Modular Roving Planetary Habitat, Laboratory, and Base

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1 Modular Roving Planetary Habitat, Laboratory, and Base RASC-AL COMPETITION April 30, 2004

2 Mission Statement Restore human exploration to the moon, investigating a large portion of the lunar surface Maximize the search for natural lunar resources through a mobile base Develop the experience and the required technologies for extended human space travel Returning to the moon is an important step for our space program The moon is home to abundant resources. Its soil contains raw materials that might be harvested and processed into rocket fuel or breathable air. We can use our time on the moon to develop and test new approaches and technologies and systems that will allow us to function in other, more challenging environments. The moon is a logical step toward further progress and achievement. ~ President George W. Bush

3 Science Objectives Study the effects of the lunar environment on life, especially long duration missions Radiation Skeletal system Cardiovascular system Plant and animal biology Nutrition and medical care Crew dynamics Muscle development and decay Study the moon and its resources Human performance and adaptations Volcanic and impact history Water ice and ore deposits as potential resources Deep lunar composition Environmental variations along the surface

and appeal of lunar structures Sites 1) Marius 2) Flamsteed 3) Gassendi 4) Tycho 5) Meretus 6) Drygalski

4 Assembly Sites and Selection Criteria Approximately 1000 km apart Apollo site candidates Surveyor landing sites Near Side Ore deposits and useful elements Permanently shadowed regions Age and appeal of lunar structures Sites 1) Marius 2) Flamsteed 3) Gassendi 4) Tycho 5) Meretus 6) Drygalski 7) Schrodinger 8) Minnaert 9) Mare Ingenii 10) Gagarin Far Side

5 Program Overview Designed to meet externally applied constraints Design/Manufacture Test Systems Launch Modules Manned Missions (every 6 months) Launch small, autonomous, mobile modules with specialized purposes to the moon Assemble the modules into a complete base Send a crew of 4 to the assembled base to conduct experiments for 3 lunar day-night cycles Disassemble base and send modules to next site of interest, up to 1000km away, over an unmanned period of 3 months

6 Module Types 6 Habitable Modules Size governed by launch vehicle payload size Need 6 to achieve the necessary floor space and volume to accommodate a crew of 4 for 3 months 6 Chassis with all-wheel drive Provide locomotion for Habitable Modules Equipped with transit connections to link vehicles in the transit phase 4 Power Modules with all-wheel drive Provides AC power to all modules Equipped with navigation computers and leads during transit

7 Modularity Transit configuration consists of 1 Power Module, 2 Habitable Modules, and 2 Chassis Modules Multiple base configurations

8 Benefits of Modularity Modules are less massive than a large-scale structure Can be launched on existing launch vehicles Increased mobility Capable of traversing great distances Multiple lunar base locations Science may be performed while modules are in transit Experiments may be subjected to long exposures to the lunar environment Feasible program expenditures Allows for cost spreading over the program duration Utilizes a cost learning curve

SUMMARY Burn # 1 2 3 4 5 Burn Name LTO LLO Lunar

9 Delta IV-H to LEO Getting to the Moon *NOTE: Not to Scale Burn 3 Burn 2 Burn 1 Burn 4 Burn 5 DELTA V SUMMARY Burn # Burn Name LTO LLO Lunar Descent Braking & Approach Landing ΔV (km/s)

Lunar Transfer and Approach Stage Modified Pratt and Whitney RL-10B-2 Isp: 465s LOX Tank Propellant Mass: 15960 kg Tank Mass:

can be throttled Titanium Thrust Structure Support loads of: 6g s vertical 2.

10 Lunar Transfer and Approach Stage Modified Pratt and Whitney RL-10B-2 Isp: 465s LOX Tank Propellant Mass: kg Tank Mass: 560 kg Insulation Mass: 50 kg Variable Density Multi- Layer Insulation to reduce boil off from radiation Mass : 280 kg Thrust can be throttled Titanium Thrust Structure Support loads of: 6g s vertical 2.5g s lateral Low Thermal Conductivity to decrease boil off Mass: 920kg LH2 Tank Propellant Mass: 2720 kg Tank Mass: 550 kg Insulation Mass: 200 kg VD-MLI to reduce boil off from radiation

5 kg Thrust can be throttled Reaction Control System Engine(32) : Kaiser Marquardt R-1E 3.

11 Lunar Descent Stage He Pressure Tank Not shown on model. He and Tank Mass < 5 kg Modified EADS S3K Isp: 350s Mass : 14.5 kg Thrust can be throttled Reaction Control System Engine(32) : Kaiser Marquardt R-1E 3.7kg Propellant Mass : 45 kg Tank Mass : 8 kg Support Mass : 20 kg MON3 Tank Propellant Mass : 145 kg Tank Mass : 45 kg MMH Tank Propellant Mass : 190 kg Tank Mass : 90 kg

Launch System Mass Breakdown Launch Transfer and Approach Stage Landing Stage Reaction Control System Engine RL-10B-2 S3K (2) R-1E (32) 277 kg 14.5 kg each 3.

12 Launch System Mass Breakdown Launch Transfer and Approach Stage Landing Stage Reaction Control System Engine RL-10B-2 S3K (2) R-1E (32) 277 kg 14.5 kg each 3.7 kg each Propellant LOX/LH2 MON3/MMH N 2 O 4 /MMH kg 330 kg 45 kg Tanks 1100 kg 130 kg 8 kg Structure 920 kg 150 kg 20 kg Resultant available landed mass: 3700 kg

13 Module Details Habitable Module Chassis Module Power Module

14 Habitable Module Science Specialized Living Specialized Living / Life Support 760 kg Avionics 100 kg Structural 1700 kg Descent / Landing 380 kg Power Systems 120 kg Total 3060 kg Margin 17% Docking Mechanism 3.7m Radiator Surface Area = 13.3 m 2 Absorptivity =.08 Emissivity =.92 4m

15 Habitable Module Structure 4 mm thick Al-2014 pressure hull.999 probability of no micrometeoroid penetration 4.7 margin of safety 6 mm thick bottom Reinforcement where stresses are above 164 MPA with 4mm thickness Max stress: 160 MPa

Habitable Module Specializations Science Specialized Living

Spectrometers for geological analysis Basement Radiation shelter 1.

8m * BFO = Blood-Forming Organs * GCR = Galactic Cosmic Radiation

16 Habitable Module Specializations Science Specialized Living Specialized EVA airlocks Science equipment Life Science Rack Spectrometers for geological analysis Basement Radiation shelter 1.9m x 1.95m x 0.8m * BFO = Blood-Forming Organs * GCR = Galactic Cosmic Radiation * SPE = Solar Particle Event Serves as sleeping quarters Dosages at 5 cm BFO: 7.08 rem = GCR, 3 months rem = 1979 type SPE

17 Habitable Module Landing Gear Structural Component Applied Load Factor of Safety Safety Margin Failure Mode Stringers Cylindrical Part of Hull 510 MPa Compression Landing Leg - Primary Strut 984 MPa Buckling Landing Leg Secondary Strut 460 MPa Buckling Landing leg Foot Pad 238 MPa Bending Foot Pad Legs Expand For Landing Primary Strut Secondary Strut

Chassis Modules Ball joint rotates ± 45 4.

18 Chassis Modules Ball joint rotates ± m Avionics 100 kg Structural 350 kg Transit Connections 200 kg Drive System 650 kg Power Systems 90 kg Total 1390 kg Margin 63% Transit connection between modules:

19 Chassis Structural Analysis Aluminum 2014 max stress allowable = 230 MPa Transit connection stresses: 0.8 MPa 10,000N 10,000N Wheel landing stresses: 80 MPa

Robotic Manipulators: Remove descent engines

20 Power Module 4.5m Avionics 200 kg Structural 780 kg Drive System 630 kg Power Systems 240 kg Landing RCS 130 kg 2 Robotic Arms 150 kg Total 2130 kg Robotic Manipulators: Remove descent engines from modules Gather rock and soil samples Connect power and data cords Module maintenance

3 kwe Dynamic Isotope Power System (DIPS) Alternator Power Out Pu

21 Dynamic Isotope Power System Shadow Shield Radiator Surface Area = 7.7 m 2 Heat Source 5.3 kwe Dynamic Isotope Power System (DIPS) Alternator Power Out Pu 238 O 2 (95 kg) Radiator Lithium Hydride Shadow Shield 200 kg (.3 m 3 ) Stirling Cycle Engine (220 kg) *(Not to Scale)

22 MORPHLAB Communications 4 communication satellites in halo orbit 90 out of phase Utilize Deep Space Network to receive transmissions Moon NS Hab-Earth Moon NS Power-Earth Moon FS Hab-Halo Moon FS Pow-Halo Mod-Mod 20km range EVA-Mod 10km range Diameter 50 cm 10 cm 50 cm 10 cm Omni antenna Omni antenna Band Ka Ka Ka Ka UHF UHF Transmit 55 Mbps 10 Mbps 55 Mbps 10 Mbps 30 Mbps 1 Mbps Bit Rate Receive 33 Mbps 10 Mbps 33 Mbps 10 Mbps 10 Mbps 1 Mbps Bit Rate Output Power 1.2 W 4.0 W 4.0 W 11.4 W 15.0 W 1.8 W Link Margin 3.0 db 3.0 db 3.0 db 3.0 db 3.0 db 6.0 db NS Near Side FS Far Side Mod Module Hab Habitable Module Pow Power Module

23 Transit Phase Vehicle Assembly

24 Vehicle Assembly Systems Inter-module communications: Omni-directional UHF antennas Transfer rate of 10Mb/sec 40Mb/sec Module communication range of 10km radius Peak Power System: Habitable Module: 101 kg Li-Ion Bank Chassis: 44 kg Li-Ion Bank

25 Transit Power Budget Locomotion Thermal Control Avionics Total Vehicle Assembly System Average 3 kwe 1 kwe 1 kwe 5 kwe Locomotion Thermal Control Avionics Total Vehicle Assembly System Peak 4.2 kwe 1.2 kwe 1.3 kwe 6.7 kwe Generated Power DIPS 5.3 kwe Battery 1.5 kwe Total 6.8 kwe

26 Locomotion Power and Speed Component Chassis Power Module Vehicle Assembly Max Power/Wheel 375 W 300 W - Max Motion Power 1.5 kwe 1.2 kwe 4.2 kwe 0º - 16 º slope : 16 º - 30 º slope : Transit Speed km/h Transit Speed km/h

Trajectory & Obstacle Avoidance Earth based decisions Mapping satellites provide high resolution altitudes for initial trajectory Mission control monitors sensors to make trajectory modifications

27 Trajectory & Obstacle Avoidance Earth based decisions Mapping satellites provide high resolution altitudes for initial trajectory Mission control monitors sensors to make trajectory modifications Autonomous sensors on modules Real-time sensors on Power Module provide data <100m IMU - vehicle attitude relative to gravity vector Star tracker- position relative to stars during night Sun tracker- position relative to sun during day Onboard computer perform analysis on immediate travel path Altitude 5 km - Tycho 0 km - -5 km - Clavius Degrees longitude Moretus Maginus Degrees latitude

28 Base Assembly Phase

29 Docking Mechanism Pressurized tunnel extends to connect: Hinged outer door collapses into walkway: Inflatable Multilayer Kevlar Inflatable Plastic Pressure Bladder Sliding Inner Doors Hinged Outer Door (Folded)

30 Base Peak Power Net Battery Totals Mass: 870 kg Storage Capacity: 108 kwhr 24 Hour Discharge: 4.5 kwe

Base Power Generation/Budget Base System Average Crew Systems Avionics House Keeping Thermal Control Rover Recharge Science Total 6 kwe 2 kwe 1 kwe 2 kwe 0.5 kwe 3.

31 Base Power Generation/Budget Base System Average Crew Systems Avionics House Keeping Thermal Control Rover Recharge Science Total 6 kwe 2 kwe 1 kwe 2 kwe 0.5 kwe 3.5 kwe 15 kwe Base System Peak Crew Systems 8 kwe Avionics 3 kwe House Keeping 1 kwe Thermal Control 3 kwe Rover Recharge 1 kwe Science 4 kwe Total 20 kwe Generated Power DIPS* 15.9 kwe Battery 4.5 kwe Total 20.4 kwe *Output of 3 Power Modules

32 Crew Systems Design Constraints: All crew interfaces shall Accommodate the 95th percentile American male to the 5th percentile Japanese female Adhere to NASA STD-3000 Nominal mission consists of 4 member crew Capable of daily 2 person EVAs Zero pre-breathe time for EVAs For optimal performance on long duration missions Minimum surface area = 61 m 2 Min. ceiling clearance = 2.2 m Min. interior volume = 135 m 3 Emergency requirements 180 day subsistence food stock At least 2 IVA exits from each module EVA bailout options * IVA = Inter-Vehicular Activities

33 Cabin Layout & ECLSS Hab-Science Modules: 2 EVA areas Main airlocks, dust removal Repair area, tool storage Durable experimentation area 1 science workplace Finer specialized equipment Backup galley ECLSS systems Water Vapor Electrolysis Electrochemical Depolarized Cells Sabatier Trace Contaminant Control Hab-Living Modules: 1 galley Food preparation area Exercise area, lounge Backup quarters 2 sleeping quarters Sunken SPE-shielded beds Sanitary systems, main level ECLSS systems Vapor Phase Catalytic Ammonia Removal Multi-filtration Supercritical Waste Oxidation

34 Galley Habitable-Living Layout docking mechanism storage & exercise equipment table & 4 chairs stowage cabinets & counter sink radiation shelter doors storage toilet docking mechanism cabinets, microwave & counter refrigeration unit shower

35 Habitable-Living Layout *2 modules docking mechanism desk desk chair chair stowage stowage mirror toilet radiation shelter doors docking mechanism closet sink & cabinet shower closet

36 Habitable-Science Layout docking mechanism storage docking mechanism extendable work table & 4 chairs science rack 3 docking mechanism exercise equipment storage cabinet & counter sink refrigeration unit cabinets, microwave & counter

37 EVA Habitable-Science Layout *2 modules airlock pump storage EMU Store (2 suits) airlock science rack 2 storage desk chair docking mechanism lounge chair lounge chair docking mechanism EMU boxes & storage stowage (3) storage tv

38 Crew Schedule Guidelines: The crew may adjust the schedule to that day s science The following guidelines should be followed when adjusting daily schedule Crew members must eat at least once every 7 hours 2 hours delegated for exercise and recreation each day 8 hours of sleep a day EVA rotation: Two, two person teams will alternate daily EVAs Teams will alternate crew members every week Crew Activity Sample Crew Schedule: Daily schedule Crewmember Task Sleep Hygiene/Breakfast Daily Coordination EVA/Tasks Lunch EVA/Tasks Exercise & Recreation Dinner Hygiene Downtime Sleep

EVA Support 2 Collapsible Lunar Rovers Apollo LRV with

capability 208 kg mass; 490 kg payload Clear obstacles 30.

slopes Pitch and roll stability of ±45º Top speed 14 km/h I-

39 EVA Support 2 Collapsible Lunar Rovers Apollo LRV with modifications Rechargeable Li ion batteries Teleoperation capability 208 kg mass; 490 kg payload Clear obstacles 30.5 cm high; crevasses 70 cm wide Traverse 25 slopes; park on 35º slopes Pitch and roll stability of ±45º Top speed 14 km/h I- Suit 8 soft-bodied suits 80 kg weight with Portable Life Support System (PLSS) 25.7 kpa, 100% O 2 atmosphere Zero pre-breathe R value of 1.3 Waist entry High mobility spacesuits/ilc.html

40 Reliability NASA JSC requires reliability of 0.99 for crew return In order to evenly distribute the reliabilities for fail safe mode, each habitable system must have an overall reliability of and the power system must have an overall reliability of This requires each Living or Science module to have a reliability of 0.930, with each the Power module s reliability of All sub-systems will have to meet these reliability requirements MORPHLAB System Reliability = 0.99 R-Power Sys = R-Living Sys = R-Science Sys = R-Power R-Power R-Power R-Power R-Living R-Living R-Living R-S cience R-S cience R-S cience R-Power =0.989 R-Living = R-S cience = Fail Safe Mode

41 Cost Analysis Assumes: 40% reserve factor, 80% production learning curve Total Program Cost: $36.2 billion Project NASA Lunar Exploration Budget: $51.5 billion over 15 years

42 Summary Designed to fulfill the goals of the President s new space initiative Stepping stone for an Earth to Mars mission Design utilizes existing launch vehicle technologies Design has great advantages over a largescale stationary lunar base Inexpensive program

43 Public Outreach February 12, 2004 Trade Study Review An in-class presentation of our initial design considerations March 1, 2004 Preliminary Design Review 12 (UMD) alumni, faculty and staff attended a 3 hour presentation of our preliminary design April 19, 2004 Critical Design Review 30 UMD alumni, faculty, staff, NASA employees and representatives from major engineering companies attended a presentation on our finalized design April 24, 2004 Maryland Day 30,000 people from around the country come to UMD to learn all about the University during this annual event Poster presentation was set up at UMD s Space Systems Laboratory April 27, 2004 Departmental Seminar Presentation to Aerospace Engineering faculty

44 Acknowledgments Our advisors, Dr. Dave Akin and Dr. Mary Bowden, for their help and support All of the people who helped by giving us feedback at our Trade Study, Preliminary Design, and Critical Design Reviews Dr. Fourney and the s Aerospace Engineering Department USRA and NASA RASC for our participation in the RASC-AL program

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