Project Future Moon PDR
PDR PRESENTATIONS
February 8th, 2019
1 Introduction
Andrew Lang PM February 9th, 2019
2 Project Background
● Earth’s strong gravity well makes space exploration difficult ● Current exploration efforts discard most of what is launched from Earth’s surface ● More sustainable mission architecture is needed ● Experts advocate in situ resource utilization ● Paul Spudis proposed a lunar outpost near the poles and orbital propellant to fuel future missions to Mars
3 Project Solution Overview
● Conduct feasibility study of the systems proposed by Spudis that will fuel future missions to Mars ○ MINIMIZE MASS sent from EARTH ○ 100Mg of prop annually ● 14 Systems ● 3 Phases ○ Discovery ○ Development ○ Habitation
4 BACKUP: Storyboard (Discovery)
*Cislunar vehicle and Major Launch Vehicle required for most/all stages
Launch From Ensure/ Establish Earth into Lunar Connection Between Orbit Moon and Earth
Communications Satellite
Land on lunar Find/Confirm Use information surface (Landing sites of to select crater / Deployment water/light Scout Rover I Vehicle)
Land in Demonstrate Move to crater regolith separation Development (L/DV) process Phase
Scout Rover II 5 BACKUP: Storyboard (Development)
Establish power Level Landing source, ground Area communications
Landing Site Prep
Land Assembly prefabricated (Possibly by materials Landing Site Prep) Resource Storage
Land Ice Separate ice Store ice/water Harvester from the lunar in Resource Components & regolith Storage area Assemble Ice Harvester 6 BACKUP: Storyboard (Development)
Begin transfer Store of ice into Propellant propellant
Lunar Propellant Depot
Land major sections of Assembly of Habitat structure components Habitat Infrastructure and life support
7
Insert Safe Habitation Haven into Phase Lunar Orbit Safe Haven BACKUP: Storyboard (Habitation)
Note: At the current stage, the location to which propellant is being transported is being re-evaluated. Either a Orbiting Propellant Depot or the Mars Transport Vehicle will come after this Vehicle. A reusable lander is required for the Reusable Lunar crewed missions Launch Vehicle M1 Orbit Moon
Crewed Mission 3
M3 Remote landing of landing vehicle
Crewed Mission 2 8 BACKUP: Storyboard (Habitation)
M3 Setup incomplete / One day stay on small scale aspects lunar surface of Habitat, small science aspect Crewed Mission 3 Repeat as necessary
Land on Lunar Surface Lunar Surface Transport
Insert into lunar orbit Remote missions for fuel storage using the Reusable Lunar Launch Orbiting Depot or Vehicle can begin
Mars Transport 9 BACKUP
M4 250 day stay on the Continue ice mining Moon missions and launches
Crewed Mission 4
Humans arrive to or Fully fuelled Mars in the Mars Transport Vehicle Transport Vehicle. begins orbit to Mars
Mars Transport Vehicle
10 SCOUT ROVER SPECIFICATIONS
Group Lead: Myles Homan Rovers/Demonstration Systems February 9, 2019
11 Problem
Requirements ● 12 rovers to search for water ice on the lunar poles and to demonstrate harvesting systems ● Need to minimize the mass and volume of this system
Need to Determine ● What science/scouting equipment is necessary ● Mass and power requirements of science and demonstration equipment ● Power required to move the rovers and range
Assumptions ● The mass of the motor, wheels, and chassis is 25 kg ● Aerodynamic resistance on the Moon is negligible ● The speed of the scout rover is constant Solution
1st wave- ● 4 scout rovers each to north and south pole ● Only scientific equipment necessary to detect water ice is carried
2nd wave- ● 4 scout rovers to best destinations chosen ● Both the scientific equipment to detect water-ice and the equipment to demonstrate the harvesting systems
All rovers will have the same main design which includes ● Chassis ● Power system ● Main body
13 Detection/Demonstration Equip.
Demonstration method: First 8 rovers: Detection Corer (planetary volatile extractor) Last 4 rovers: Demonstration ● double walled coring auger with inside heaters No science on scout rovers ● corer penetrates surface and captures regolith ● volatiles are sublimated, condensed, and stored Mass/Power/Volume of Detection and Demonstration Equipment:
14 Slide by: Pavi Ravi POWER SYSTEM
Requirements ● Needs to provide 341 W peak power ● Needs to last until its mission is over
After considering many power options, lithium-sulfur batteries were chosen due to its high power density
3 Specific energy W*hour/kg W*hour/m 500 350,000
Mass Mg Power W*hour Volume m3 0.02 10,000 0.0286
15 TOTAL M.P.V. and Performance
Scout Rovers Demonstration Rovers Mass Mg Power kW Volume m3 Mass Mg Power kW Volume m3 0.0826 0.341 0.349 0.0957 0.319 0.4655
-Each set of 4 scout rovers will -Each set of 4 demonstration take up approximately 1.4 m3 and rovers will take up approximately has a mass of .357 kg 1.9 m3 and has a mass of .383 kg
Range
Time hours 29.32
Distance km 87
16 Backup: Detection/Demo Equip.
Corer description: A Corer based volatiles extractor is essentially a dual wall coring auger. The outer wall is a traditional auger with shallow flutes, made of low conductivity composite material. The inner wall is perforated and also covered with heaters. The coring drill penetrates subsurface and captures a core. Heaters are turned on to sublime volatiles within the core. Volatiles then flow within the annual space between the inner conductive cylinder and the outer insulating cylinder (auger), and into a cold trap on the surface.
Demonstration equipment references: ● http://rascal.nianet.org/wp-content/uploads/2016/08/PVEx-for-ISRU.pdf ● https://www.hou.usra.edu/meetings/V2050/pdf/8082.pdf ● https://www.hou.usra.edu/meetings/leag2016/presentations/Thursday/Indyk.pdf ● http://rascal.nianet.org/wp-content/uploads/2016/08/PVEx-for-ISRU.pdf 17 Slide by: Pavi Ravi BACKUP: Power
18 BACKUP: Power
19 BACKUP: Power
20 Major Launch Vehicle Overview
Project Future Moon Preliminary Design Review February 9, 2019
21 Purpose
REQUIREMENTS - Use a reusable rocket to minimize launch costs - Must launch at most a payload of 51.8 Mg and 2032 m3 (will change) - Four pressurized rovers, one empty MLDV and six astronauts - Must achieve a delta-V of 8.415 km/s from Cape Canaveral to LEO - The total initial mass launched from Earth's surface to Low Earth Orbit (LEO) should be minimized.
THE MISSION - If MLDV design shrinks down and we can make launch payload in one launch - Launch to LEO and let the MLDV descent to the moon surface to bring rovers
22 Major Launch Vehicle
SLS Block 2 Cargo - Provides us with more breathing room in terms of packing and allows for unexpected changes in payload masses and volumes. This was deemed the most logical choice for now given that not much is set in stone yet.
QUANT. PARAMETERS - Mass: 980 Mg - Thrust: 52,000 kN - Payload to LEO: 130 Mg - Provides more freedom for - Payload volume: 905 m3
Possible Future Iterations depend on when final payload masses and volumes will be obtained. Major Launch Vehicle
NEEDS FROM MLV TEAM - Finalize a MLDV design (PROP will get that done soon!) - Collaborate on payload packing with each team that will send payload *see Slack*
MOVING FORWARD - I do not recommend working on this unless systems volumes are drastically changed and it is needed. Landing/Deployment Vehicle (LDV)
Project Future Moon Preliminary Design Review February 10, 2019 Lunar Deployment Vehicle
Background “This system delivers scout/demonstration rovers from lunar orbit to lunar surface” during the Discovery Phase
Requirements HLR 1: “Land a dozen small rovers near the lunar poles…” HLR 3: “Prepare the lunar surface to avoid dust during landing”
Solution 1) Major Launch Vehicle puts system in lunar orbit 2) Disposable vehicle takes 4 rovers near lunar surface 3) Sky crane maneuver to lower rovers to lunar surface
Kyle Duckering Mission Design
- LDV is an expendable system exclusively used during Discovery phase of mission
- Must land 12 scout rovers on the north and south lunar poles
- Descend from LLO (100 km altitude) -> Propulsive landing
Step Description Avg. ΔV (km/s)
1 Enter descent arc 0.021
2 Propulsive landing 1.951
/ TOTAL 1.922
Cody Hawkins Structures and CAD
Structures Overview - Primary vehicle made out of aluminum - Structural mass will be <0.1 Mg - Moon crane must be able to lower ~0.2 Mg about 25m - Spectra fiber rope to be used to lower rovers - <1 kg in mass - ~3,000 kg tensile strength Tyler Stark
Utilized Sky Crane maneuver for lunar lander in order to avoid dust and debris. Matthew Eustace Communications and Controls
Communication Module Power: 25W ● 8X 71 kN, 300 isp thrusters. ○ offers redundant control on all axes Sense & Compute Module:
Mass: 2 kg Power: 65 W Volume: 0.03 m^3
Kevin Sheridan Propulsion
Parameters (All per thruster) Project Future Moon LDV Apollo Descent Propulsion System
Thruster count 8 1
Thrust 71 kN 45 kN
Inputs Isp 300 s 311 s
Delta-v 1.9506 km/s 1.7 km/s*
Dry Mass ? 2000 kg
Propellant Mass (Aerozine 50) 11.36 mg 8.2 mg Calculated Pressurant Mass (He) 40 kg 22 kg
LDV currently calls for 8 x 71 kN thrust, need to bring down required thrust (per thruster) to pass sanity check compared to Apollo Descent Stage or realize scale of lander
Revisit required thrust or realize scale of payloads, implement LH2 architecture to increase Isp, avoid toxic hypergolics on landing site, and integrate with cislunar economy
Sam Evani Power/Thermal
Problem: Power components of the LDV
Power Requirements: Power Sources:
- Communications and Control - - Parallel battery Compute and Sensing Package - configuration requires 25 W (12-24V) Li-ion to provide 500 W of - SkyCrane Winch - linear actuated power motor required 405 W assuming 0.8 m/s downward velocity of 0.2 - No requirement for Mg rover payload solar cell technology given low power requirements
Mihir Joshi Backup - Rover Sizes
Water-ice detector: Primary options: ● Neutron spectrometer - measures H abundance (0.01 wt.%) ● UV or IR - useful for detecting trace amounts of pure water ● Impactor - measures atmospheric properties after disturbance ● Ground penetrating radar - can image subsurface geologic features
Sunlight detector: Primary options: ● Infrared sensor - estimates ground temperature from IR radiation ● Solar panels - higher power generation in sunlit areas ● Camera - visual detection of sunlight
Mass (kg) Power (W) Volume (m3) Detection rovers 37.6545 65.39 0.286
Demo. rovers 50.6545 195.39 0.403
32 Pavi Ravi CisLunar Transport Vehicle
Project Future Moon Preliminary Design Review 9 February 2019 Mission Design
● Cislunar vehicle transfer will be from 300 km low Earth orbit (LEO) to approximately 90 km low lunar orbit (LLO)
● Assumptions include impulsive maneuvers, centrobaric celestial bodies, 20% MoE, and an isolated system
● Through comparative analysis, it has been decided that a Hohmann transfer would provide the lowest ΔV
ΔV from LEO to ΔV from LLO to L1 ΔV from L1 back Total Time of LLO (km/s) (km/s) to Earth (km/s) flight (Earth days)
4.716 0.8576 5.574 15.404
34 CLTV Human Requirements
● Requirements for Crewed Mission ○ Numbers calculated per person per day ○ Water: ~10 liters ○ Oxygen: ~720 liters ● Basic requirements, add safety factor as needed. ● Total Mass: 2.1985 Mg
Human Requirements Weight Volume for Crewed Missions
Food 0.72 kg .004 m3
Water 10 kg 0.01 m3
3 Oxygen 1.1 kg 0.72 m 35 CAD Design
18.19 m
10 m POWER for CLTV
Problem: Supply power to the Cis-lunar Vehicle Cislunar Vehicle Power Sources : - Gallium Arsenide (GaAs) Solar Panels → Integrated with Maximum Power Point Tracker (MPPT) feeding into DC-DC converter for bus voltage regulation - Li-ion Batteries for backup power storage - Can supply to communications, electrical loads, solar panel attitude control - Potentially can use solar concentrators → intensify sunlight
GaAs Solar Panels on CLTV Efficiency 37% + Power Supplied 4.055 kW Surface Area 8 m2
Mass 6.4 kg (based on 80 mg/cm2 areal mass density) 37 CLTV Propulsion System
Aluminum 6061-T6 Work done up to this point: Tank Properties -LO2 / LH2 - Twin tank design at 1379000 Pa Al 6061-T6 - 20% Ullage, 1.5 Factor of Safety Density 2.72 - 10% Fuel used for film cooling (Mg/m3) -Mass calculation of empty fuel tanks using fuel and oxidizer volume estimates from 1/31/19. Hydrogen -Total empty tank mass: 0.4245 Mg Tank Mass 0.3909 (Mg)
Oxygen Tank Mass 0.0336 3 VOx Tank VFuel Tank (m ) MOx (kg) MFuel (kg) (Mg) (m3) Tensile 86.1866 257.2164 81949.0 13658.0 Yield 241 Strength (MPa) 38 Communication Satellites
Project Future Moon Preliminary Design Review February 9, 2019 Constellation Design
3 satellites Orbital Parameters Sat 1 Sat 2 Sat 3 2 phases Semi-major axis ● Discovery: a (km) 4900 4900 4900 Even coverage of both poles ○ Circular polar orbit Eccentricity e 0.5 0.5 0.5 ● Development/Occupation: Focus coverage on the Inclination i 70 70 70 inhabited pole (for now Argument of assumed to be the South periapsis ⍵ Pole) ○ Elliptical orbit (deg) 90 90 90 RAAN Ω (deg) 0 90 180 Mean anomaly M(deg) 0 90 180 True anomaly 훉 152.562 207.437 (deg) 0 9 1 Station Keeping Requirements
● Will require a substantial amount of delta V to keep communication satellites in orbit
● Station keeping maneuvers retain full visibility of the satellites from the habitat
● Future work will need to be done to calculate additional delta V requirements from Sat 1 Sat 2 Sat 3 Phase 1 of the constellation design (circular orbits) 힓V after 0.011 0.023 0.014 ~120 days (km/s)
힓V after 0.145 0.304 0.185 1533 days (km/s) Propulsion
● Hydrazine resistojet electric thrusters to be used for station keeping ● Future work will analyze whether or not these thrusters can also be used to control attitude
Mass Power Volume per satellite ● Mass: Total (.55 Mg), Propellant ( .4 Mg) ● Volume: 1.5 m3 ● Power Required : 2.5 kW (thruster and heaters) Science Equipment on Satellites
● Cameras and altimeters analyze topography ● Other equipment monitors space weather and atmosphere ● Mass and power evenly distributed over satellites
43 Summary of Progress
Current progress ● Antenna will need to be drastically resized - power requirement and diameter not accurate ● Station keeping propellant/solar panels will be resized as more data comes in ● Batteries/science equipment/ADAC package all fairly accurate estimates
Work to be done ● Full link budget analysis needs to be completed to resize the antenna properly ● Station keeping delta V for the full duration of the mission needs to be calculated ● Structural mass of the satellite bus needs to be calculated ● Details of attitude control through thrusters and reaction wheels needs more detailed analysis Ice Harvesters System
Project Future Moon Preliminary Design Review February 9, 2019
45 Background: Ice Harvesting
Background It was discovered that H20 is present on the moon underneath the surface regolith in the form of ice. Ice exists in parts of the moon where there is no exposure to the sun. These spots are craters where the walls of the craters create a barrier from the sun due to the moon’s axis.
Credit: NASA 46 Problem: Ice Harvesting
Requirements ● Harvest the ice on the moon in order to use for fuel, survival, health, etc. for the mission. ● The ice will need to be excavated and separated from other material/chemicals that might be in the regolith for H20 use.
Need to Determine ● How we will dig up the regolith/ice mixture ● How we will separate the ice/H20 from the rest of material
Assumptions ● Ice is located in craters that do not get sunlight and on the edge of craters that get partial sunlight such as Shackleton crater ● Ice will not be in its purest form and will require some type of distillery and purifying process
47 Solution: Ice Harvester System
Harvester Trailer Specs
Wet Mass (Mg) 6.920
Harvester Miner Specs Dry Mass (Mg) 5.17
3 Mass (Mg) ~1 (estimate) Tank Volume (m ) 1.75
Volume (m3) ~9 (estimate) Max Power Req. (kW) 19.74
Battery Capacity 870 48 (kWh) Solution: How deep and how much is ice?
● Science team is currently investigating what the moon surface is made up of ○ Sources have found that 1 - 6% of the regolith crust but upwards of 12% is made up of ice ○ Looking into if there are pure sheets of ice beneath a certain depth ○ Assumption: Ice is mixed with the regolith and a depth of at least 5 m is required but water-ice is usually present at 2 m ● Current existing demo systems ○ Water extraction system that can get 30 kgs of water from 12% regolith everyday
49 Solution: How much ice and how many machines?
● Overestimation of 300 Mg of ice/water needs to be provided for the sake of our mission ○ 300 Mg per year (365 days) equals 822 kg of water-ice mined on average per day ● System proposed to extract water can hopefully be scaled up to fit the needs of our mission
50 Landing Site Prep - PDR
Tyler Stark Structures Landing Site Prep February 7, 2019
51 Problem: Landing Site Prep
Background The lunar surface is uneven and covered in dust and rocks. There is also no real atmosphere. These two facts combined mean the a propulsive landing is required for any large vehicle or system landing on the lunar surface. Propulsive landings will send dangerous debris around the lunar surface which may jeopardize other aspects of the mission. By preparing a landing site we can minimize this debris while also providing a system that allows future landings to land accurately.
Requirements - Must prep landing site for lunar launch vehicle - Minimize dust dispersion during landings/take-off - Provide a communication system to assist landing vehicles
Need to Determine - Strategy, required materials, and system for site prep - What kind of position information the site should relay
Assumptions - Several kilometers of space between site and habitat - Sunlight for solar power is available - Ground not completely flat 52 Solution: Landing Site Prep
Solution - Multi-purpose Lunar Construction Vehicle (MLCV) - MLCV will look similar to a terrestrial loader but will be fit with a tile laying mechanism on the opposite side - The loader will be used to flatten the landing site - MLCV will then go over the landing site placing thermal tiles similar to those used on the Space Shuttle - Loader will then be available to be used for habitation development
- Lunar Push Vacuum (LPV) - The LPV will be delivered with the MLCV and used to clean the pad between launches to prevent dust build-up on the pad - When the LPV is idle it will recharge using solar power and act as a relay to the next landing vehicle providing location tracking assistance
53 MLCV Overview
Multi-purpose Lunar Construction Vehicle Overview
- Able to clear a 25m diameter launch/landing zone - Places ~1.1 Mg of thermal tiles - Loader to be used to partially cover habitat for radiation protection
MLCV Specs
Mass (Mg) Power (kW) Volume (m3)
<1 TBD 9
54 LPV Overview
Lunar Push Vacuum (LPV) Overview
- Mechanical vacuum system capable of clearing the launch pad in between launches - Communication package that is able to track and relay information to landing vehicles
LPV Specs
Mass (Mg) Power (kW) Volume (m3)
<0.1 TBD 5
55 References
“THERMAL PROTECTION SYSTEM,” NASA Available: http://science.ksc.nasa.gov/shuttle/technology/sts-newsref/sts-tps.html#sts-hrsi.
56 Resource Storage - PDR
Sandra Bonilla Human Factors Resource Storage 2/9/2019
57 Problem
Additional storage space will be needed for all extra supplies and equipment.
What we expect to need storage space for: ● water ● oxygen/nitrogen ● Hydro-Lox ● food ● clothing/supplies ● extra parts and tools for repairs ● science samples
58 Solution
Two separate storage units will be used for regular supplies and chemicals or hazardous materials. ○ Supplies that will need to be accessed frequently by the crew will be stored in space easily accessible by the crew in or near the habitat. ○ All other supplies will be stored in a separate unit.
59 Solution
First storage unit in or near the habitat: 50 m3
Second unit: 150 m3 (Rough estimate)
*More accurate numbers are dependent on requirements of other systems that have not been finalized or specified yet.
60 Lunar Launch/Descent Vehicle
Project Future Moon Preliminary Design Review February 9, 2019 Mission Design
Values in this table are for launch and descent to/from 100 km circular lunar orbit
Site Latitude Launch ΔV Descent ΔV (km/s) (km/s)
Shackleton 89.9° S 1.8837 1.9506
Sverdrup 88.5° S 1.8835 1.9504
Rozhdestvenskiy 82.2° N 1.8829 1.9499
Note: Apollo ascent required 6055 ft/s (1.845 km/s), descent required 6287 ft/s (2.08 km/s) Source: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19720018205.pdf (pages 19 and 23) Comm & Control
Communication Module Power: 25W ● 8X 71 kN, 300 isp thrusters. ○ offers redundant control on all axes Sense & Compute Module:
Mass: 2 kg Power: 65 W Volume: 0.03 m^3 Human Factors
• Needs • Air • Room for 6
• Solution • Pump with oxygen generated from base • 62 kg(Avg. mass of human) *6 ~~ 372 kg (crew) • 0.0774(Avg. volume of human)*6 = 0.4626 m^3 (crew)
64 Scientific Considerations
The main scientific considerations of the lunar launch and descent vehicle will be to mitigate the disturbances experienced by samples and equipment being transported. This will be done by reducing the G forces upon the equipment and ensuring the samples are kept in controlled environments, protected from changes in chemical composition and radiation effects. However, until the exact Scientific objective is known it is unknown exactly these conditions will need to be Pressurized Rovers/Spacesuits
Project Future Moon Preliminary Design Review February 9, 2019 Pressurized Rover Facts
● Astronaut safety during missions is utmost priority ● Trip length less than 8 hours ● Rover fits 6 astronauts in case of emergency (average mass of 75 kg) ● Usual operation will only include 2-3 astronauts ● The mass of the pressurized rover structure is about 3 Mg ● The Rover will contain science payload, multiple arms, and 4 wheels
Various configurations for Rover arms (Fully Deployed vs Stowed). Can have claws, drills, jackhammers, etc to assist with science objectives. Spacesuit Facts
● Spacesuits feature science equipment requiring about 40 W of power ● Spacesuits contain water cooling tubes, radiation protection, oxygen supply, pressure garments, and layers. ● Suitport has a total mass of about 60 kg ● The pressure of the suitport is about 0.5 bar ● The amount of oxygen in the suitport is 6.4 kg in a 15 liter tank at about 300 bar. MPV Pressurized Rovers/Spacesuits
ROVE Mass Volume Pressuri Spacesui R (kg) (m3) zed t 3 person Rover crew on 8 hour Mass 3.5 Mg 0.05 Mg * mission
Water 15 0.015 Power 5.2 kW (9 125 W km/h) Food 4.3 0.024 10.4 kW Air (O2, 105 0.45 (18 km/h) N mix) 2 Volume 16.6 m3 * 0.15 m3 * First Aid 2 0.03 Supplie s Spacesuit/rover sketches
Suitport and space suit connected to the pressurized Rover.
Rough sketch of pressurized rover, space suits, habitat docking, and suitport. Science Payloads
The pressurise rover will be acting as the missions primary science vehicle and so will have a large amount of onboard science equipment. The exact equipment required is still unknown as the primary science objective is still under consideration. However, the rovers will require an estimated 500kg of scientific equipment. This will largely be sample collection and measurement equipment upon the rovers including: ● Atmospheric and surface composition spectrometer ● Energetic particle and plasma spectrometer ● Robotic Arms capable of drilling into and sampling the regolith ● Cameras ● Lunar Dust Detector PDR: Habitat
Team Lead: Chris Saccoccio CAD Habitat February 9, 2019
72 Habitat CAD Overview
Requirements for CAD: Structure based analysis: ● Habitat must be large enough to hold 6 person crew ● Large enough to hold sports court ● List of rooms include ○ Personal & common space ○ Bathroom ○ Water/food storage ○ Medical area ○ Science lab ○ Airlocks ○ Radiation room ○ Logistics closet ○ Tunnels between each section ● Assumed habitat would be outside of the primary crater Environmental based analysis: ● Can hard dock pressurized rovers to habitat ● Height about 4.3 m (~2 stories) ● Radius found with spherical cap formula: 4.85 m ● Tunnels+Dome Volume = ~1075 m3 ● But if we round down once we pack science equipment and food + water in logistics we would have less room ● Total Mass: 90-120 Mg ○ Each module: 18-24 Mg ○ Falcon 9 max payload: ~23-24 Mg (to LEO) ○ ISS sections typically between 5-25 Mg ○ For tunnels sections add: 5 Mg * 7 = 35 Mg 73 Habitat Power Overview
Science Power Requirements ● Power required for equipment: 720 Watts
O2 Generation Power Requirements: ● About 1 to 1.5 kW Internal Module Habitat Power Options: (More Info in backup slide) Note: We need to have a life support system for each habitat module and below shows the options available. ● ECLSS-OGS ● Elektron ● Solid Fuel (SFOG) Internal lighting Requirements: ● Large rooms: 8800 to 20500 lumens at 65 to 160 Watts for low and high intensity lighting ● Small rooms/ Personal Space: 2000 to 5000 lumens at 14 to 36 Watts for low and high intensity
Power Generation Methods SOLAR NUCLEAR
Specific power density 150 W/kg ** >33.3 W/kg
** only includes the cell itself
With 1 large solar farm on one of the peaks of eternal light, power could be provided to most of the lunar base modules. The solar panels will be high efficiency multi-junction panels which have a 478.1 W/m2 power density on the lunar surface with a mass of 3.19 kg/m2 surface. 74 Habitat Science Overview
● Continued international research from Habitat Science Laboratory Sizing and CASIS submitted research proposals for Equipment Requirements: both academic and government users ● The laboratory must not exceed 40 cubic meters of ○ Life sciences, physical sciences, space technology development, remote ● Equipment must not exceed 100 kg sensing, etc. ● Equipment plus tables/shelves must not exceed 1000 kg ● See how the tools we bring to the moon ● Minimum of 8 cubic meters of free space to move fare while exposed to the harsh about environment (with an eye towards ● Must be capable of analyzing geological samples permanently settling the Moon and Mars) ● Mass (excluding surrounding structure): 740 kg ○ Material and structure weathering ● Power required for equipment: 720 Watts ○ Radiation shielding ● Volume: 30 cubic meters ■ Material samples Potential Equipment ■ Radiation Detector ● Scales (2) ● Hammers (2) ● Chisels (full set) ● Polarizing light microscope ● Scanning Electron Microscope
2.5 meters
75 3 meters
4 meters Habitat Structures Overview
● Primary Structure Types: Radiation Hazard Assessment: ○ Inflatables ● Conduct mission during solar minimum ○ Rigid/hard body ● Habitation on cool zones (South Pole) ○ Cable ● Utilize lunar regolith ● Limit extravehicular operations ○ Fully or partial underground structures ● 10 g/cm2 Al with additional 10 g/cm2 Al in storm Environmental concerns for habitation: shelter ● Temperature, Radiation/Shielding, Atmosphere and ● Active radiation monitoring pressure, Meteoroids, Gravity, Length of the lunar day, ● Limit of 500 mSv for 250 days Dust, Seismicity, Landing zone safety ● Protection in habitation compensates for Structural Requirements: EVA/Science rover exposure ● Mass/Volume of shielding fits launch vehicle ● Structure must maintain loads for long period of time
● Materials must safe, reliable, and withstand high temperature ranges ● Maintenance must be kept to a minimum ● Functionality increase such that usable volume is reduced ● Compatible with various systems as mission complexity increases ● Low mass for transportation to the lunar surface ● Ease of construction ● Use of local materials
76 Habitat Human Factors Overview
● Food & water budget for 6 astronauts: Overall food requirements: ● Harvesting ice will allow for a higher water Time (Days) Mass (kg) Volume (m3) supply and more comfortable living conditions. 1 4.4 0.024 Purpose Daily Requirement 250 1,100 6 Drinking (accounts for 4 liters total from 1000 4,400 24 water lost from exercise) fluids and food Shower 30 liters • Each astronaut will need to eat approximately 2,000 calories Other hygiene (brushing 3 liters teeth, washing hands, etc.) • Assuming annual resupply CRS flights, we must have enough food and water for additional 12 to 18 months in ● Approximately 222 liters of water a day is worst case with loss of cargo resupply vehicle and astronaut return needed for 6 person crew ● Oxygen /Atmospheric Needs ● 21% O2, 78% N2, 1% CO2 Fitness Requirements ● Requirements: 6.1732 kg O2/ Earth day ● Use a device similar to bicycle with resistance ● Oxygen & Nitrogen will not be readily available ● Use resistance-based exercise equipment and will need to be manufactured/stored in ○ e.g. ARED on the ISS each vehicle and living space. ● Simulate gravity with spin ● Working options: Electrolysis, solid fuel ● Recreational equipment: ~50 kg oxygen, bottled
77 BACKUP: Evaluation Criteria
Structural and Environmental Evaluation :
78 BACKUP: Habitat Map
79 BACKUP: Science Equipment
Equipment Mass (Kg) Power (Watts)
Hammers 2 0
SEM [1] 50 700
Polarizing 9 20 Light Microscope [2]
Chisels 5 0
Total 66 kg 720 W
[1]https://www.nikonmetrology.com/en-gb/product/jcm-6000-plus-neoscope [2]https://microscopecentral.com/collections/petrology-geology-microscopes/products/amscope-binoc ular-polarizing-microscope-40x-640x 80 BACKUP: Science Equipment
81 BACKUP: Habitat Radiation
*Habitat height provided by Chris Saccoccio Suggested thicknesses and mass/volume analysis: Preparation: ● Regolith depth of 4.3 meters ● Area of high radioactive reflectivity
Materials and Layering:
● High hydrogen polymer such as *Mass and volume based on lithium hydroxide square cm of shielding, ● Aluminum or other high Z water thickness based on structure material 1989 flare fluence ● Stored water for bulk protection ● Layers should lip at ceiling depending on attitude of sun
82 BACKUP: BFO Dose/ Radiation
83 BACKUP: O Generation 2
System ECLSS-OGS Elektron Solid Fuel (SFOG) [2],[4],[6],[7] [3],[4],[8] [5]
Power 1.44 kW/Day 1kW/Day N/A (6 people) (3-4 people)
Mass 680kg 110kg No Data (14kg/can estimate)
Volume 6.44m^3 0.2711m^3 2.712m^3 (estimate) (estimate) (four canisters)
Additional Requires about Known to function One can = one day Info 23 liters water/Day improperly requiring oxygen (1 person) more power 84 BACKUP: O Generation 2
Power Volume (255 Days) Mass (kg) Cost (USD) Notes (kW/day) (m3)
Assume water = Water N/A 3570 3.57 0 pure
KOH N/A 544.3108 0.454249 3072 N/A Use disc. rover Solar 3 UNKNOWN UNKNOWN 0 power sys. 1.25V, 100 Amp Battery 3 216 0.0943 1400 (parallel)
85 Backup: Storage Requirements
Problem: Personal supplies and basic items necessary for human survival.
Requirements: • The crew must have enough supplies for a 250-day mission. • Sufficient resources for 500 days is needed in case of emergencies.
Need to Determine: • Necessary supplies and in what quantity. • Total mass and volume of supplies. • Whether a shower is feasible or if other options should be used.
86 Backup: Storage Requirements
Mass (Mg) Volume (m3) Food 2 12 *calculated by Miles Hokanson Water (2 week 5 5 supply) Beds .36 46.1
Possible shower design: • Water will not run and drain • 1.34 m3 continuously – less water • .2 Mg will be needed. • 10.5 kW • Water must be collected 3 after each shower. • Total of 45 m resource storage needed. Mass and Volume for Clothing and Toiletries • 2 week water supply located in the habitat. Shower Rinseless Shower Total Mass (Mg) 0.894 1.39 Total volume (m3) 13.4 20.9
87 Backup: Storage Requirements
88 Backup: Human Factors
● Recreational equipment ○ ~50 kg ● Space ○ ~200 m3 ● Lighting ○ Large rooms: ■ ~8800-20500 lumens ■ ~65-160 W ■ ~0.001 m3 per bulb/array ■ ~1 kg per bulb/array w/ setup ○ Smaller rooms: ■ ~2000 - 5000 lumens ■ ~14-36 W ■ ~0.001 m3 per bulb/array ■ ~0.75 kg per bulb/array w/ setup
89 Backup: Power
90 Orbital Propellant Depot - PDR
Bryn Clarke Power and Thermal Orbital Propellant Depot February 9, 2019
91 Problem: Orbital Propellant Depot
Relevant HLRs
4 Determine the best location for fuel depots and staging (e.g. LEO, NRHO, Lagrange points).
5 Design fuel depots that are able to turn water into hydrolox.
22 Build a large scale capability of propellant production enough to return astronauts from the Moon to the Earth
(18) A Mars transfer vehicle will be designed to follow the interplanetary trajectory (described in the previous section) which includes details for V maneuvers, the propellant cost, and the interior living space. Requirements in Flux ● Need of approximately 2Mg hydrolox to loft every 1Mg to OPD means propellant production will likely be consolidated on Lunar surface (HLR 5 can be applied there) ● Possibility of OPD being removed entirely, but it is likely needed for quick fuelling of MTV
Current Problem ● Have a depot located in an orbit accessible both from the lunar surface and a Martian trajectory ● Capable of receiving 400Mg hydrolox over 4 years and storing it with minimal losses ○ and transferring it to the MTV for its interplanetary mission 92 Solution: Orbital Propellant Depot
Cryogenically Cooled, Insulated Tankage ● ZBO technology being developed by Creare for NASA can allow liquid hydrogen to be stored indefinitely ○ Liquid Oxygen easier for ZBO - the first stage alone of a 2-stage cooler in development cools to 90K ○ Additionally higher density means smaller volume (around ⅓ in extant vehicles) so less surface and struts for heat flux
Preliminary Power Reqs ● Subject to change based on actual strut requirements, and effectiveness of a potential sunshade (JWST style)
Component Power (kW) Mass (Mg) Heat Flux (kW)
MLI 0 4.91 0.0868
Cryocooler 126.7 8.87 0
Struts (CFRP, 0 ~0 2.112 8 per tank) 93 Radiator 0 2.71 -128.8 Solution: Orbital Propellant Depot
Sun-Facing Rotating Configuration ● Set. up to slowly rotate around the long axis to keep propellant against the outer edge of the tanks for the cooler and drain ● Meanwhile the solar array stays pointed at the sun and the tanks can be shaded ○ Fuel slosh might cause precession to axis of least energy; a ring configuration may be better
Structure Mass (Mg) Volume (m3)
LOX Tank 1.72 320
LH2 Tank 3.44 900
94 Propellant Depot ΔV Budget
● Produces Hydrogen/Oxygen Propellent ● Origin: 300 km LEO ○ Needs nearly constant sunlight
● Universal access for versatile use ○ Access from Earth Burn Total ΔV Flight Time ○ Access from Moon (km/s) +20% (Days) ○ Waypoint to Mars & beyond MoE
● ΔV to move Fuel Depot from Earth to desired location L1 3.977 3.855
LLO 4.716 5.015
Polar Lunar 7.373 5.175
Orbit
● Conclusion: L1 ○ Change to Eccentric Polar Orbit pending feasibility study ○ Architecture could change further Communications : Link budget analysis (for L1 orbit)
Parameter Value,dB Notes ● The propellant depot RF frequency (GHz) X band needs to communicate Distance to ground station with the communication
Data rate only the TMTC transmissions required satellites regarding the level of propellant Phase modulation index (rad/pk) present, status of its Transmit power 5 100 W TWTA required for deep space activity as well as regular Transmit Passive loss -2 telemetry and
Transmitting antenna gain 10 3m dish telecommand. ● X band is chosen for this EIRP 13 Pt Lt Gt as it the lowest frequency Path loss -222.3248641 (4 pi d f / c)^2 that has a range that Atmospheric loss -1 includes L1.
Ground antenna gain 61 Parks antenna on Earth ● The data rate is assumed to be 100 kpbs, as no Total Recieved power -149.3248641 video data is to be Data to total power -0.611317494 transmitted. Data to noise power -209.5703093 Assume noise temperature of 80 k Parameter Received Eb/ No 9.634127706 Pr + Dr -N - Datarate(dB) Antenna Gain (dB) 10.00 Required Eb/No 4
Receiver system loss -2 Antenna Diameter (m) 0.05
Link Margin 3.634127706 Antenna Beamwidth 49.17
96 Communications : Power and mass summary (for L1 orbit)
Total Unit Qty Power(W) Total mass(kg) X band transponder 2 24 6 X band TWTA 2 50 5 X band diplexer 2 0 1.2 X band Cables 0 5 X band high gain antenna 1 0 6 Total 74 23.2 Basic communication equipment required, along with the mass and power associated. (Source: Space Mission Engineering)
97 Safe Haven
Preliminary Design Review February 9, 2019 CAD and Structures
Necessary Features ● Docking Mechanisms ● Crew area ● Resources and storage ● Return module (Earth reentry) ● Radiation Protection ● Capable Engine
Overall Mass Estimate: ~14 Mg
Overall Volume Estimate: ~ 11 m3
Aaron Etterer Jack Green Structures
Crew Area 10.0 m3 Structural 10.5 Mg Volume Mass Storage 2.4 m3 Engine 2.5 Mg Volume Mass* Hardware 3.0 m3 Equipment 1.45 Mg Volume Mass Total 15.4 Total Mass 14.45 Mg Volume*
*excluding propellant mass *excludes radiation shielding/propellant tank
Jack Green Safe Haven ΔV Budget
● Move from Earth to final location ● Location: Eccentric Lunar Polar Orbit
● Respond to surface catastrophes ● Origin: 300 km LEO ○ “Reachable within a few hours”
● Mission Duration: 250 days ○ Station keeping ΔV required Burn Total ΔV (km/s) Flight Time +20% MoE (Days)
LEO - LLO 4.716* 5.015
LLO - Eccentric 0.521 0.160 Lunar Orbit
Plane Change 0.826 n/a (83.32°)*
Station Keeping 1.310 250
101H Hamilton Southworth Earth Communication Parameters
• After the discovery phase, the Safe Haven is to be used as another Smallest Earth visibility time = 2.81 h satellite in the communication satellite constellation. • This provides improved Earth coverage, increased data Total no of passes per day = 3 X 4 transmission times as well as a redundant direct link to Earth in case the communication network fails. Definition of video = 1080 p • The data rate is calculated to satisfy the high definition video communication requirements. Required bitrate = 15 Mbps [1]
Data per day = 15 X 24 X 60 X 60 Mb
Total visibility = 12 X 2.81
Data Frequency Antenna Antenna Antenna Data rate = Data per day / Total visibility rate gain diameter beamwi = 10.6762 Mbps dth
13.62 8.5 GHz 20 dB 0.16 m 15.55 Mbps (downlink),8.7
GHz(uplink) Data rate calculation for Safe Haven - Earth downlink video transmissions
Earth communication parameters.
Minduli Wijayatunga (C&C) 102 Safe Haven Human Factors
Mass (Mg) Power (Watts) Volume (Cubic Meters) Total Food 0.0571 0 0.68 Consumption Total Water Needs 0.318 0 0.62 Radiation 13.77 0 5.1 Shielding Oxygen 0.857 500 1 Habitation 0.2 250 10 Human Waste 0.025 1000 0.063
● Sustainable for 14 days ● Food and water include waste volumes ● Radiation shielding makes up habitation structure ● Oxygen includes CO2 removal ● Habitation includes sleeping, command, and seating space as well as lighting and accommodations estimates.
Parker Herman PDR: Mars Transport
Sam Evani (Prop), Aaron Etterer (CAD), Miles Hokanson (HF), Bryn Clarke (POW), Cody Hawkins (MD), Minduli Wijayatunga (COM), Pavi Ravi (Science), Austen Bowen (STRUC) Mars Transport Vehicle (MTV) February 9, 2019
104 MTV Trajectory: Cody
Phase Time (days) ΔV (km/s) OPD -> Earth Swingby 5 0.8211 Earth Departure & Mars Transit 233 0.7253 Mars Capture & Dwell 547 1.7979 Mars Orbit Reorientation 0 1.2346 Mars Departure & Transit 200 2.2245 Earth Capture & Earth -> OPD 5 1.0398 OPD Stop 0 0.8211 TOTAL 990 8.6644 TOTAL + 2% Margin 990 9.6587
Delta-v notes: Ballistic shown here, gravity assist and low thrust possible 105 Prop notes: ~300 Mg (LH2) & 800 Mg (O2) to Mars Boil Off Concerns: Sam & Bryn
Problem: Mitigate propellant boil-off Solution: Zero Boil-off system (in progress) Sun Cooler LH2 Temp < ~20K Conclusions: Shade
Passive LH2 average boil-off rate: .2% per day Multi Layer Insulation (MLI) MTV Travel time: 990 days
Loss @ 350 days in: 50% of propellant Component Power Mass Heat Flux ➢ Halfway to Mars (kW) (Mg) (kW) Loss @ 800 days in: 80% of propellant ➢ Trying to leave Mars MLI 0 4.91 0.0868
Outputs (rough estimates) Cryocooler 126.7 8.87 0 ● Active LH2 average boil-off rate: .05% per day ● Loss @ 350 days in: 15% of propellant Struts (CFRP, 0 ~0 2.112 ● Break even in mass point: ~60 days 8 per tank)
Radiator 0 2.71 -128.8
Mitigating boil-off will drive power requirements 106 Link Budget Analysis: Minduli
Martian transport > Earth (TMTC)
Parameter Value Value,dB Notes ● Ka band is used for communications, as it is of high RF frequency (GHz) 32 Ka band frequency (high range) Distance to ground station 3.74E+08 ● Data rate accommodates for telemetry and telecommand. Data rate 2.1 before error correction coding
Phase modulation index (rad/pk) 1.2
Transmit power 1000 30 100 W TWTA required for deep space
Transmit Passive loss 0.630957344 -2
Transmitting antenna gain 10 10 3m dish
EIRP 6309.573445 38 Pt Lt Gt
Path loss 2.51E+23 -2.34E+02 (4 pi d f / c)^2 Atmospheric loss 0.794328235 -1 Parameter Ground antenna gain 1258925.412 61 Parks antenna on Earth Antenna Gain Total Recieced power 2.51061E-14 -136.0022038 10.00 Data to total power 0.868696858 -0.611317494 (dB) Data to noise power 1.104E-21 -209.5703093 Assume noise temperature of 80 k Antenna 0.01 Received Eb/ No 10.82907227 9.734595028 Pr + Dr -N - Datarate(dB) Diameter (m) Required Eb/No 2.511886432 4 Antenna Receiver system loss 0.630957344 -2 49.17 Link Margin 3.734595028 Beamwidth Power and Mass budget for Communications: Minduli
Total Total Unit Qty Power(W) mass(kg)
Ka band modulator 2 3 0.6
Ka band TWTA 2 81 0.6
Ka band waveguide 0 3
Ka band high gain antenna 1 0 2.5
Ultrastable oscillator 2 5 2.6
Total 89 9.3 Human Factors: Miles
Constraints/Assumptions: • ~ 1000 day mission (according to mission design) • 6 astronauts • ⅙ g (corresponding to lunar gravity) to be provided To be considered: • Food (grow or bring) • Oxygen (Electrolysis?) • Water (recycled from moisture/urine) • Radiation protection • Waste removal • Living area and personal spaces (similar dimensions from habitat constraints? • Exercise equipment (spring/friction based) • Clothing/personal hygiene