APPENDIX TABLE OF CONTENTS - College of … TABLE OF CONTENTS ... Volume (m^3) 2451.2 2312.3 2361.8...

APPENDIX TABLE OF CONTENTS • Communication and Controls

• Exploration Module – XM2

• Fuel Depot

• Habitats

• In-Situ Resource Utilization

• Impactors

• Life Support System

• Power and Thermodynamics

• Permanently Shadowed Region - PSR

• Mission Design

• Mission Timeline

• Radiation

• Regolith Bagging

• Rovers

• Science Objectives

• Science Rovers

• Systems Trade Studies

1

IMPACTORS

2

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APPENDIX: MOON IMPACTOR MISSION LAUNCH

Crater Model

Excavated Mass 4800 [Mg]

Excavated Volume

Mass of Impactors 2.900 [Mg]

Volume of Impactors

Dr. Aldrin’s habitat layout

Dr. Aldrin Habitat Layout

Required Mass 4300 [Mg]

Required Volume

Crater Model

3

APPENDIX: TRAJECTORY OVERVIEW

High Altitude Retrograde Orbit

Trans-Lunar Injection Orbit

Impactor Vehicle Separation and Trajectories

Moon’s Velocity

4

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 5

APPENDIX: IMPACT TRAJECTORY

FINDER PROGRAM OUTPUT

6

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

7

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

8

APPENDIX: IMPACTOR ASSUMPTIONS

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

Figure 2: One of Three Pits for Dr. Aldrin’s Hab Layout

Figure 1: Pit for Rectangular Hab Layout

APPENDIX: CONSTRUCTION PROCEDURE The Procedure

1. The impactors hit

2. Rovers fill in the craters to create

pits

3. Hab 1L 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 walls are built

immediately after habs 1L, 3R and

6LL land

7. Repeat steps 3 – 5 for the remaining

habs as per the order in Figure 2

8. Fill in ramps as clusters are

completed

9. Attach cluster connectors between

habs 5W, 7M and 8A

Figure 1: First Hab Cluster in Pit

Figure 2: Full Layout with Placement Order

APPENDIX: IMPACTORS VS DIGGING What was needed?

• Needed to find the most efficient method to move regolith for hab construction

Assumptions:

• Time numbers assumed rover is constantly moving regolith or charging

• Time numbers assumed only one rover is working

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

Table 1: Method Effort Comparison Table

RADIATION

12


APPENDIX: 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]

13

APPENDIX: RADIATION SHIELDING

14

Habs GCR 73%

Habs SPE 13%

Space Travel

8%

Rover 6%

2-YEAR MISSION RADIATION DOSE BREAKDOWN

APPENDIX: 2-YEAR MISSION RADIATION DOSE

750 Day Mission Breakdown: • 750 days at Lunar Base • 21 days of Rover time (min.) • 14 days of Space Travel

Total Dose: <0.358 Sv

Radiation Type Unmitigated Dose

Dose after Mitigation

Galactic Cosmic Rays (GCRs)

0.75-1.0 Sv 0.312 Sv

Solar Particle Events (SPEs)

80-300 Sv 0.0458 Sv

Total 81 – 301 Sv 0.358 Sv

15

ROVERS

16


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] 17

2025 ADAMS 2: UNIFIED ROVER SYSTEM

Universal Pallets

JVA Bed

18 – Austin Black

Scoop

Volume: 0.5 [m3/scoop]

Mass: 1.987 [Mg/arm]

JVA-01

Volume: 14 [m3]

Mass: 1.2 [Mg]

Power: 390 [W]

Extended configuration Collapsed configuration

2025 ADAMS 2: UNIFIED ROVER SYSTEM

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

19

APPENDIX: SUSPENSION SYSTEM

Fig. 3: Coil-Over Shock Attached to Axle and Frame

Specification Value

Travel 152.4 [mm]

Spring Rate 347.410 [N/mm]

Motion Ratio 1:0.75

Shock Type Coil-Over

Fig. 4: Rear View of Rover Showing Ground Clearance Fig. 5: Rover Chassis

Specification Value

Travel 152.4 [mm]

Spring Rate 347.41 [N/mm]

Motion Ratio 1:0.75

Shock Type Coil-Over


AXLE DESIGN AND FEA


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.

23

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]

24

Leveraging current technology of

JPL’s ATHLETE (All Terrain Hex-

Limbed Extra-Terrestrial Explorer)

and modifying to fit requirements.

Linking Points

Cargo Lifting Wheels

APPENDIX: NASA’S ATHLETE

25

POWER AND THERMODYNAMICS

26


APPENDIX: BASE POWER CONSUMPTION

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

Rachel Lucas

Mission Name

Year Description

Washington 3

2023 Raise TRL from 7 to 8

Washington 4

2023 Raise TRL from 8 to 9

Adams 2 2025 Delivery of two nuclear reactors for base usage

Adams 11 2028 Delivery of one replacement reactor for the base

Interior of SAFE-400 Reactor

APPENDIX: NUCLEAR POWER SYSTEM

Total Mass: 1.08 Mg Total Power: 200 kWe, 800 kWt,

Total Volume: 0.24 m3

Working Fluid: Sodium Distance from Base: 1.1 km

Fuel: Uranium Nitrate Lifetime: 5-7 years

Radiator: Potassium Heat Pipe

APPENDIX: THERMAL CONTROL SYSTEM

R11

Ammonia Q

Heat Pump, Rankine Cycle

W

MOON

RADIATOR ARRAY

HABS

COMPRESSOR

HEAT EXCHANGER

Active Thermal Control System

Passive Thermal Control System

Insulation Layers Thickness (cm)

MLI 10 2

TOTAL MASS: 1.471 Mg

APPENDIX: THERMAL SYSTEM OVERVIEW

Project Legacy • Insulation

• MLI (aluminized Mylar) • Power Requirement: 154 kW • Coolant: Ammonia, R11

• 1 acquisition coolant loop • R11 outer loop (greater

pumping power) • Radiated Heat: 250 kW/m2

• Radiator • 200 m2

• Fixed, vertically oriented • Thermal louvers

ISS • Insulation

• MLI (aluminized Mylar) • Power Requirement: 75-90 kW • Coolant: Ammonia

• 2 loops (two-temperature loops) • Radiated Heat: 275 kW/m2

• Radiator • 154 m2

• Rotate to reject maximum heat

APPENDIX: THERMAL SYSTEM System Mass

(Mg)

Compressor 0.01645

Evaporator 0.247

Pipes and Fluid 0.174

Radiator Array 0.5001

Heat Exchanger (Cold Plates, Fluid, Piping)

0.432

Properties Mass (Mg)

Fin Efficiency 0.8

Rejection Loop T [K]

362

Coolant Loop T [K] 275

APPENDIX: THERMAL SYSTEM

Figures: NASA, ATCS

APPENDIX: POSSIBLE NUCLEAR RISKS

Nuclear Meltdown

• Occurs when a reactor is improperly cooled

• Constant supervision of the reactors is recommended as they haven’t

been tested in a lunar environment previously

• Regular checks of reactor components should be made

Radiation Shielding

• Reactor produces enough radiation that it could be dangerous and

possibly fatal to nearby inhabitants

• It is therefore recommended that the reactor be a distance of at least 1.1

km from the base

Orbital Failure

• Danger lies in the possibility of nuclear fuel being dispersed throughout

a planet’s atmosphere

Rachel Lucas

EXPLORATION MODULE - XM2

34


APPENDIX: SCIENCE INSTRUMENTS ON XM2 Objective: Put science instruments on the XM2 to take science measurements from orbit

Reasoning: To optimize every opportunity we have to do science

• Gamma Ray Spectrometer – to measure abundance of certain elements on surface, including hydrogen, silicon, iron, potassium, thorium, and chlorine

• Infrared Spectrometer – good for finding geologically interesting minerals, such as carbonates, silicates, hydroxides, sulfates, hydrothermal silica, oxides and phosphates

• Magnetometer – measure the magnetosphere and the Moons magnetic field, which can tell us about the interior of the Moon

• Radiation Detector – detects harmful radiation from the Sun and outer space • Imaging Camera – captures detailed images of surface

Mass (Mg) Power (W) Volume (m3)

0.0571 65.1 0.21

PERMANENTLY SHADOWED REGION - PSR

36


APPENDIX: LAUNCHING FROM THE PSR Objective: Need to know if launching from the PSR is feasible

Reasoning: Launch pad may need to be moved from PSR

37

Look at Challenger Failure:

• Primary O-ring failure caused by

low temperatures at Launch

•Hardened O-ring didn’t form

proper seal because it wasn’t

rated for launch conditions

Recommendation:

• Use components rated for launch

conditions

• Vacuum

• Tamb = 50 K

• OmniSeal Raco

•Rated for 6 K and vacuum

pressures (excellent for

cryogenics)

Installed O-Ring O-Ring Failure

REGOLITH BAGGING

38


REGOLITH BAGGING

39 – Austin Black

Bag Spool

Fill Tube

Spring loaded hook

Regolith scoop

Bagging Process

1. Roll bag

2. Scoop regolith

3. Catch opening

4. Fill trough

5. Cut perforations

6. Cinch

7. Drop

This system is one of our rover pallets which can be moved on/off our rover.

APPENDIX: REGOLITH BAGGING

APPENDIX: REGOLITH BAGGING

Objective: Design a machine to fill bags with lunar regolith

Spools • Approximately 1 Mg/spool • 1030 bags/spool • 17 spools needed Bags • Holds 0.4 m3/bag • ~17500 bags needed • ~600 kg filled

Bags will placed on the sides and tops of the habs

APPENDIX: STORING BAG SPOOLS

Motivation:

Store bag spools inside habs. Not requiring additional cargo landings – minimizing IMLEO.

Unused volume and mass still available in certain habs.

No. of Spools 23

Spool Diameter 1.7 m

Spool Length 0.8 m

Spool Mass 1 Mg

Bags Per Spool 750

Spool Volume 7.26 m3 Carbon based fabric bags

HABITATS

42


APPENDIX: HABITAT MODULES

Hab number Hab type Total mass,

Mg

Power,

kW

1L Living quarters 1 16.14 6.44

2L Living quarters 2 16.14 6.44

3R Recreation 14.10 4.64

4R Exercise 15.80 5.16

5W Waste/water management 18.91 13.15

6LL Laboratory/work station 16.58 9.12

7M Medical bay 16.99 9.79

8A Aeroponics 18.09 8.87

9F Food preparation/storage 19.25 12.64

Airlock

44

Hab 1L (Living) Residential Areas

Hab 2L (Living) Residential Areas

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

Hab 4R (Rec Center) Exercise Equipment

Hab 5W (Waste/Water) Water Reclamation



45

Hab 6LL (Laboratory) Laboratory Equipment

Hab 7M (Medical) Medical Bay

Hab 8A (Aeroponics) Food Production

Hab 9F (Food Storage) Food Storage and Preparation

APPENDIX: HAB 1L & 2L: LIVING QUARTERS

APPENDIX: HAB 3R: MULTIPURPOSE

COURT

APPENDIX: HAB 4R: RECREATION

APPENDIX: HAB 5W: WASTE & WATER RECLAMATION

APPENDIX: HAB 6LL: LABORATORY STATION

APPENDIX: HAB 7M: MEDICAL BAY

APPENDIX: HAB 8A: AEROPONICS

APPENDIX: HAB 9F: FOOD STORAGE

APPENDIX: STEADY STATE OPERATIONS 2032: First Crew to Lunar Surface 40.6 Mg water, 5.35 Mg packaged food already on base 2033: Resupply mission 3 Mg water, 2 Mg food 2034: Resupply mission 3 Mg water, 2 Mg food 2035: Resupply mission 3 Mg water, 2 Mg food 4.8 Mg water First crew to cycler

Week 64, Day 3

Time Time

08:00 Wake up 16:00

Rover excursion

08:30 Breakfast

16:30

09:00 17:00

09:30

Medical test

17:30

10:00 18:00

10:30 18:30

11:00 Wallyball game

19:00

11:30 19:30 Dinner

12:00 Rest/free time

20:00

12:30 20:30 Priority task

13:00 Lunch

21:00

13:30 21:30 Exercise program

14:00

Rest

22:00

14:30 22:30 Personal time

15:00 23:00

15:30 23:30 Sleep

APPENDIX: CREW SELECTION AND MENTAL HEALTH Crew screening, selection, composition

• Height: 60-72 in.

• Blood Pressure: 140/90

• Visual acuity: 20/100

• Degrees: medical, engineering, science

Risk Mitigation and Support

• Autonomy for crewmembers

• Delegate tasks

• Goal-oriented, meaningful work

• Rotation of leadership

• Uplink of news, media, email

• Psychological conferences

• Private Earth contact

Sleep and Circadian Rhythms

• Strict work-rest schedule

• NASA developed LED light systems

• Rest during day, long sleep at night

LIFE SUPPORT SYSTEM

56


APPENDIX: WATER PRODUCTION COST SAVINGS ANALYSIS

Recommendation: After mission reaches steady state, stop shipping H2O and make all

H2O in-situ (less IMLEO and cheaper)

Limitations:

• Capacity of rover to supply 2 ISRU units

• Radiation contamination of ice deposits

• ISRU TRL low until later in mission (start-up time)

• Assume no need for additional power generation

Water production costs Shipped

(Mg) Shipped one-

time (Mg) Cost/yr % Savings

Ship all H2O but prop 49.9 16 $ 313,825,476.19 0% Make all but drinking in situ 17.9 52 $ 332,873,095.24 -6%

Make all H2O in situ 0 52 $ 247,619,047.62 21%

Using cost of ~$4.76M per Mg to lunar surface (SLS cost per launch/launch capacity)

APPENDIX: HABS LIFE SUPPORT REQUIREMENTS OBJECTIVE: MASS AND VOLUME FOR WATER AND AIR

Component Mass Volume Losses

Water 42.0 Mg 42 m3 2.94 Mg/yr

O2 (in habs) 0.25Mg 826 m3 -

N2 (in habs) 3.12 Mg 3154 m3 -

O2 (stored) 1 Mg - -

N2 2 Mg -

-

Water storage

1.2m

7.2m

• 0.05 m away from hab Walls

• 48.8 m3 of volume

APPENDIX: ROVER LIFE SUPPORT OBJECTIVE: LIFE SUPPORT FOR ROVER

Use the same Air system as used in the habs

Total V = 22.65

Volume O2 = 4.76 m3

Volume N2 = 17.9 m3

Mass O2 = 1.43 kg

Mass N2 = 17.7 kg

Life support system

Mass: 853 kg

Volume = 2.21 m3

Power = 4,195 We

CAD credit: Ariel Dimston

At 1 atm, with normal sea level atmosphere composition: Partial Pressure of O2 = 0.21 atm Partial Pressure of N2 = 0.79 atm Vtotal = 3933 m3 Voxygen = (3933 m3 )(0.21) = 825.9m3 Vnitrogen = (3933 m3 )(0.79) = 3155m3

voxygen = (259.8N/kg.K)(273.15K)/(0.21*101325 Pa) = 3.34 m3/kg vnitrogen = (296.8/kg.K)(273.15K)/(.79*101325 Pa) = 1.0128m3/kg moxygen = (825.9m3)/(3.34m3/kg) = .25Mg mtotal =3.37Mg mnitrogen = (3155m3)/(1.0128m3/kg) = 3.12Mg

APPENDIX: LIFE SUPPORT SYSTEM MASS OF AIR IN HABS

Equation from Project Aldrin-Purdue p420

The mass of oxygen consumed mO2T = (mO2t*ncrew+mO2loss)*tduration

Where mO2T = Total mass of oxygen for time mO2u = Mass consumed by 1 person in a unit of time Ncrew = Number of people mO2loss = Losses due to leaks etc. Tduration = amount of time in the units defined by mO2u So for 8 people who consume 0.84 kg of oxygen a day (assume 0 loss)

mO2T|2 years= 4.9 Mg

Vgas

Vtotal=Pgas

Ptotal

v =RT

P

m =V

v

APPENDIX: LIFE SUPPORT SYSTEM

Rapid Activation of Biological

Wastewater Treatment Systems

•Uses inoculum (bacteria) to remove

organic material (95%), ammonium

(95%) and nitrates from waste water

•Bacteria can be freeze dried to have

back up stores incase of emergency

•Techport has a TRL 4 by Dec. 2015

•Based on the speed of development it

is reasonable this tech could be TRL 8

by the beginning of the project

ADVANCED TECHNOLOGY

Lyophilization

•Microwave Enhanced Freeze Drying

of Solid Waste

•Last info from November 2006,

however this is a well developed tech

and could be reasonably forecasted to

be ready for launch date.

•Will freeze dry all wastes to separate

solids and particulates

Recommendation:

Use both a waste freeze dry system and an inoculum based treatment system in the water system. See next slide for a system diagram showing how the system changes

(REFRESHER FROM BEFORE)

APPENDIX: LIFE SUPPORT SYSTEMS MODIFIED

Waste Water Tank

Liquid/Particulate Separator

Filtration

Volatile Removal

Urine Tank

Ion bed

Vapor Distillation &

G/L separation

Microbe Check Valve

Potable Water

Hygiene, Food, Thermal Waste Water

Venting Waste water

Human Waste

Clean water

BASE LINE WATER MANAGEMENT

Waste Water Tank

Biological Waste water

treatment

Lyophilizer

Urine Tank

Vapor Distillation &

G/L separation

Microbe Check Valve

Potable Water

Hygiene, Food, Thermal Waste Water

Venting

ADVANCED WATER MANAGEMENT

Volatiles

(REFRESHER FROM BEFORE)

APPENDIX: LIFE SUPPORT SYSTEMS

Component Mass (kg) Volume (m3) Power (We)

Liophilizer and Biological waste treatment 591.2 2.050 2,869

Urine/Waste Water Collection* 4.550 0.020 4.000

Urine, Hygiene & Potable Water & Brine Tanks 181.6 0.470 17.80

Microbial Check Valve 5.720 0.020 0.000

Process Controller 36.11 0.080 156.2

Water Quality Monitoring 14.07 0.040 4.720

Product Water Delivery 51.73 0.120 3.440

Potable Water Storage 595.5 0.440 20.74

Totals 1,480 kg 3.24 m3 3,076 We

TABLE 5. ADVANCED WATER MANAGEMENT SYSTEM MASS, VOLUME, POWER DETAILED

Kate Fowee

Assume 4 needed water systems and two backup systems

Mass: 5920kg** Volume: 12.96m3** Power: 12,300 We**

* ISS proven

Table based on Table 6.14 and 6.9 from Hanford (2005)

**Only 4 running units considered

APPENDIX: LIFE SUPPORT SYSTEMS

Component Mass (kg) Volume (m3) Power (We)

Atmosphere Pressure Control 119.4 0.260 70.50

Carbon Dioxide Removal 179.1 0.420 534.0

Oxygen generation 379.2 1.000 3,293

Gaseous Trace Contaminant Control 85.81 0.400 194.4

Atmosphere Composition Monitoring 54.30 0.090 103.5

Sample Delivery System 35.11 0.040 0.000

Nitrogen Storage (high pressure) * 1,029 0.920 0.000

Oxygen Storage (high pressure) * 300.2 0.150 0.000

Totals 2182 kg 3.280 m3 4,195 We

TABLE 2. ATMOSPHERE REGENERATION SYSTEM MASS, VOLUME, POWER DETAILED (ISS PROVEN)

ISS handles 3-6 people Scale for 16, with four possible living habs and 1 shared work hab (2 units) and 2 back up units– 8 units

Mass: 17,456kg Volume: 26.24m3 Power: 25,170We**

*Not iss proven **Only 6 running units considered

Table based on Table 6.9 from Hanford (2005)

SCIENCE OBJECTIVES

65


APPENDIX: STM OBJECTIVES

What we can learn with orbiter instruments

APPENDIX: 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 using our science rovers.

67

SCIENCE ROVERS

68


APPENDIX: SCIENCE ROVER

Objective: Determine specific measurements, length of stay at various

sampling sites in order to satisfy objectives in the STM.

Instrument

Model Accuracy/Limitation

Time of

Measurement Other Limitations

DAN 1wt% 1min 1 m

(DAN) 0.1 - 0.3 wt% 30 min <0.5 m (vertical

distribution)

RAD varies, largest is 7.3% statistical

accuracy

15 min, once

every hour

ChemCam 10% accuracy "rapid" 7 m

APXS 0.5% abundance 3 hr

CheMin 3% abundance, accuracy of 15%

of amount sampled 10 hr 0 ev - 25 keV

Recommendation:

• Spend approximately one day at each sample site, longer at Schrödinger


Schrödinger Basin

• Minimum traverse duration: 3 months

• Assuming constant 20 km/h

• 1 month to get there

• At least 1 month worth of stops

• 1 month to get back

• Assuming traveling through “night”

(powered by an RTG)

Past Schrödinger

• Crater rims to sample SPA melt sheet

• Does not necessarily need to return

Traverse map created by Ellen Czaplinski

Recommendation:

• Sample return from Schrödinger, then

send another rover on extended traverse

Traverse map created by Ellen Czaplinski

Returning Rover

• 600km to Schrödinger

• 30kg samples

Extended Mission Potential Sites

1. Antonaldi (~513km from

Schrödinger)

2. Bhabha

3. Bose

4. Apollo Basin

5. Finsen

6. Leibnitz


UPDATED SCIENCE INSTRUMENT LIST

Instrument Mass (kg) Power (W) Volume (m3)

DAN 2.6 13 0.0019025

NIRVSS Unknown Unknown Unknown

MastCam-Z 4.5 11.8 0.009

RAD 1.6 4.2 0.00024

ChemCam 5.778 Unknown 0.00133

APXS 0.37 Unknown 0.000368

CheMin 10 40 0.027

**Mars Compass 0.5 2.5 Unknown

**Ground

penetrating radar 4.53 Unknown 0.0063

**Drill (5 cm) 4 Unknown Unknown

**Dust Counter 1.6 5.1 Unknown

Total 35.478 77 0.0461405

**Added since last presentation


MISSION DESIGN

73


APPENDIX: FERRY TO CYCLER

Exploration Upper Stage (EUS) • Places FEMAC into elliptical orbit

Booster • Performs hyperbolic insertion maneuver

Service Module • Identical ΔV capabilities as Booster • Only used if Booster fails

Crew Capsule • Supports a crew of 4 (payload of 22 Mg) • Heat shield capable of Earth reentry • Performs docking maneuver

Ferry to Mars Cycler (FEMAC) stage configuration:

37

Crew Capsule

APPENDIX: 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 – 2.09 km/s

3. EUS jettison

4. FEMAC Booster burn: Inject into hyperbolic departure orbit –

1.69 km/s

5. FEMAC Booster burn: Trajectory correction maneuver – 0.066

km/s

6. FEMAC Booster and Service Module jettison

7. FEMAC RCS burn: Rendezvous/dock with cycler – 0.030 km/s

Total required ΔV – 4.194 km/s

Launch Vehicle

SLS Block 2

IMLEO 273.2 Mg

IVLEO 1171 m3

Total ΔV Capability

7.979 km/s

Time of Flight

46.11 hr

FEMAC Specifications

Abort Options • Safe return with controlled reentry: 3 hours after

insertion • Prevent escape: 34 hours after insertion

Crew survival rate 96.96%

Mission success rate 93.96%

758

APPENDIX: HYPERBOLIC RENDEZVOUS

• Previous designs were based on FEMAC-35, which requires the

lowest ΔV

• 2039 flyby requires the most ΔV – the vehicle must accommodate

future missions, so we are sizing the vehicle based on the 2039 flyby

Reasoning: A FEMAC (FErry to MArs Cycler) will dock with a Mars

cycler every two years, and each flyby is different

Year Vinf (km/s) rmin (km) ΔVtot (km/s)

2033 4.41 26700 4.4632

2035 3.75 9700 4.1941

2037 4.25 9000 4.2879

2039 5.53 23900 4.9473

69

APPENDIX: FERRYING LANDER MISSION PARAMETERS

Mission: • Lunar Surface CLO XM-2 • Drop off old astronauts, pick up new ones • XM-2 Lunar Surface

Event Time-of-Flight

Takeoff 6.7 min

Ascent Hohmann Transfer

4.5 hours

Descent Hohmann Transfer

4.5 hour

Landing 13 min.

Total 9.33 hours

Maneuver ΔV (km/s) Number Required

Takeoff 1.961 1

Circularizing Burton to Enter CLO

0.231 1

15o Plane Change 0.271 2

Descent Hohmann and Landing

2.459 1

Total 5.193

APPENDIX: FERRYING LANDER TAKE ASTRONAUTS TO AND FROM XM-2 IN CLO

3. Enter CLO ΔV = 0.231 km/s

1. Takeoff ΔV = 1.96 km/s

2. Hohmann Transfer to CLO

4. Up to 15o Plane change to CLO ΔV = 0.271 km/s

5. Rendezvous with XM-2

6. Return and Land ΔV = 2.73 km/s

Event Time-of-Flight

Takeoff 6.7 min

Ascent Hohmann Transfer

4.5 hours

Descent Hohmann Transfer

4.5 hour

Landing 13 min.

Total 9 hours, 20 min

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 79

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.

80

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 81

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 82

APPENDIX: NUCLEAR THERMAL PROPULSION

83

Pros Cons

High specific Impulse > 800s Never been flight tested

Decreased time of flight High development costs

Broader launch window Potential for spreading nuclear

material if disaster occurs

Public fear of nuclear energy

Long shutdown times

Despite advantages, nuclear thermal rockets will not be available during our mission schedule. Thus, we chose to exclude them from our designs.

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.

84

COMMUNICATIONS AND CONTROLS

85


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

86

EARTH - MOON

APPENDIX: COMMUNICATIONS MAP

LUNAR

APPENDIX: COMMUNICATIONS MAP

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

89

APPENDIX: XM ATTITUDE CONTROL ENGINE & PROPELLANT SELECTION Assumptions

• ΔV = 100 m/s/year

• XM Module weight = 20 tons

• 20 year life span of BA330/XM

Requirements

• Ability to pulse

• Quick start up

• High ISP

• 6 DOF control

Propellant/Engine Selection

• 16x MR-107 (220 N)

• Monopropellant Hydrazine

• Catalyst S405/LCH-202

• ISP = 229 sec

• Refuel every 10 years

90

System Parameters – 20 years

Propellant Mass 12Mg/10 years

Inert Mass 20.01 Mg

Power 34.5 W/thruster

Propellant Volume 12 m3/10 years

APPENDIX: COM SATS

Figure Z.z. Backside view of communication satellite

APPENDIX: SATELLITE PARAMETERS Table X provides the mass, power, and size off all antennas in the communication scheme for the

whole mission.

Vehicle/Location of Antenna Mass (Mg) Power (W) Diameter (m)

Earth Bases (3) 4.70 100 9.40

Moon Base 1.50 25 3.00

Comm. Sats to Moon (3) 0.047 18 0.044

Comm. Sats. to Earth (3) 0.047 55 1.31

Ferrying Lander 0.003 25 0.131

Cargo Lander 0.003 8.0 0/188

Ferry-Cycler 0.003 65 1.220

Pressurized Rover (X-Band) 0.001 2.0 0.769

Pressurized Rover (HGA) 0.001 1.0 1.31

Science Probes 0.047 2.0 0.769

XM-2 0.047 50 0.088

Table X: Parameters for all satellites in the communication

scheme for Project Legacy IMLEO: 1.887 Mg

APPENDIX: VEHICLE CONTROLS Table X provides the mass, power, and volume of the full control system on each

vehicle. These vehicles must be controlled due to the forces listed below.

Vehicle Control Method Mass (Mg) Power (W)

XM CMGs & Thrusters 0.826 200 1.00

Ferry to Cycler CMGs 0.544 552 3.24

Ferrying Lander Reaction Wheels &

CMGs

1.108 356 1.63

Cargo Lander Reaction wheels &

CMGs

0.241 1015 1.63

Comm. Satellites Reaction Wheels &

Thrusters

0.296 430 0.047

Table X: Parameters for all control systems for each vehicle in Project Legacy

Environmental forces we are concerned with:

•Gravitational forces

•Reflected solar radiation

•Solar radiation

•Gravity gradient

•Magnetic field force

IMLEO: 3.015 Mg

SYSTEMS TRADE STUDIES

94


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

95

APPENDIX: HYDROLOX VERSUS METHALOX

96

Parameter Hydrolox Methalox

Specific impulse (s) 450 375-400

Boiling Point (K) 20 111

Manufacture Method Electrolysis Electrolysis and Sabatier

Ease of Storage Will boil in PSR Can be stored in PSR

TRL # 9 6

Hydrolox is the most useful propellant for our application as it decreases the IMLEO due to its low density and high specific impulse.

APPENDIX: METHALOX TRADE STUDY METHALOX TRADE STUDY FOR CARGO LANDER

[Table values are based on a 1 to 5 scale, 5 being the best]

Startability – Both Require ignition systems

Refueling – For now, the cargo landers are not planned to be refueled

Efficiency – Hydrolox have Isp values of about 450 s, Methalox is about 390 s

Storage – More volume will be needed for Hydrolox (less dense fuel)

TRL – Hydrolox is highly proven, having flown many missions as opposed to Methalox which has a TLR of 3-4

Fuel Type Startability Refuelling Efficiency Storage TRL Totals

Hydrolox 2.5 2.5 5 2 5 3.75

Methalox 2.5 5 3 4 1.5 2.975

Weighting 0.15 0.05 0.35 0.25 0.2

APPENDIX: ESI AND MSI

0.0 – 0.2 Completely Dissimilar

0.2 – 0.4 Dissimilar

0.4 – 0.6 Somewhat Dissimilar

0.6 – 0.8 Somewhat Similar

0.8 – 1.00 Very Similar

APPENDIX: RESULTS AND RECOMMENDATION

Results: Interestingly enough, Antarctica is considered the most “Mars-like” based off of the MSI calculations. The Moon would also still be considered somewhat “Mars-like.” In fact, some past research for future Mars missions has been done in Antarctica.

Future Considerations: Early testing for key systems (ISRU, habs, rovers, etc.) could be done in Antarctica to gain at least basic functionality or data on how they need to operate. Doing so could potentially save millions or billions of dollars in testing and would eliminate many unknowns when being used on the Moon or Mars.

Location in our Solar System ESI

Earth (Average Conditions) 1.0000

Venus (High Atmosphere) 0.9712

Antarctica 0.8473

Mars 0.6975

Moon 0.5606

Venus (Surface) 0.4398

Location in our Solar System MSI

Mars 1.0000

Antarctica 0.7080

Moon 0.6892

Venus (High Atmosphere) 0.6451

Earth (Average Conditions) 0.6309

Venus (Surface) 0.3557

APPENDIX: BACKUP SLIDES The weight parameters that are used to calculate ESI are obtained by using the definitions

of terrestrial planets. The lower and upper bounds of these definitions are put into the ESI

equation and equated to 0.8 which is the boundary for “like-ness.” The equation is then

solved for w to obtain the weight factor for each boundary. The two boundary values are

averaged to obtain the official weight exponent.

For example, terrestrial planet definition for radius is between 0.1 and 10 Earth radii.

These two values help to define the upper and lower boundary values which are averaged

to obtain the weight exponent. An exponent with a higher value has a greater effect on the

similarity index. Each parameter has its own unique weight exponent.

Since the weight exponents are created based on parameters written in Earth units, new

weight exponents were made using Mars units to create the Mars similarity index. ESI is

commonly used as a way to gauge potential habitability because the temperature

exponent for ESI is calculated from a range of 0°C to 50°, the most suitable temperature

range for life as we know it.

APPENDIX: SCALING FOR MARS MISSION CHANCES IN WORKING AND ENVIRONMENTAL CONDITIONS

• Temperature Range: -207°F to 80°F (extremes)

• Atmospheric properties: 95% CO2

• Radiation: Galactic Cosmic Rays, solar flares

• Gravity: 3.711 m/s2

• Transit time: ~6 months

APPENDIX: SCALING FOR MARS MISSION BENEFITS OF OUR TECHNOLOGY

ISRU and Fuel Depot

• Ground extracting methods

• Processing ice

• Fuel Storage

Communications

• XM2 has similar orbital properties of

Phobos

Rovers/Attachments

• Semi-autonomous capabilities

• Airlock system

Habs • Construction capabilities • Proving aeroponics

Mental and Physical Health • Long term physical effects on the

human body • Mental effects of long duration away

from society

APPENDIX: WHO WE SHOULD CONSIDER

103

TOP 5 MAJOR SPACE FAIRING NATIONS: European Space Agency (France, Germany, Italy):

• ESA: proposed ‘Lunarville’ (2024)

• CNES: launch vehicles, propulsion

• DLR: robotics, rovers, automation

• ASI: propulsion

Roscosmos State Corporation:

• Luna 27 (2020)

• ‘Lunarville’

• Proposed crewed Lunar launch station (2029)

China National Space Administration:

• Chang’e Program

• Lunar Sample Return (2017)

• Proposed crewed mission (mid-2020s)

Japan Aerospace Exploration Agency:

• SLIM (2018)

Indian Space Research Organization:

• Chandrayaan-2 (2018)

Institutions/Schools/Research Labs

APPENDIX: SUGGESTED FUTURE COLLABORATIONS

Other Possibilities:

• Institutions/Universities/Research Labs

• International Commercial Companies

• Competitions

• Educational Science Experiments

** Green: Excelled/Proven Capital

Yellow: Proven/Known Capability

Red: Missing Requirements

104

Rank Agency Interest Resources Capability

1 ESA

2 Roscosmos

3 JAXA

4 CNSA

5 ISRO

APPENDIX: VOLATILE TRADE STUDY WHAT IF THERE ARE NO VOLATILES ON THE MOON?– ALEXANDRA DUKES

Hydrolox Mass Required for One Year

Hydrogen [Mg] 4.09

LOX [Mg] 24.03

Crewed Launch Years

2029

2031

2032

2033

2034

2035

2 Launches Required per Crewed Mission

Hydrolox Mass Required for Mission (2022 – 2035)

Hydrogen [Mg] 22.50

LOX [Mg] 120.13

Assumptions: The Fuel Depot is launched to store Ferrying Lander fuel.

Assumed 4.5 for Hydrogen Boil off and

Margin

Number of Fuel Tanks: 10 Launches Capable of Carrying Fuel Tanks: Launch 20 (SLS Block 2): Hab 9F Launch 22, 24, 26, 29 (Falcon Heavy): Food/Water

Extra Launches Required: 10 Falcon Heavy launches (2 per Lander use) before crewed missions IMLEO increases by 135 Mg

APPENDIX: VOLATILE TRADE STUDY ADDRESSING HYDROGEN BOIL OFF – ALEXANDRA DUKES

Hydrogen Boil Off Days Before Storage

On Launch Pad 3

Launch to LEO Ideal Case 1

Worst Case 14

LEO to Moon 5.5

Landing Site to Fuel Depot

0.03

Total Days: Ideal Case 9.53

Worst Case 22.53

Boil Off Calculations & Results

Boil Off per Day 0.001%

Ideal Boil Off 0.041 [Mg]

Worst Case Boil Off 0.104 [Mg]

Minimum Fuel Needed

4.086 [Mg]

Total Resulting Fuel from Ideal Case

4.460 [Mg]

Total Resulting Fuel from Worst Case

4.397 [Mg]

IN-SITU RESOURCE UTILIZATION

107


APPENDIX: ISRU

108

ISRU PATENT

U.S. Patent #: US 8357884 B1 Inventors: • Edwin Ethridge (MSFC) • William Kaukler (U of A Huntsville) Utilizes boring cylinder and microwave emitter to heat volatiles. Volatiles (water) are collected and ran into a cold trap which is then stored in a tank.

APPENDIX: ISRU ROVER AND DRILL

• Rover design with attachment for drilling into regolith

• Drills down to ice and uses microwaves to sublimate ice

• Gaseous H2O travels up drill and into tanks

• Mass: 3.0668 Mg (mass of rover + tanks + drill)

• Power: 100 W for microwave emitter + power required to run drill

• Drill applies a torque of 10kNm

Top View of Drill

APPENDIX: ISRU ROVER AND DRILLINGS

Need 0.15Mg water per day

0.15Mg = 150kg

5,000kg regolith * 0.03 = 150kg

So we need to heat 5,000kg regolith

Based on drill parameters, we can heat 0.63m3 with one hole

That gives 1500kg/m3 * 0.63m3 = 945kg with one hole

5,000kg / 945kg = 5.29 holes

So drill 6 holes per day to get required water

Heating time approximately 10 minutes based on computer model

APPENDIX: ISRU ROVER AND DRILL MODEL Isothermal plots (from 100 to 200K) at the tip of the monopole launcher after 1 minute (on the left) and 10 minutes (on the right). The brown region is >200K, and should be completely devoid of water.

Ethridge, Edwin C., Kaukler, William, Finite Element Analysis of Three Methods for Microwave Heating of Planetary Surfaces

APPENDIX: TOP VIEW OF DRILL

30cm

1.27cm

Outside ring lined with teeth for cutting into ice

Microwave Emitter

APPENDIX: MOVEABLE DRILL Drill is on a hinge so it can be laid flat on rover for driving

APPENDIX: INSTRUMENT SPECS MASS, POWER, VOLUME FOR REQUESTED INSTRUMENTS

Instrument Mass (Mg) Power (W) Volume (m3) Data Rate (kbps)

Gamma Ray Spectrometer

0.0305 32 0.151 -

Infrared Spectrometer

0.0112 14 0.057 -

Magnetometer 0.003 3.1 - 3.60

Radiation Detector

0.0033 7 0.007 -

Imaging Camera

0.0091 8.6 0.052

Total 0.0571 65.1 0.21

114 Caleb Engle

FUEL DEPOT

115


2026 ADAMS 5: FUEL DEPOT

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

116 – Austin Black

Fuel Depot

Location: PSR At mining site

Function: Processes water into fuel/oxidizer

Mass (dry): 16.64 [Mg]

Power: 300 [Watts]

Volume: 313.9 [m3]

LOX

Tank

LH2

Tank

H2O Tank

Heat

Exchanger

MLI Insulation

Aluminum

Support 1

5

4

3 2

H2O Input Line

LOX/LH2

Output Lines

2026 ADAMS 5: FUEL DEPOT

MISSION TIMELINE

117


APPENDIX: MISSION TIMELINE

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

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

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