first two being based upon distinctly different landing

techniques. The first stage is pre-deployment of supplies. This is accomplished with architecture and landing techniques based upon the MSL (Mars Science Laboratory). The second stage is the deployment of the vehicles utilized for manned transportation, both to Martian orbit, as well as to the surface of Mars. The third stage is the integration of hardware deployed in Stages 1 and 2 into the final habitat. The culmination of these three stages will provide a feasible shelter for the astronauts as they live on Mars.

2. Stage 1 MSL Based Pre-deployment

The modules implemented in the pre-deployment stage are all based upon the hardware created for the Mars Science Laboratory. Each of these modules are landed separately, and connected on the surface. The pre-deployment architecture consists of four types of modules. The conjunction of these will make up the existing supplies, that the astronauts will have access to upon reaching the surface. Module 1 is a storage unit for essential resources ranging from food and water to scientific equipment. Module 2 provides additional volume to the habitat by means of telescoping sections. This space provides crew quarters, research facilities, and storage. Module 3, the Active Radiation Shielding Vehicle (ARSV), provides electrostatic shielding from cosmic radiation. Module 4, the Ares Unification System (AUS), is a mobile unit whose purpose is to reconnect the other stages on the surface.

2.1 Stage 1 Launch Vehicle (LV)

Just like the MSL that the pre-deployment stage is based upon, these mission elements will be launched by the existing Atlas V 541 Launch Vehicle. Launching the Stage 1 modules in this manner will require little to no modification from the techniques used to launch the MSL. .

2.3 Stage 1 Modules

2.3.1 Storage Unit Module

Due to the nature of Ares’s design, the descent module with the crew will have room for very limited resources. To account for this, the remainder of supplies will be sent to the surface separately via storage units (Stage 1 of Ares). These units will attach to stage 2 of Ares, becoming accessible by the crew and will provide food, water, necessary recycling systems, etc. These units will have dimensions as follows:

• Length- 3m • Width- 2.75m • Height- 2.15m

The height includes the wheelbase, which is approximately 3 feet tall, leaving 4 feet of storage.


The wheel base does not have a motorized portion to give mobility, but instead, another rover pulls it where it is needed. After the storage unit has landed, it will be recovered by the AUS and assembled into the habitat. There it will be accessible to the astronauts throughout their stay on Mars to provide food, water and scientific equipment.

2.3.2 Expanding Module

The expanding rover has the ability to create habitat and laboratory space for the astronauts. It attaches to the main lander and then stored liquid polyethylene fills the walls, causing the entire rover to extend out before hardening. The void that was occupied by the polyethylene then becomes empty, usable space for the crew. The expanding wall is made up of aluminum sheets placed in layers. The walls are compacted into the shell of the two end caps, and when filled, flex into position much like an accordion. The two layers of wall, outer and inner, give the shape and size of the extended wall. The polyethylene that fills the walls is very effective by weight at blocking cosmic radiation and therefore will become effective passive radiation shielding. This allows for expansion while maintaining the necessary radiation shielding for crew survival. In order to rotate the expanding section into position the wheel base contains a hydraulic section with the ability to tip the rover. The two points of contact where the hydraulics connect allow the rover to pivot its body onto its end. The wheel base, once the rover has extended, is still wider than the habitat. This allows the extended rover to still be mobile if needed. The rover has four main components which include the end caps, wheel base, expanding walls, and the polyethylene storage container. The end caps are made of aluminum sheets and are 3 in. thick. Hatches are also present to connect to the other rovers and the habitat module.

The polyethylene storage container is a simple aluminum tank. It holds the polyethylene shielding that will go into the walls. It also has an attached pump that starts the filling process. The container can also fold into a smaller size once empty, in order to be removed from the original rover to utilize the entire space.

Overall, it has approximately the same dimensions as the above mentioned Storage Rover. These dimensions include the wheel base and components. Therefore the entire space is not usable, and when the wheels are taken into account the height of the usable space becomes 4 ft. This gives the expanding section an initial volume of 360 ft2.

The wheel base does not have a motorized portion to give mobility, but instead, another rover pulls it where it is needed. This joint is shown in Figure 6.

2.3.3 Active Radiation Shielding Module

The Active Radiation Shielding Module (ARSM) uses electrostatic spheres to combat dangerous high speed electrons and protons by using the fact that like charges repel. It is built with multi-directional wheels on the bottom so that it may be mobile with the assistance of the AUS. On top of the wheels lies a 5kW generator and from the generator comes a 22m telescoping pole with a dual triangular formation that will support the spheres (figure 4). The entire spherical support frame is made from 6061 aluminum alloy and polystyrene for minimum secondary radiation (radiation consisting of deflected atoms from the material radiation with which the radiation contacts) and minimum weight. The spheres of the ASRM will consist of 3 positively charged spheres with a 2m diameter in the inner triangle and 4 negatively charged spheres with a 4 m diameter in the outer triangle. There is also an extra 4m diameter negatively charged sphere at the center of the configuration (figure 4). These spheres will be made out of 25 µm thick film of Kapton® that is filled with titanium dioxide for UV protection of the underlying structure. The negative charge is on the outside because electrons are lighter and when they are stopped initially, the heavier protons are slowed, and there is more capability for proton reflection from the inner charged spheres. The central charge is to balance the spheres and for any excess electrons that make it through the first spheres.

2.3.4 Ares Unification System (AUS)

Due to the nature of Ares’s design, the descent module with the crew will have room for very limited resources. To account for this, the remainder of supplies will be sent to the surface separately via a storage units. In order for these units, which are un-powered, to be accessible by the crew, another module of Stage 1 must retrieve the supplies and bring them to the habitat. After the storage units have landed, they will be recovered by the ASUS rovers and assembled near the planned landing zone of the ascent/descent vehicle. There it will be accessible to the astronauts once they have landed on Mars in order to provide them food, water and other necessities.


The AUS is the essential component to combine the stages of Ares on the surface of Mars to form the complete habitat. The ascent/descent vehicle will not be mobile, so it will be important to be able to bring the storage units, expanding rovers, and radiation shielding module to the landing. ASUS will have a towing system attached to the rear side, as seen in Figure 5 and Figure 6. The towing mechanism will be 18”, and will have an expanding mechanism with which attach to the other rovers. Overall, the ASUS is very similar to the storage unit, with the exception of having a motorized wheel system. Where the storage unit has space for supplies, the ASUS carries with it a motor system capable of towing loads up to the weight of the storage units. The AUS will have dimensions similar to the other Stage 1 modules, however it will not be carrying the weight supplies or scientific equipment to the surface. Therefore it will be modified to have increased speed and hauling weight over the existing MSL. In addition to this it would be designed to have lightweight seating attached and fly-by wire controls so that it could be used as a primitive form of transportation by the crew after all the supplies had been moved to the landing site.

3. Stage 2 Manned Transfer Vehicles

3.1 Stage 2 Launch Vehicle (LV) Launch Vehicle (LV) selection for stage 2 is based upon currently deployed launch vehicles. LVs that have been retired and no longer have practical production capacities will not be considered in this report. Furthermore launch vehicles that are currently in development, such as the SLS and Falcon HVY, or theoretical launch technologies, such as NTP, will not be included because of the sizable developmental costs that could be avoided by using existing technologies. Due to the heavy lift requirements that are inherent in any planned mars mission only two domestically produced rocket systems could possibly be used in a manned Mars missions. The first of these is the Atlas V, which is used to launch the rover based cargo, radiation protection, transportation, and habitat elements that are pre-deployed to the surface. The second option is the Delta IV HVY rocket, which is the largest currently deployed launch vehicle. The Delta IV HVY was chosen as the LV for stage 2 because it has a larger payload capacity.

3.2 Stage 2 Transfer Elements

3.2.1 Transfer Habitat Vehicle

The Transfer Habitat Vehicle (THV) chosen for this application is the Orion MPCV currently in development with a scheduled testing date in 2014. It was chosen because no currently existing crew transportation modules would be able to support long duration missions of this type. The Orion module is the most mission capable module that will be available in the shortest time frame with the lowest developmental cost. The Orion MPCV, however was predominantly designed for lunar missions with a far shorter duration, of 21.1 days with a crew capacity of four. In order to augment the Orion for longer duration travel capacities a habitat expansion module will be necessary. The current launch vehicle selected for the first unmanned test flight is the Delta IV HVY, the same LV that has been selected for our stage 2 mission architecture.

3.2.2 Trans-Hab Expansion Module

The Trans-Hab Expansion Module (THEM) is included in the Transfer Habitat Assembly (THA) in order expand and supplement the capabilities of the Orion MPCV, in order to create a long duration habitat module that is acceptable for the round trip from the Earth to Mars. The chosen THEM for the mission is the Bigelow BA 330 expandable space habitation module. The Bigelow BA 330 is based upon TransHab technology purchased from NASA, which was originally conceived as a method to transfer humans to Mars. This technology involves the use of an inflatable hull, which allows for a 330 m³ pressurized volume while still providing radiation shielding equivalent to the International Space Station (ISS). The BA 330 is currently in development with a planned test flight in the same approximate time frame (2014-2015) as the Orion MPCV


3.2.3 Mars Modular Ascent Stage

The Mars Modular Ascent Stage (MMAS) is the proposed surface insertion vehicle used by the crew to enter the Martian atmosphere and land. Unlike most of the other mission elements, no existing or proposed vehicle meets the required specifications for the stringent requirements of landing on Mars. Therefore it will need to developed specifically for this mission. It is designed to dock with the mars descent stage in martian orbit before entering the atmosphere for descent. The bottom aeroshield, as well as main ascent/descent engine will be housed in this module, but not the descent fuel which will be contained in the descent stage (MMDS). The MMAV will contain the life support and recycling systems for the crew during the stay on the Martian surface. Due to weight considerations it is only designed for short term habitation while the supply and expanding habitat rovers move into position at the landing site.

3.2.4 Mars Modular Descent Stage

The Mars Modular Descent Stage (MMDS) is designed to supplement the MMAS, while it is docked to it during landing operations, by housing the top aeroshield, descent fuel, and parachute assembly. By doing so it lessens the amount of weight that must be physically landed on the surface. After aerobraking into the upper atmosphere it will deploy a parachute to assist slowing the craft. The powered descent rocket located on the MMAS will then draw fuel from the large fuel tank located inside MMDS until it is depleted. Then the MMDS will be released from the top of the MMAS and the drag from the deployed parachute will pull it free from the vehicle.

3.2.5 Modular Fuel Stage

The Modular Fuel Stage (MFS) is designed in order to boost the range capabilities of all mission elements. The MFS will be based upon the Delta III Cryogenic Second Stage and will be launched as the payload from Delta IV HVYs employing 5-metre second stages. The most notable modification will be the inclusion of a docking coupling to in order to attach to the other Manned Mars Transfer Elements in stacks in order to boost the overall range of the transfer assemblies. As the fuel from each MFS is expended the unit will be discarded from the assembly and the RL-10B engine from the next unit will begin its boost stage.

3.3 Stage 2 Transfer Mission Assemblies

3.3.1 Transfer Habitat Assembly

The Transfer Habitat Assembly will consist of a stack of four MFS elements, the Transfer Habitat Vehicle, and the Transfer Habitat Expansion Module. This Assembly will be the habitat for the crew of three during the entirety of the Trans Mars Injection (TMI) and Trans Earth Injection (TEI) stages of the mission. Overall mission time spent in transit will be approximately 400-450 days.

3.3.2 Mars Descent Stage Assembly

The Mars Descent Stage Assembly will consist of a stack of three MFS elements and the Mars Modular Descent Stage (MMDS). The MMDS will not dock with the MMAS until in Mars orbit to allow ingress of the crew into the MMAS.

3.3.3 Mars Ascent Stage Assembly

The Mars Descent Stage Assembly will consist of a stack of three MFS elements and the Mars modular Ascent Stage (MMAS). The MMAS will not dock with the MMDS until it reaches Mars orbit, in order to allow the ingress of the crew into the MMAS.

4. Stage 3 Landing and Habitat Assembly


4.1 Landing Challenges

Mars has a gravitational field approximately one-third the strength of the Earth’s, and an atmosphere less than one percent as thick. The combination of these two factors poses a serious challenge to landing a habitat on the Martian surface. Current methods of landing payloads on the surface are inadequate to land an entire habitat as a single unit. Airbags have been used more commonly in the past, however they are limited by the size of the payload and subject the payload to immense forces upon deceleration which would kill a human crew. Due to this

4.1.1 Stage 1 Landing Mechanism

In the same manner the Stage 1 modules will be able to use the same launch vehicle as the Mars Science Laboratory, due to their similarity in both dimensions and weight, the modules will be able to capitalize upon the framework of the sky-crane based landing technique. This will allow for landing equipment on the surface with nearly zero developmental cost.

The Skycrane begins entry like many previous entry designs, with the rover tucked inside a heat shield, and a parachute on top. When the heat shield has slowed the capsule to approximately Mach 2 (relative to the Mars atmosphere), the 65-foot parachute will deploy. Once the parachute has slowed the rover over the next three miles, it will be released along with the heat shields when the system’s rockets ignite, slowing the rover down to manageable landing speeds, where the Skycrane lowers the rover on a tether. Once the payload is on the surface, the Skycrane releases itself and crash lands a safe distance away.

The first stage of Project Ares was designed specifically to be landed by the Skycrane system, in order to decrease development costs and decrease the time needed to develop new landing systems.

4.2.1 Stage 2 Landing Mechanism

Once in Mars orbit the Orion MPCV will dock with the Mars Modular Ascent Stage (MMAS) and the crew will be transferred. Once the crew are safely aboard the MMAS, the MMAS will dock with the Mars Modular Descent Stage (MMDS). This docking operation will include attaching fuel lines to MMDS, as well as, combining the two sections of heat shield. Once the MMAS and MMDS have completed docking the crew will begin their descent.

The heat shielding will protect the vehicle as it begins to aerobrake through the atmosphere. Once the vehicle has slowed significantly a parachute will deploy from the top of the MMDS. Soon after parachute deployment, the bottom of the MMAS heat shield will be jettisoned and the main thrusters on the MMAS will begin to fire, while using fuel stored in the MMDS's fuel tanks. Once the fuel in the MMDS's fuel tanks has been exhausted, the MMAS will release the MMDS, which will be pulled free by the drag supplied by the parachute. Once separated from the MMDS, the MMAS will use the remainder of its onboard fuel in order to land.

4.3 Supply Retrieval

The AUS rover, as mentioned before, is equipped with an arm that attaches to the other rovers. In order to connect to

another rover, the AUS approaches another rover until approximately three feet away. The arm then extends and aligns with the receiving end on the other rover. Once in place, the end of the arm connects with the available space as seen in figure 6. The connected AUS rover can then pull the rover into position.

The arm is also equipped with a joint in order to accommodate turning while in transit. The rover, after pulling the rover to location, will then pull the arm out of the secondary rover. The exact process for docking is reversed so that the AUS rover can then service the next rover.

4.4 Expansion of Habitat

Due to the landing and transportation methods used, the rover is oriented on its side. This results in the two end caps, as seen in figure 1, being on top and bottom. The rover is pulled where it needs to be by the AUS rover via the connecting mechanism. After being located adjacent to the ascent module, the rover then rotates the expanding section, so that the caps can be separated. The hydraulics on the wheel base positions the rover so that the doors are able to attach to the main lander. Once in place and connected, the rover begins to expand. The pump begins to push the polyethylene material between the two layers of aluminum, and the resulting pressure causes first, the walls to fill, and second, the expansion of


the two end caps. After expansion the walls of the expanded rover contain six inches of polyethylene shielding. The shielding container is then collapsed by lack of volume, and can then be removed later by the crew. The rover has the ability to expand from 4 ft. to 13 ft. long. The new space has the following dimensions:

• Length- 4m • Width- 1m • Height- 2.5m The overall gain in volume is well over 200%. This space will be used together with the supply rover to give the crew

ample space to store their gear, and supplies, conduct research, and various other activities.

4.5 ASRV Assembly

Once the AUS has placed the ARSV near the rest of the habitation elements, its telescoping pole will fully extend. The electrostatic spheres will then have a charge sent through them from the generator and will be “inflated” by that charge by the repulsion of the other similar charges of a minimum of 100MV sent through the sphere. The ARSV does not need to physically combine with the other parts of the habitat. An alternative outlet, will be provided in case the generator inside of the ARSV fails, for redundancy’s sake.

4.6 Final Assembly

The AUS rover will then attach the storage units to the expanding sections, thereby giving the crew access to the

supplies needed. After this is completed, the habitat is finished. The final product is a fully functioning habitat with ample room for the crew. It contains all the fuel needed for ascent form the planet, as well as food and water for the 450 day stay. It has the necessary radiation shielding to protect the crew. Project Ares will sustain the three person crew for the full 450 days, allowing research to be conducted during that time. After the mission is finished, the crew will detach from the expanding sections, and being contained in the ascent module, the take-off from the surface will commence.

5. Conclusion

This report should not be seen as directly supporting a zero-development approach towards exploring Mars. Instead it should be seen as investigation into modular architecture, that could be used in conjunction with future developments in order to further the cause of space travel. Cutting short space development is in fact, would be the furthest from ideal.

If anything this report simply shows how close man is to being able to travel to mars, not remotely through probes, but directly. Many technologies and new systems were outside of the short-term developmental window outlined in this report, but that does not mean that they have been dismissed or ignored. New heavy lift rocket designs such as the SpaceX's Falcon HVY or NASA's SLS, will soon increase the capabilities of manned spaceflight even further. That being said, reports such as this one show that manned travel to Mars may not need to be 20-30 years in the future. Perhaps holding out for Ares or nuclear propulsion technology or whatever seems to be on the horizon is what has held us back in the past.


6. References [1] NASA, "Final Minutes of Curiosity's Arrival at Mars", July 19th, 2010.http://www.nasa.gov/mission_ pages/msl/multimedia/gallery/pia13282.html [2] Rivellini, Tommaso. "The Challenges of Landing on Mars". Engineering Challenges. Marshal’s Resources [3] Nelson, Jon. “Building Curiosity”. Frequently Asked Questions. 4/8/2012. http://www.jpl.nasa.gov/msl/ curiosity/index.cfm?page=faq [4] Watson, Tracy. “Troubles parallel ambitions in NASA Mars project”. USA Today. 4/14/2008. http://www.usatoday.com/tech/science/space/2008-04-13-mars_N.htm [5] R. M. Zubrin and D. B Weaver, “Practical Methods for Near-Term Piloted Mars Missions,” AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 29th, Monterey, CA, June 28-30, 1993. [6] H. Price et al., “Austere Human Missions to Mars,” AIAA Space 2009 Conference, Pasadena, California, September 16, 2009. [7] G. Bonin, “Reaching Mars for Less: The Reference Mission Design of the MarsDrive Consortium,” 25th International Space Development Conference, Los Angeles, California, 2006.


Appendix A: Figures


Figure 1: Un-deployed Expanding Module Figure 2: Expanding Rover preparing for deployment


Figure 3: Expanding Module beginning Deployment

Figure 4: Active Radiation Shielding Module


Figure 5: Storage Unit Module

Figure 6: AUS Tow Mechanism


Figure 7: Ascent Module Appendix B: Weights


Mars Modular Ascent Stage Weight

Structural Elements Main Structure 3,000 kg Lower Heat Shield 2,000 kg Main Propulsion System Main Rocket Engine 500 kg Supplementary Descent Fuel 1,000 kg Fuel Storage Tank 500 kg Reaction Control System 450 kg In-Situ Ascent Fuel System Hydrogen Feed Stock 4,000 kg Sabatier Reaction Plant 1,000 kg Supplies and Support Systems Consumables 6,500 kg Life Support System 2,000 kg Electronics Photovoltaic Power Generation

1,500 kg

Communications/Electronics 500 kg Total Ascent Stage Weight 22,950 kg

Mars Modular Descent Stage Weight

Structural Elements Main Structure 500 kg Upper Heat Shield 2,000 kg Coupler to Ascent Stage 500 kg Propulsion System Primary Descent Fuel 16,000 kg Fuel Storage Tank 1,500 kg Reaction Control System 450 kg Connection Plumbing 500 kg Descent Aero-braking Parachute Parachute 1,000 kg Electronics Electronics 500 kg Total Descent Stage Weight 22,950 kg


MSL Based Pre-deployment Weights

Storage Modules x 16 Unpowered Suspension

300kg x16 4,800kg

Container Structure 100kg x16 1,600kg Consumables Cargo 500kg x12 6,000kg Science Equip Cargo 500kg x4 2,000kg Total Storage Modules 900kg x16 14,400kg Expanding Modules x 4 Unpowered Suspension

300kg x4 1,200kg

Expanding Structure 100kg x4 400kg Polyurethane Filler 500kg x4 2,000kg Total Expanding Modules 900kg x4 3,600kg Radiation Shielding Module Unpowered Suspension

300kg x1 300kg

Field Generator 300kg x1 300kg Nuclear Generator 300kg x 1 300kh Total Radiation Modules 900kg x1 900kg Ares Unification Module x3 Suspension 300kg x3 900kg Drive Train 400kg x3 1,200kg Towing System 30kg x3 60kg Seat and Steering 100kg x 3 300kg Electronics 20kg x3 150kg Nuclear Generator 50kg x3 150kg Total Ares Modules 900kg x3 2,700kg Total Pre-deployment 900kg x24 216,000kg

Appendix C: Specifications Stage 1 Launch Vehicle Specs


Atlas V 541 Maximum Payload to LEO: 17,443 kg Maximum Payload to GTO: 8,290 kg Stage 1: Common Booster Core (CBC) x 1 and Aerojet Solid Fuel Rocket x 4 Stage 1 Engine: RD-180 x 1 and Aerojet AJ60 x 4 Thrust: 4,152 kN x 1 and 1,270 kN x 4 Stage 2: Centaur SEC Stage 2 Engine: RL-10A-4-2 x 1 Thrust: 99.1 kN x 1 Stage 2 Launch Vehicle Specs Delta IV HVY 9250H Specifications: Maximum Mass to LEO: 22,950 kg Maximum Mass to escape orbit: 9,306 kg Stage 1: Common Booster Core (CBC) x 3 Stage 1 Engine: RS-68 x 3 Thrust: 3,312.8 kN x 3 Stage 2: Delta Cryogenic Second Stage (5-metre stage) Stage 2 Engine: RL-10B-2 x1 Thrust: 110,1 kN x1 Orion MPCV Specifications: Pressurized Volume: 19.56 m³ Habitat Volume: 8.95 m³ Capsule Mass: 8,913 kg Service Module Mass: 12,337 kg Service Module Propellant Mass: 7,907 kg Total Mass: 21,250 kg Delta III Cryogenic Second Stage Specifications: Stage 2 Engine: RL-10B-2 x1 Thrust: 110,1 kN x1 Specific impulse: 462 seconds Burn time: 700 seconds Empty mass 2,480 kilograms (5,500 lb) Gross Mass 19,300 kilograms (43,000 lb) Bigelow BA 330 Specifications: Mass: 20,000 kg Length: 9.5 m Diameter: 6.7 m Pressurized Volume: 330 m³ Mars Modular Ascent Vehicle (MMAV) Maximum Crew: 9

project ares: creating a feasible habitat for astronauts ......april 21th, 2012 abstract project...

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