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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)

Design a proving ground mission for a lunar base which functions to understand the effects of long term crewed missions, to achieve science objectives and to advance technologies for the eventual

establishment of a crewed Mars base.

PROJECT LEGACY Project Specifications – Lunar Surface

• 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

PROJECT LEGACY Project Specifications – Lunar Orbit

• 1 Impact vehicle

• 2 Ferrying Landers for crew of 8

• XM2 Space Habitat

• 3 Com Sats (24/7 HD coverage)

MISSION ARCHITECTURE Project Manager: Trevor Jahn


MISSION ARCHITECTURE

Washington Series (2022-2023, 4 missions)

Testing and XM2 Phase

• Raising TRL of power/orbiters

• XM2 Delivered to CLO

• Moon Impact Mission for habitat foundation

Adams Series (2023-2029, 12 missions)

First Construction Phase

• Deliver crew to orbiter for shakedown

• Validate life-support systems and resources

• Landing first five habs, ISRU equipment, consumables, rovers

• Crew construction mission 1

Jefferson Series (2029-2031, 5 missions)

Second Construction Phase

• Landing remaining four habs

• Crew construction mission 2

TIMELINE, MISSION COUNT

Madison Series (2032-2035, 11 missions)

Crew and Resupply

• Deliver personal items and consumables

• Crew delivery and rotation via Orion

capsule

Monroe Series (2035+)

• Crew to cycler rendezvous

• Crew rotation

WASHINGTON SERIES

2022-2023, 4 MISSIONS

Project Manager: Trevor Jahn


2022-2023 WASHINGTON 1-4 Washington (2022-2023, 4 missions)

• 2022 Mission 1: Moon Impactor Mission Launch

• 2022 Mission 2: 3 Com Sats

• 2023 Mission 3: XM2 Space Hab, Orion Docking Mechanism, Nuclear

Reactor Test 1 (TRL 7 – 8)

• 2020 Mission 4: 3 Science Rovers, Nuclear Reactor Test 2 (TRL 8 – 9), 4

Science Probes

2022 WASHINGTON 1: MOON IMPACTOR MISSION LAUNCH

Crater Model

Excavated Mass 5202 [Mg]

Excavated Volume

Mass of Impactors 2.925 [Mg]

Volume of Impactors

Dr. Aldrin’s habitat layout

Dr. Aldrin Habitat Layout

Required Mass 12210 [Mg]

Required Volume

Crater Model

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

2022 WASHINGTON 2: COM SATS

2023 WASHINGTON 3: XM2

Purpose: A go-between from Earth

and the Moon Base

Dimensions based on Bigelow

Aerospace B330:

• Deployed Volume: 330 m3

• Deployed Mass: 20 Mg

• Power: TBD

• Lifespan: 20 years

2023 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

2023 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

2023 WASHINGTON 4: TRAVERSE MAP FOR SCIENCE ROVER CABEUS CRATER TO SCHRÖDINGER BASIN = ~600 KM. TOTAL TRAVEL DISTANCE ~1200 KM

2023 WASHINGTON 4: SCIENCE PROBES

4 science probes sent to lunar surface for condition assessment

1 Launch from LEO to CLO using Falcon heavy

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

2023 WASHINGTON 4: SCIENCE PROBES 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

2023-2029, 12 MISSIONS



2023-2029 ADAMS 1 – 12 Adams Series (2023-2029, 12 missions)

• 2023 Mission 1: Crew of 2 to XM2 (1 week duration), docking test, and return to Earth

• 2025 Mission 2: Modular Rover / Attachments, 2 reactors, and ATHLETE

• 2025 Mission 3: Hab 1L (Living)

• 2026 Mission 4: Hab 2L (Living)

• 2026 Mission 5: Fuel Depot

• 2027 Mission 6: ISRU, 2 Reactors

• 2027 Mission 7: Hab 3R (Rec center)

• 2027 Mission 8: Hab 4R (Rec center)

• 2028 Mission 9: Hab 5W (Wast/Water)

• 2028 Mission 10: Ferrying Lander to XM2

• 2028 Mission 11: Ferrying Lander to lunar surface

• 2029 Mission 12: Crew of 2 to XM2, and 2 Crew to Surface (1 week): test systems

LUNAR SURFACE LOCATIONS

14.3 Km

2025 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

2025 ADAMS 2: UNIFIED ROVER SYSTEM Operation Parameter

Value

Max Speed 30 [km/h]

Cross country Speed

20 [km/h]

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]

2025 ADAMS 2: UNIFIED ROVER SYSTEM

Universal Pallets

JVA Bed

JVA-01: Volume: 14 [m3] Mass: 1.2 [Mg] Power: 390 [W]

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]

RADIATION SHIELDING

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

REGOLITH BAGGING

Fill Process: 1) Roll bag

2) Catch opening

3) Fill

4) Cut perforations

5) Cinch

6) Drop

This system is one

of our rover pallets

which can moved

on/off our rover.

Bag Spool

Fill Tube

Spring loaded hook

[1]

[3]

[6] [5]

[4]

Leveraging current technology of

JPL’s ATHLETE (All Terrain Hex-

Limbed Extra-Terrestrial Explorer)

and modifying to fit requirements.

Linking Points

Cargo Lifting Wheels

2025 ADAMS 2: NASA’S ATHLETE

2025 – 2027 ADAMS 3 – 9: HABS 1 – 5

Hab 3R (Rec Center) Wally ball/Multipurpose Court

Hab 4R (Rec Center) Exercise Equipment

Hab 1L (Living) Residential Areas

Hab 2L (Living) Residential Areas

Hab 5W (Waste/Water) Water Reclamation

2026 ADAMS 5: FUEL DEPOT

• Location: PSR At mining site • Function: Processes water

into fuel/oxidizer • Mass (dry): 16.64Mg • Power: 300 Watts • Volume: 313.9m^3

LOX

Tank

LH2

Tank

H2O Tank

Heat

Exchanger

MLI

Insulation

Aluminum

Support 1

5

4

3 2

Tube # Service

1 Liquid Water to H2O

Tank

2 Gaseous Hydrogen to

LH2 Tank

3 Liquid Hydrogen output

line

4 Gaseous Oxygen to LOX

Tank

5 Liquid Oxygen output

line

2027 ADAMS 6: ISRU SYSTEM • 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

2027 ADAMS 6: ISRU CONCEPT PATENT INFO

• Edwin C. Ethridge ([email protected])

• William F. Kaukler ([email protected])

• Capable of sublimating 10cm of water per minute (2D application)

• We plan to modify and scale up this version

SYSTEM REQUIREMENTS

• Microwave

• Boring cylinder (auger)

• Cold trap (collection chamber)

CHANGES FROM PREVIOUS SYSTEM

• Doesn’t require moving regolith

• Doesn’t require vacuum pumps

• Only has 1 collection tank

• Doesn’t require any separation of the volatiles

• Decreases IMLEO

JEFFERSON SERIES

2029-2031, 5 MISSIONS



2029-2031 JEFFERSON 1-5 Jefferson Series (2029-2031, 5 missions)

• 2029 Mission 1: Hab 6LL (Laboratory), Spacesuits, Laboratory Supplies

• 2030 Mission 2: Hab 7M (Medical), Medical Hab Supplies

• 2030 Mission 3: Hab 8A (Aeroponics), Aeroponics equipment

• 2031 Mission 4: Hab 9F (Food Prep/Storage)

• 2031 Mission 5: Crew of 2 to XM2, and 2 Crew to Surface (1 week): test

systems

2029 – 2031 JEFFERSON 1 – 4: HABS 6 – 9

Hab 8A (Aeroponics) Aeroponics Facility

Hab 6LL (Laboratory) Science Lab

Hab 9F (Food Prep/Storage) Food Storage and Preperation

Hab 7M (Medical) Medical Research

MADISON SERIES

2032-2035, 11 MISSIONS



2032-2035 MADISON 1-11: FOOD/WATER/CREW

Madison Series (2032-2035, 11 missions)

• 2032 Mission 1: 2 Mg Food and 3 Mg Water

• 2032 Mission 2: 4 humans, Orion Capsule, and Service Module




• 2034 Mission 6: Madison 2 Crew Return to Earth



• 2035 Mission 9: 4.8 Mg Food and 5 Mg Water

• 2035 Mission 10: Madison 4 Crew Return to Earth

• 2035 Mission 11:Personal Items, 4 humans, Orion Capsule, and Service Module

MONROE SERIES

2035+



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



APPENDIX: JVA-01 DESIGN Objective: Design mechanism to attach and remove rover attachments

Reasoning: Shirt-sleeve pressurized environment and radiation exposure prevents astronauts from attaching and detaching the rover attachments

• Miniaturization and redesign of

ATHLETE (1/4th scale)

• Universal pallet design for ease of

addition and removal

• Pallet will attach to rover

• Slides on rail

• Universal pallet design for ease of

addition and removal

Detailed design for JVA bed:

* CAD design and concept art by Amit Soni

Universal Pallets

Part Material Mass (Mg) Volume (m3)

Slide Bar (x2) Al 2090 0.1023 3.542*10-2

Slant Torsion Bar (x2)

Al 2090 0.01872 3.542*10-2

Torsion Bar Al 2090 0.008320 2.879*10-3

Pallet Al 2090 0.4483 0.1551

Total ---- 0.5776 0.2289

JVA Bed

APPENDIX: 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

APPENDIX: 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

APPENDIX: CONSTRUCTION SCHEDULE

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

High Altitude Retrograde Orbit

Trans-Lunar Injection Orbit

Impactor Vehicle Separation and Trajectories

Moon’s Velocity

APPENDIX: VEHICLE MASS/VOLUME BREAKDOWN

IMPACTOR VEHICLE Quantity: 3

Payload Mass 0.975 Mg

Fuel Mass 1.220 Mg

Inert Mass 0.387 Mg

ISP 320 s

2.0 km/s

Unloaded Mass 1.362 Mg

Loaded Mass 2.582 Mg

Volume

TLI STAGE Quantity: 1

Payload Mass 7.747 Mg

Fuel Mass 5.500 Mg

Inert Mass 1.912 Mg

ISP 320 s

1.314 km/s

Unloaded Mass 9.659 Mg

Loaded Mass 14.71 Mg

Volume

IMLEO: 14.71 Mg

APPENDIX: IMPACT TRAJECTORY

FINDER PROGRAM OUTPUT

APPENDIX: IMPACTING MINING SITE

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

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

APPENDIX: 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

Table 1: Comparison of Mass, Power, Volume and Time for Regolith Moving

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

APPENDIX: COMMUNICATIONS MAP EARTH – MOON SYSTEM

Objective: To create a communications map

Reasoning: To visually understand how the communication system will be positioned and operated

APPENDIX: COMMUNICATIONS MAP MOON SYSTEM

APPENDIX: COMMUNICATIONS

Vehicle Antenna / Location Mass [Mg] Power [W] Diameter [m]

Ferrying Lander 0.003 25 0.1313

Cargo Lander 0.003 8 0.1875

Ferry-Cycler 0.003 65 1.22

ComSat (to Earth, x3) 0.047 55 1.3125

Comsat (to Moon, x3) 0.047 18 0.0438

Pressurized Rover (X-band) 0.001 2 0.7698

Pressurized Rover (HGA) 0.001 1 1.3125

Moon Base 1.500 25 3.00

Earth Base (x4) 4.700 100 9.4

XM2 0.047 50 0.0875

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]

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

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.

APPENDIX: ROVER ATTACHMENTS

OTHER ATTACHMENTS PLANNED: SCOOP SHOVEL, MINING IMPLEMENT, BULLDOZER BLADE

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.

APPENDIX: 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

APPENDIX: 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

APPENDIX: 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

APPENDIX: FERRYING LANDER PROPULSION PARAMETERS

Ferrying Lander Propulsion System

Propellant Choice Liquid Hydrogen Liquid Oxygen

Engine RL10B2

Payload Mass 5 Mg

Inert Mass 0.9-2.6 Mg

Hydrogen Mass 1.8-2.4Mg

Hydrogen Volume 25.6-33.2m3

LOX Mass 10.7-13.8Mg

LOX Volume 9.3-12.1 m3

Total Mass 18.4-23.8 Mg

# of Engines 1

OX PUMP FUEL PUMP

FUEL TURBINE OX TURBINE

BELL NOZZLE

APPENDIX: ISRU PATENT INFO

65

http://arc.aiaa.org/doi/pdf/10.2514/6.2012-801 https://patents.google.com/patent/US8357884B1/en

http://arc.aiaa.org/doi/pdf/10.2514/6.2012-801




https://patents.google.com/patent/US8357884B1/en



66









FIG. 1 illustrates a side view of an

exemplary embodiment of volatile

extraction and collection device 100 for

extraction of volatiles from soil using

microwaves. In the embodiment shown,

volatile extraction and collection

device 100 is comprised of microwave

source 10, microwave delivery

component 20, collection chamber 30,

boring component 50, and wave dipole

antenna 45.

67








APPENDIX: LUNAR BASE POWER CONSUMPTION

At the beginning of the Madison series, steady operation of the lunar base will require a total of 154 kW.

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