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WELCOME TO CRITICAL DESIGN REVIEW
PROJECT LEGACY Project Manager: Trevor Jahn
Assistant Project Manager: Michael Young
PROJECT OVERVIEW
Photo Credit: (NASA, 2016) https://www.nasa.gov/content/journey-to-mars-overview
Lunar Base • 8 astronauts • Missions spanning
2 years • Investigate the
effects of long term crew mission
• Science Objectives • Technology
Readiness Levels (TRL)
• 2035 Crew to Mars Cycler Rendezvous
PROJECT LEGACY Solution
• 9 habs (Radiation Shielding)
• 2 autonomous/crewed rovers
• In-Situ Resource Utilization (ISRU)
• Fuel Depot
• 4 Science Probes
• 3 Science Rovers (Range of +1200 km)
• +3 Nuclear Reactors
• JPL’s ATHLETE and JVA
1
2 3
4 5
6
PROJECT LEGACY Solution
• 1 Impact vehicle
• 1 Ferrying Lander for crew of 8
• XM2 Space Habitat
• 3 Com Sats (24/7 HD coverage)
MISSION ARCHITECTURE Project Manager: Trevor Jahn
Assistant Project Manager: Michael Young
MISSION ARCHITECTURE
Washington Series (2021-2023, 4 missions)
Aka Testing and XM2 Phase
• Raising TRL of power/orbiters/science objectives
• XM2 Delivered to CLO
• Moon Impact Mission for habitat foundation
Adams Series (2023-2029, 12 missions)
Aka First Construction Phase
• Deliver crew to orbiter for shakedown
• Validate life-support systems, resources
• Landing first five habs, ISRU equipment, consumables, rovers
• Crew construction mission 1
Jefferson Series (2029-2031, 5 missions)
Aka Second Construction Phase
• Remaining four habs
• Crew construction mission 2
TIMELINE, MISSION COUNT
Madison Series (2032-2035, 11 missions)
Aka Crew and Resupply
• Personal items, consumables deliveries
• Crew delivery and rotation via Orion
capsule
Monroe Series (2035+)
• Crew to cycler rendezvous
• Crew rotation
WASHINGTON SERIES
2018-2020, 4 MISSIONS
Project Manager: Trevor Jahn
Assistant Project Manager: Michael Young
2018-2020 WASHINGTON 1-4
Washington (2018-2020, 4 missions)
• 2018 Mission 1: XM2
• 2019 Mission 2: Moon Impactor Mission Launch
• 2019 Mission 3: Orion Docking Mechanism, 3 Com Sats, Nuclear
Reactor Test 1 (TRL 7 – 8)
• 2020 Mission 4: Lander, 3 Science Rovers, Nuclear Reactor Test 2 (TRL
8 – 9), 4 Science Probes
2018 WASHINGTON 2: MOON IMPACTOR MISSION LAUNCH
Excavated Mass 5202 [Mg]
Excavated Volume
Mass of Impactors 2.925 [Mg]
Volume of Impactors
Dr. Aldrin’s habitat layout
Required Mass [Mg]
Required Volume
Crater Model
2019 WASHINGTON 3: XM2
10 Amit Soni
Purpose: A go between from Earth
and the Moon Base
Dimensions based on BA330
• Deployed Volume: ~338 m3
• Deployed Mass: TBD
• Power: TBD
Requirement: 24-hour HD video communication with crew throughout mission
Communication Satellite Specifications:
• Number of satellites: 3
• Orbit altitude: 1,200 km
• Period: 4 hours
• Inclination: 88 degrees (polar orbit)
• Relays data from Earth to Moon or from Moon to Earth
Control Characteristics: - 3 axis stabilization - Using 3 reaction wheels - Desaturate about once every half year - Thrusters are used for small
maneuver changes
2019 WASHINGTON 3: COM SATS
2020 WASHINGTON 4: CARGO LANDER - For the 20 Mg lander, the total DeltaV to land from our 4500 km orbiting radius will be 2.5
km/s.
- Both landers are powered by 1 Aerojet Rocketdyne RL10B-2 Engine.
- 20 Mg Lander is 10.5 meters tall 7 meters wide at the top and 14 meters wide at the struts
Variant LHy Vol. (m3)
LHy Mass (Mg)
LOx. Vol. (m3)
LOx. Mass (Mg)
5 Mg 8.31 0.589 3.03 3.465
20 Mg 33.29 2.357 12.15 13.860
Hab and Lander in SLS Fairing
Cargo Lander with Extended Struts
2020 WASHINGTON 4: SCIENCE TRACEABILITY MATRIX
Science Objective Justification Measurement Objective
Measurement Requirement
Instrument Selected
Constrain Bulk Composition of
the Moon
Constrain age of SPA and Late
Heavy Bombardment (LHB) theory
Sample return from SPA to
analyze mineralogy and
volatile distributions
Age SPA melt sheet within 20 My ppb level –
measure high FeO areas
Drill, Sample, NSS, SuperCam, hand
lens
Example of one row from the STM. Full STM encompasses 3 goals.
The South Pole-Aitken Basin (SPA) has high Iron Oxide levels (yellow) that we want to sample.
SPA Basin
2020 WASHINGTON 4: TRAVERSE MAP FOR SCIENCE ROVER
CABEUS CRATER TO SCHRÖDINGER BASIN = ~600 KM. TOTAL TRAVEL DISTANCE ~1200 KM
2020 WASHINGTON 4: SCIENCE PROBES
4 science probes sent to lunar surface for condition assessment
1 Launch from LEO to CLO using Falcon heavy
15
Science Instruments and Objectives: ● Determine inner structure of Moon ● Measure global heat flow ● Examine Moon’s magnetic field ● Seismic activity
Science Probe Overview:
Mass (kg) 149.6
Power (W) 157.6
Volume (m^3) 0.783
*Totals for one probe
2020 WASHINGTON 4: SCIENCE PROBES
16
ACS Requirements: • Accommodate Precision Landing • Efficient use of fuel
ACS: • Use variable thrust main engines • Use Control Moment Gyroscope
(CMG) system Overall Propulsion System: Aerojet Rocketdyne R-6D (x3)
Mass (kg) Volume (m^3)
Propulsion 89.54 0.069
Total 149.6 0.783
* for one probe
ADAMS SERIES
2021-2024, 10 MISSIONS
Project Manager: Trevor Jahn
Assistant Project Manager: Michael Young
2020-2025 ADAMS 1 – 12 Adams Series (2020-2025, 10 missions)
• 2020 Mission 1: Crew of 2 to XM2 (1 week duration), docking test, and return to Earth
• 2023 Mission 2: Modular Rover / Attachments, 3 reactors, and ATHLETE
• 2023 Mission 3: Hab 1L (Living, Hab 1)
• 2023 Mission 4: Hab 2L (Living, Hab 2)
• 2023 Mission 5: Hab 3R (Rec center, Hab 3)
• 2024 Mission 6: Hab 4R (Rec center, Hab 4)
• 2024 Mission 7: Hab 5W (Wast/Water, Hab 5)
• 2024 Mission 8: Ferrying Lander to Lunar Surface
• 2024 Mission 9: ISRU, 3 Reactors
• 2024 Mission 10: Fuel Depot
• 2024 Mission 11: Ferrying Lander to XM2
• 2025 Mission 12: Crew of 2 to XM2, and 2 Crew to Surface (1 week): test systems
LUNAR SURFACE LOCATIONS
Objective: Determine locations for Power
Structure Components
Reasoning: Navigational understanding and
General distance of separation
14.3 Km
ADAMS 2: NUCLEAR POWER SYSTEM
Reactor Electric Power (kWe) Thermal Power (kWt) Mass (Mg)
SAFE-400 100 400 0.541
Lifespan of 5-7 years Raising the TRL of the reactor • Washington-1 in 2018 will raise the TRL from
a 7 to an 8 • Washington-3 in 2019 will raise the TRL from
an 8 to a 9 Replacement missions every 5 years
SAFE 400 Nuclear Reactor
SAFE 400 Nuclear Reactor Interior
2023 ADAMS 2: UNIFIED ROVER SYSTEM Operation Parameter
Value
Max Speed 30 [kph]
Cross country Speed
20 [kph]
Range 200 [km]
Carrying Capacity
3.5 [Mg]
Science Bay: Volume: 17.08 [m3] Mass: 0.912 [Mg]
Fluid Storage Module: Volume: 3.80 [m3] Mass: 0.709 [Mg]
Rover Arms: Volume: 8.9x10-3 [m3] Mass: 0.021 [Mg/arm]
Scoop: Volume: 0.66 [m3] Mass: 1.987 [Mg/arm] Volume: 0.66 [m3]
2023 ADAMS 2: UNIFIED ROVER SYSTEM
Universal Pallets
JVA Bed
RADIATION SHIELDING
Fig.1: Habitat Radiation Mitigation Design. Cross section and top down views.
lower Inter-hab connector
Lunar ground
level Water Tank
Reg. bags
ground
storage
GCR SCR
RADIATION
Radiation Type Unmitigated Dose Dose after Mitigation
Top Sides
Galactic Cosmic Rays 0.75-1.0 Sv 0.0255 Sv 0.031 Sv
Solar Cosmic Rays 80-300 Sv 0.330 mSv 0.271 mSv
Total 81 – 301 Sv 0.0565 Sv
Table 2: Habitat radiation dosage. Comparison of the unmitigated and mitigated dosage from the most harmful sources of radiation (over 2 years).
Mass: 11,200 Mg Regolith, 8 Mg bags, 22440 kg of water necessary Volume: 7,450 m3 Total Dose: 0.0565 Sv over 2 years
2 major sources of radiation on the moon:
• Galactic Cosmic Rays [1 Sv]
• Solar Proton Events [~150 Sv]
Leveraging current technology of
JPL’s ATHLETE (All Terrain Hex-
Limbed Extra-Terrestrial Explorer)
and modifying to fit requirements.
Linking Points
Cargo Lifting Wheels
2023 ADAMS 2: NASA’S ATHLETE
2021 – 2023 ADAMS 3 – 7: HABS 1 – 5
Hab 3R (Rec Center, Hab 3) Wally ball/Multipurpose Court
Hab 4R (Rec Center, Hab 4) Exercise Equipment
Hab 1L (Living, Hab 1) Residential Areas
Hab 2L (Living, Hab 2) Residential Areas
Hab 5W (Waste/Water, Hab 5) Exercise Equipment
2024 ADAMS 8: ISRU SYSTEM
27
COMPONENT BOILING POINT 1 ATM [C]
H2O (Water) 100
CH3OH (Methanol) 66
OH (Hydroxide) 35
SO2 (Sulfur Dioxide) -10
NH3 (Amonia) -33.34
H2S (Hydrogen Sulfide) -60
CO2 (Carbon Dioxide) Boils at 5.2 atm and -78.5
C2H4 (Ethylene) -103.7
CH4 (Methane) -161.5
• Heats up regolith to sublimate out “ice material” • Cool gases to slowly separate components into
liquids • Expels waste regolith and “ice material” out of
the system • Holds important materials (CO2, CH4, H2O) to be
picked up by the fuel rover
Regolith tank
Mixture gas tank
CO2 tank H2O tank CH4 tank
Microwave
Vent lines
Vacuum pump
Solenoid valves
LCH4 Tank
LOX Tank
Reactants Tank GCH4
Tank
GCO2
Tank
LH2O Tank
1
2
3
4 5
6
- Heat Exchanger MLI Outer Shield
2024 ADAMS 9: FUEL DEPOT
Tube # Service
1 Liquid Water to LOX Tank
2 Gaseous Hydrogen to RT
3 Liquid Water to LH20 Tank
4 Gaseous Carbon Dioxide to Reactants Tank
5 Gaseous Methane to GCH4 Tank
6 Gaseous Methane to LCH4 Tank
Austin Black
Fuel Depot • Location: Partially shadowed region • Function: generates fuel/ox for reusable lander • Mass: 18.4 Mg (dry) • Power: 176.86 watts • Volume: 258 m^3
JEFFERSON SERIES
2024-2028, 5 MISSIONS
Project Manager: Trevor Jahn
Assistant Project Manager: Michael Young
2024-2028 JEFFERSON 1-5
Jefferson Series (2025-2027, 5 missions)
• 2025 Mission 1: Hab 6LL (Laboratory, Hab 6), Spacesuits, Laboratory
Supplies
• 2026 Mission 2: Hab 7M (Medical, Hab 7), Medical Hab Supplies
• 2026 Mission 3: Hab 8A (Aeroponics, Hab 8), Aeroponics equipment
• 2027 Mission 4: Hab 9F (Food Prep/Storage, Hab 9)
• 2027 Mission 5: Crew of 2 to XM2, and 2 Crew to Surface (1 week): test
systems
2025 – 2027 JEFFERSON 1 – 4: HABS 6 – 9
Hab 8A (Aeroponics, Hab 8) Aeroponics Facility
Hab 6LL (Laboratory, Hab 6) Science Lab
Hab 9F (Food Prep/Storage, Hab 9) Food Storage and Preperation
Hab 7M (Medical, Hab 7) Medical Research
MADISON SERIES
2028-2036, 7 MISSIONS
Project Manager: Trevor Jahn
Assistant Project Manager: Michael Young
2028-2035 MADISON 1-13: FOOD/WATER/PERSONAL
Madison Series (2028-2034, 19 missions) • 2028 Mission 1: Food and Water
• 2028 Mission 2: Personal Items, 4 humans, Orion Capsule, and Service Module
• 2029 Mission 3: Food and Water
• 2029 Mission 4: Personal Items, 4 humans, Orion Capsule, and Service Module
• 2030 Mission 5: Food and Water
• 2030 Mission 6: Madison 2 Crew Return to Earth
• 2030 Mission 7: Personal Items, 4 humans, Orion Capsule, and Service Module
• 2031 Mission 8: Food and Water
• 2031 Mission 9: Madison 4 Crew Return to Earth
• 2031 Mission 10: Personal Items, 4 humans, Orion Capsule, and Service Module
• 2032 Mission 11: Food and Water
• 2032 Mission 12: Madison 7 Crew Return to Earth
• 2032 Mission 13: Personal Items, 4 humans, Orion Capsule, and Service Module
• 2033 Mission 14: Food and Water
• 2033 Mission 15: Madison 11 Crew Return to Earth
• 2033 Mission 16: Personal Items, 4 humans, Orion Capsule, and Service Module
• 2034 Mission 17: Food and Water
• 2034 Mission 18: Madison 13 Crew Return to Earth
• 2034 Mission 19: Personal Items, 4 humans, Orion Capsule, and Service Module
MONROE SERIES
2035+
Project Manager: Trevor Jahn
Assistant Project Manager: Michael Young
2035 MONROE 1: FERRY TO CYCLER Objective: Design ferry to mars cycler to carry payload of 20Mg with safety option Reasoning: To make the hyperbolic rendezvous as safe as possible.
EUS, Exploration Upper Stage • Provide delta-v required to make
Hohmann transfer & initial stage of hyperbolic transfer
Booster • Provide delta-v required after EUS burn • Continue and finish hyperbolic transfer and perform approach maneuver
Service Module • Capable of doing same maneuver as
the Booster stage • Only used in Booster failure
Service Module • 20Mg, carries 4 crews • Has docking thruster and heat shield
FEMAC(Ferry to Mars Cycler) stage configuration:
2035 MONROE 1: FERRY TO CYCLER Maneuver breakdown:
1. EUS burn: Hohmann transfer to 1000 km altitude – 0.32 km/s
2. EUS burn: Transfer to high energy ellipse – 2.09km/s
3. EUS jettison
4. Booster Burn: Inject into hyperbolic departure orbit – 1.69 km/s
5. Booster Burn: Trajectory correction maneuver – 0.066 km/s
6. Booster and Service Module jettison
7. Ferry RCS burn: Rendezvous/dock with cycler – 0.0300 km/s
*Booster burn can be also done by service module in emergency case
Launch Vehicle SLS Block 2
IMLEO 175.34 Mg
IVLEO 1040 m^3
Total Delta-V from LEO
4.1941 km/s
Time of Flight 46.11 hr
Basic specification of the FEMAC Configuration allows us to achieve; • Crew Survival rate: 96.96% • Mission Success rate: 93.96% Abort Options • Safe return 0.7 hr (2039) to 2.4 hr (2035)
after insertion • Prevent escape 2.6 hr (2039) to 84 hr
(2035) after insertion
APPENDIX
Project Manager: Trevor Jahn
Assistant Project Manager: Michael Young
METHOD COMPARISON What is needed?
• Need to find the most efficient method to move regolith for hab construction
• Need a construction schedule to reflect the recommended method
Assumptions:
• Time numbers are assuming rover is constantly moving regolith or charging
• Full list of assumptions is located on slide 47
Rectangle Dig Only
Rectangle Impact
Aldrin Dig Only
Aldrin Impact
Mass (Mg) 3676.8 3468.4 3542.6 3634.3
Power Required (kW) 1857.0 1542.6 1789.2 1101.3
Volume (m^3) 2451.2 2312.3 2361.8 2422.9
Excavation Time (days) 291.36 222.20 283.91 176.46
Fill in Time (days) 117.18 117.18 109.72 65.833
Recommendation: We use the impactors with Dr. Aldrin’s layout
CONSTRUCTION SCHEDULE The Procedure
1. The impactors hit
2. Rovers fill in the craters to create pits
3. The first hab lands and is positioned in the pit closest to landing site
4. Rover fills in regolith around hab
5. First connector is positioned and attached
6. Regolith bag wall is built between pit and landing site
7. Repeat steps 3 – 5 for other two habs and connectors in cluster
8. Repeat steps 3 - 7 for the other 2 hab clusters
9. Position and attach the intermediate connectors
10.Create the remainder of the regolith bag wall
Figure 1: First Hab Cluster
Figure 2: Full Layout
BACKUP SLIDE
The rover:
• The ramps giving access to the pits all have an incline of 16°
• Volume of rover scoop: 0.66 m^3
• Power for a low work trip: 300 W
• Power for a high work trip: 500 W
• Battery charge time: 28.8 hrs
• Battery Life: 10000 W and 24 hrs
The habs:
• 7.4 m diameter
• Short connectors are 0.5 m long
• Habs are buried 2.7m
The Moon
• Regolith density: 1500 kg/m^3
• Rectangle crater is 32 x 32 x 3.11 m initially with 4 m long sloping walls
• Aldrin crater has diameter of 20 m that slopes into a diameter of 5 m over a depth of 4.17 m
LIST OF ASSUMPTIONS/GATHERED VALUES
Figure 4: One of Three Pits for Dr. Aldrin’s Hab Layout
Figure 3: Pit for Rectangular Hab Layout
APPENDIX: VEHICLE CONTROLS AFFECTING FORCES AND CONTROL METHODS
Vehicle Control Method Mass [Mg] Power [W] Volume [m3 ]
Ferrying Lander
CMG/Reaction Wheels
0.292 356 1.627
Ferry to Cycler
CMG 0.544 552 3.240
XM CMG/Thrusters 0.010 200 1.000
Environmental forces:
• Gravitational forces
• Reflected solar radiation
• Solar radiation
• Gravity gradient
• Particle collision forces
• Magnetic field force
Nonenvironmental forces
• Nonpropulsive mass expulsion force
• Damping and structural flexing
• Propulsive maneuvers
• Fuel sloshing
• Other non-environmental movement
APPENDIX: TRAJECTORY OVERVIEW
James Millane High Altitude Retrograde Orbit
Trans-Lunar Injection Orbit
Impactor Vehicle Separation and Trajectories
Moon’s Velocity
APPENDIX: VEHICLE MASS/VOLUME BREAKDOWN
IMPACTOR VEHICLE Quantity: 6
Payload Mass 0.65 Mg
Fuel Mass 0.7 Mg
Inert Mass 0.238 Mg
ISP 320 s
2.0 km/s
Unloaded Mass 0.938 Mg
Loaded Mass 1.588 Mg
Volume
TLI STAGE Quantity: 1
Payload Mass 9.53 Mg
Fuel Mass 3.67 Mg
Inert Mass 2.33 Mg
ISP 320 s
0.9688 km/s
Unloaded Mass 6.01 Mg
Loaded Mass 15.536 Mg
Volume
IMLEO: 15.6 Mg
APPENDIX: IMPACT TRAJECTORY
FINDER PROGRAM OUTPUT
James Millane
APPENDIX: IMPACTING MINING SITE
Jake Elliott
Recommendation: Mine/dig the mining site
Area under the impact site will heat to > 373 K
Assuming the first 2 meters is removed: • 9.424 m2 of floor is exposed • Next ~0.75 m is heated to > 373 K • Rocks are not melted, but volatiles will evaporate
Objective: Determine whether it is possible to excavate material from mining site Reasoning: We want to minimize digging by rovers
APPENDIX: IMPACTOR AND CRATER PARAMETERS
Jake Elliott
Individual Impactor Parameters
Number of impactors: 4
Mass: 975 kg
Density: 2700 kg m-3
Volume: 0.36 m-3
Velocity: 4600 m s-1
Impact angle: 40°
Individual Crater Properties
Diameter: 20.67m
Depth: 4.17 m
Volume: 1,156 m3
Total IMLEO: 12.104 Mg See Jay Millane’s slides from 2/25/16
APPENDIX: ISALE MATERIAL FILE #ISMAT ---------------------------------------------------------------- MATNAME Material name : crust__ : aluminu EOSNAME EOS name : miesand : aluminu EOSTYPE EOS type : tillo : tillo STRMOD Strength model : DRPR : ROCK DILMOD Dilatancy model : ALPHAPT : ALPHAPT DAMMOD Damage model : IVANOV : IVANOV ACFL Acoustic fluidisation : BLOCK : BLOCK PORMOD Porosity model : WUNNEMA : NONE THSOFT Thermal softening : OHNAKA : OHNAKA LDWEAK Low density weakening : POLY : POLY ------------------------------------------------------------------------------ POIS pois : 2.5000D-01 : 3.000D-01 ------------------------------------------------------------------------------ TMELT0 tmelt0 : 1.5130D+03 : 1.673D+03 CHEAT C_heat : 5.9000D+02 : 1.D+03 TFRAC tfrac : 1.2000D+00 : 1.2D+00 ASIMON a_simon : 1.8400D+09 : 6.D+09 CSIMON c_simon : 7.2700D+00 : 3.D+00 ------------------------------------------------------------------------------ YDAM0 ydam0 (ycoh) : 1.0000D+05 : 1.D+04 FRICDAM fricdam : 7.1000D-01 : 8.D-01 YLIMDAM ylimdam : 2.4700D+09 : 2.D+09 ---------------------------------------------------------------------------- YINT0 yint0 : 3.1900D+07 : 1.D+07 FRICINT fricint : 1.1000D+00 : 1.1D+00 YLIMINT ylimint : 2.4700D+09 : 2.5D+09 ------------------------------------------------------------------------------ IVANOV_A Damage parameter : 1.0000D-04 : 1.0000D-04 IVANOV_B Damage parameter : 1.0000D-11 : 1.0000D-11 IVANOV_C Damage parameter : 3.0000D+08 : 3.0000D+08 ------------------------------------------------------------------------------ GAMETA gam_eta : 2.0000D-02 : 8.D-03 GAMBETA gam_beta : 3.0000D+02 : 1.15D+02 ------------------------------------------------------------------------------ ALPHACRIT Zero dil angle distension : 1.2D0 : 1.2D0 DILATCOEF Max. dil angle : 0.0450 : 0.045D0 DILATPLIM Zero dil angle pressure : 2.0D8 : 2.0D8 DILATFRIC dam dist fric : 0.4D0 : 0.4D0 ------------------------------------------------------------------------------ ALPHA0 Initial porosity : 1.0730D+0 : 0.0000D+0 EPSE0 Elastic threshold : -1.0000D-2 : 0.0000D+0 ALPHAX Transition : 1.0898D+0 : 0.0000D+0 KAPPA Exp coefficient : 0.9800D+0 : 0.0000D+0 CHI Sound speed ratio : 1.0000D+0 : 0.0000D+0 ------------------------------------------------------------------------------- <<END
METHOD COMPARISON What is needed?
• Need to find the most efficient method to move regolith for hab construction
• Need a construction schedule to reflect the recommended method
Assumptions:
• Time numbers are assuming rover is constantly moving regolith or charging
• More assumptions are located in backup slide
Rectangle Dig Only
Rectangle Impact
Aldrin Dig Only
Aldrin Impact
Mass (Mg) 4638.8 4476.4 4347.3 4845.8
Power Required (kW) 2342.8 1960.4 2195.6 1468.4
Volume (m^3) 3092.6 2984.3 2898.2 3230.5
Excavation Time (days) 373.84 289.69 357.64 247.82
Fill in Time (days) 141.59 141.59 125.39 75.235
Recommendation: We use the impactors with Dr. Aldrin’s layout
Kyle Bush
Table 1: Comparison of Mass, Power, Volume and Time for Regolith Moving
CONSTRUCTION SCHEDULE The Procedure
1. The impactors hit
2. Rovers fill in the craters to create pits
3. The first hab lands and is positioned in
the pit closest to landing site
4. Rover fills in regolith around hab
5. First connector is positioned and
attached
6. Regolith bag wall is built between pit
and landing site
7. Repeat steps 3 – 5 for other two habs
and connectors in cluster
8. Repeat steps 3 - 7 for the other three
hab clusters
9. Position and attach the 3 long
connectors
10. Create the remainder of the regolith
bag wall
Kyle Bush
Figure 2: Full Layout
Figure 1: First Hab Cluster
BACKUP SLIDE
The rover:
• The ramps giving access to the pits all have an incline of 16°
• Volume of rover scoop: 0.66 m^3
• Power for a low work trip: 300 W
• Power for a high work trip: 500 W
• Battery charge time: 28.8 hrs
• Battery Life: 10000 W and 24 hrs
The habs:
• 7.4 m diameter
• Short connectors are 0.5 m long
• Habs are buried 2.7m
The Moon
• Regolith density: 1500 kg/m^3
• Rectangle crater is 40 x 32 x 3.11 m initially with 4 m long sloping walls
• Aldrin crater has diameter of 20 m that slopes into a diameter of 5 m over a depth of 4.17 m
LIST OF ASSUMPTIONS/GATHERED VALUES AND PIT DIMENSIONS
Kyle Bush
Dimensions of Excavated Pits
Figure 3: Pit for Rectangular Hab Layout
Figure 4: One of Four Pits for Dr. Aldrin’s Hab Layout
APPENDIX: NUCLEAR POWER ESTIMATES CHARGED SPHERES AS A POTENTIAL METHOD OF RADIATION SHIELDING
Power Estimates for Charged Spheres
• Chose a sphere radius of 1 m
• To charge 35 spheres we need 0.0131 kWh of energy
• 35 spheres would then take up a volume of 146.6077 m3
• Spheres must be 50 MV each
COMMUNICATIONS MAP EARTH – MOON SYSTEM
Objective: To create a communications map
Reasoning: To visually understand how the communication system will be positioned and operated
Chad Oetting
COMMUNICATIONS MAP MOON SYSTEM
Chad Oetting
BACKUP
Vehicle / Location Mass [kg] Power [W] Diameter [m]
Ferrying Lander 2.5 3 0.2019 0.0097
Cargo Lander 2.5 25 0.0875 0.1311
Ferry-Cycler 3 65 1.22 0.3897
ComSats (x3) 0.047 55 1.3125 0.0024
Pressurized Rover (UHF) 1 2 0.7698 0.6206
Pressurized Rover (HGA) 1 1 1.3125 1.804
Moon Base 4.7 Mg 100,000 9.4 110
Earth Base 4.7 (x2) Mg 100,000 9.4 110
Chad Oetting
APPENDIX: XM 2 DESIGN
• Dimensions based on BA330
• Deployed Volume: ~338 m3
• Deployed Mass: TBD
• Power: TBD
• Items Left to Determine
• Need material definition.
• Need to finalize XM shell.
• Need to work with
Power/Thermal and Human
Factors to define power
requirements.
BASED ON BIGELOW 330
55 Amit Soni
APPENDIX: XM SHELL STRESS ANALYSIS
• Major structural concern is the multi-layer inflatable shell.
• Loading conditions
• Interior pressurization
• Launch load
• Orbital Maneuvers
• Docking/undocking
• Solar radiation, etc.
• Need to determine shell layer composition.
• Systems Request: Payload Fairing Envelope
• 7.5m dia
• 14.03m length
• Usable volume : 620m3
* SolidWorks models by Amit Soni
56 Amit Soni
APPENDIX: XM-2 DIMENSIONS
57 Amit Soni
* SolidWorks drawing by Amit Soni. All dimensions in meters.
APPENDIX: STRESS ANALYSIS SETUP PROOF OF CONCEPT
• Internal Pressure Model: 101.325 kPa
• Gravity Load: 6 G’s
• Proof of concept modeled with 30 plys of Kevlar 29, oriented at 0°, 45°, 90°, -45° for isotropic properties.
• Only outer shell analyzed.
58 Amit Soni
* SolidWorks FEA model by Amit Soni
APPENDIX: CARGO LANDER
-10 and 20 Mg cargo landers are both powered by RL10B-2 Hydrolox Engines
-20 Mg lander and payload has a total mass of 45 Mg: 3.3 Mg inert mass, 20 Mg payload,
and 21.7 Mg of propellant. The volume of the fuel tank is 44.55 cubic meters while the
volume of the oxidizer tank is 16.25 cubic meters.
-The 10 Mg lander and payload has a total mass of 25 Mg: 2.9 Mg inert mass, 10 Mg
payload, and 12.1 Mg of propellant. The volume of the fuel tank is 24.84 cubic meters
while the volume of the oxidizer tank is 9.06 cubic meters.
- For the 20 Mg lander, the landing struts require an outer radius of 0.15m, an inner radius
of 0.13m, a total strut mass of 112.6 kg, and a volume of 1.2 m^3
- For the 10 Mg lander, the landing struts require an outer radius of 0.15m, an inner radius
of 0.145m, a total strut mass of 29.6 kg, and a volume of 1.2 m^3
- For the 20 Mg lander, the total DeltaV to land from our 4500 km orbiting radius will be
2.8031 km/s. This will include a 0.2761 km/s Descent Orbit Insertion, a 2.183 km/s
Braking and Rotation phase, and a .344 km/s Vertical Descent phase.
APPENDIX: UNIFIED ROVER SYSTEM FOR ASTRONAUTS
Operation Paramete
r
Value
Max Speed
30 [kph]
Cross country Speed
20 [kph]
Range 200 [km]
Height 2.765 [m]
Length 6.9 [m]
Width 2.6 [m]
Carrying Capacity
3.5 [Mg]
Ariel Dimston
APPENDIX: SCIENCE ROVER ARM DESIGN • Powered by geared motors motors for movement.
• 6 degrees of freedom
• 1.8 m fully extended
• Attachment barrel for multiple science tools
• Camera, drill, scoop, claw, etc.
• Can attach to multiple attachment points on rover with electrical access.
*Science Arms CAD designs by Amit Soni
Amit Soni
Shoulder
Attachment Barrel
Arm
Wrist
Geared motor
(x4)
Part Material Qty. Mass (kg) Volume (m3)
Shoulder Al 2090 1 6.72 2.59*10-3
Arm Zoltek™ PX 35 2 7.25 4.01*10-3
Wrist Zoltek™ PX 35 1 0.45 2.46*10-4
Barrel Al 2090 1 2.64 1.02*10-3
Geared Motor ---- 4 2 7.32*10-4
Holder Al 2090 1 0.4 1.59*10-4
Holder Motor ---- 1 1 1.12*10-4
Bolts A286 Steel 4 0.72 1.0*10-4
Mass: 0.021 Mg/arm
Volume: 8.9x10-3 m3
Power: 10W
Recommendation: Scale up science arm design for industrial applications.
ROVER ATTACHMENTS
OTHER ATTACHMENTS PLANNED: SCOOP SHOVEL, MINING IMPLEMENT, BULLDOZER BLADE
Benjamin Mishler
Fluid Storage Module: Tank Volume: 3.80 [m3] Tank Mass: 0.709 [Mg]
Science Bay: Volume: 17.08 [m3] Mass: 0.912 [Mg]
APPENDIX: FERRYING LANDER MISSION PARAMETERS
Maneuver ΔV (km/s) Number Required
Takeoff 1.962 1
Circularizing Burn to Enter CLO
0.231 1
15o Plane Change 0.271 2
Descent Hohmann and Landing
2.459 1
Total 5.194
Component TOF
Takeoff 6.7 min
Hohmann to CLO 2 hours, 19 min
Hohmann from CLO 2 hours, 19 min
Landing 13 min
Total 4 hours, 58 min
Purpose: To carry crew members between the Lunar Surface and the XM-2 module orbiting in CLO. To fulfill its mission it must be able to perform the following maneuvers.
RISK TOP MISSION RISKS
Risk Risk Ranks
Launch Failure 1
Radiation 2
Hyperbolic Rendezvous
3
Communications Failure
4
Pressurized Rover Failure
5
ISRU Failure 6
Fuel Depot Failure 7
XM Failure 8
Crewed Lander Failure
9
1 2 3
4 5 6 7 8 9
LUNAR VEHICLE SUMMARY 5 Mg Lander
20 Mg Lander
5 Mg Ferry
Vehicle 5 Mg Lander Descent
20 Mg Lander Descent
5 Mg Ferry Ascent Phase
5 Mg Ferry Descent Phase
Payload 5 Mg 20 Mg 5 Mg 5 Mg
Delta-V 2.5 km/s 2.5 km/s 2.5 km/s 2.5 km/s
Prop Mass 3833 – 4054 kg
15335 – 16218 kg
7161 – 8527 kg 4122 – 4908 kg
Initial Mass
9035 – 9555 kg
36142 – 38222 kg
16878 – 20097 kg
9717 – 11570 kg
Launch Vehicle
Falcon Heavy
SLS Block 1B SLS Block 1B SLS Block 1B
Surface
XM-2 Orbit r=4500 km
• Mass Ranges are for Inert Mass Fraction from .05 to .11 • All Lunar Vehicles powered by Aerojet Rocketdyne RL10B-2 Engine
20 MG CARGO LANDER • 20 Mg Cargo Lander launched atop the SLS Block
1B within the 8 meter Payload Fairing
• Used primarily to land the habs on the surface of the moon
• Powered by RL10B-2 Engine, ISP of 464 sec
• Even designed at the historically largest Inert Mass Fraction the Cargo Lander is able to land 20 Mg on the surface while still fitting within the 41 Mg to CLO limit of the SLS Block 1B EUS
• The images on the right are of the Cargo Lander designed at an Inert Mass Fraction of .11
Habs and Lander in SLS Fairing
Cargo Lander with Extended Struts
Inert Mass Fraction .05 .11
Payload [Mg] 20 20
Inert Mass [Mg] 0.807 2.004
Initial Mass [Mg] 36.142 38.222
Prop Mass [Mg] 15.335 16.218
LHy [Mg] 2.228 2.357
LOX [Mg] 13.106 13.860