PRESENTATIONS – GROUP 1

January 16th, 2017

1/15/2018 1

CONSIDERATIONS FOR A CITY ON MARS

Amy Comeau

Project Manager

January 16th, 2017

1/15/2018 2

THE PROBLEM: THINKING BIG

Balancing creativity with scope creep

Big picture questions:

1. How does the City deal with GCR exposure?

2. How does the City deal with planet-scale risks (i.e. war, famine, asteroids…)?

3. How does the City transport resources on the ground?

4. What types of science missions can the City conduct?

5. How do tourists/goods move between Earth and Mars?

6. How does the City make room for “the next generation”?

1/15/2018 3

SOLUTIONS1. GCR exposure

− Radiation protection in every structure

− Limiting the dose of daily radiation

2. Planet-scale risks− No war, 200 asteroid impacts a year (1-2 m in diameter) [1]

− Understanding how to store food, crop rotations, biodiversity

3. Resource transportation on Mars− Trucks, pipes, ski lifts etc.

4. Science missions− No budget! Yay!

5. Earth-to-Mars− Mass drivers− Tether sling on Mars/Phobos

6. Clearing out lava tubes− Construction equipment

− Humans vs. machines

− Spacesuits, exoskeletons, supersuits etc.

1/15/2018 4

CITATIONS

[1] Space.com Staff, “Pow! Mars Hit By Space Rocks 200 Times a Year,” Space.com [online], https://www.space.com/21198-mars-asteroid-strikes-common.html

1/15/2018 5

WATER PURIFICATION ON MARS

Adit KhajuriaResource Management - CAD representative

1/16/2018 6

THE PROBLEM

1/16/2018 7

Cl

O

O OO

Figure 1:

Perchlorate

THE SOLUTION

1/16/2018 8

Extraction Purification

• 1,000 GPD*• 30 kg*• 370W*

Figure 2: Mineral Extraction

Vehicle

Figure 3*: Reverse-Osmosis

System

* Figure and Values based on US Water Systems

AR-4-1000 [4]

CITATIONS

1. Hernandez, D., “What It Would Take To Drink The Water On Mars,” The Huffington Post Available: https://www.huffingtonpost.com/entry/drink-water-mars_us_5611efd2e4b0af3706e13449.

2. Dent, S., “NASA finds easy-to-access water all over Mars,” Engadget Available: https://www.engadget.com/2018/01/12/nasa-ice-sheets-mars-reconnaissance-orbiter/.

3. DeSliva, F., “Perchlorate Removal,” Water Quality Products Available: https://www.wqpmag.com/perchlorate-removal.

4. US Water Systems, “US Water 1000 GPD American Revolution Commercial Reverse Osmosis System | AR-4-1000,” USWaterSystems.com, Jul. 2016.

9

ROVER: MOBILE LAB

Logan Kirsch

Rover CAD

Science Support

1/16/2018

1/16/2018 10

OVERVIEW

1/16/2018 11

ROVER PARAMETERS

• Frame Mass: 3500 kg

• Internal Volume: 8.5 m3

1/16/2018 12

REFERENCES

• Williams, D., “Mars Rover "Spirit" Images,” NASA Available: https://nssdc.gsfc.nasa.gov/planetary/mars/mars_exploration_rovers/mera_images.html.

1/16/2018 13

POSSIBLE DESIGNS FOR GROUND TRANSPORT

METHODS

By: Sean Thompson

January 16, 2018

CAD for Ground Transportation

1/15/2018 14

GROUND TRANSPORTATION OPTION 1: RAIL SYSTEM

• Underground or above ground

• Need shielding if above ground

• Used for passenger to and from city

• Requires a lot of resources

1/15/2018 15

GROUND TRANSPORTATION OPTION 2: TRUCK

• Use Wheels, Tracks, or Walkers

• Used for resource collection

• Manned Vehicles

1/15/2018 16

El-Genk, M., Morley, N., “Conceptual Studies on the

Integration of a Nuclear Reactor System to a Manned

Rover for Mars Missions,” 1991.

SPACE TRANSPORTATION COMMUNICATIONS

Noah Gordon

Space Transportation | Comms & Control

January 16, 2018

1/16/2018 17

THE PROBLEM

• Communicate with space transportation vehicles

• Navigation of vehicles

1/16/2018 18

POTENTIAL SOLUTIONS

• Deep Space Network – Martian Equivalent• On Earth: 3 ground stations spaced 120 degrees

• 34-70m diameter antennas

• Alternative considerations• Ground station with aerostationary satellite

1/16/2018 19

REFERENCES

[1] “Mars Exploration Rover Mission: Communications With Earth,” Available: https://mars.nasa.gov/mer/mission/communications.html.

[2] “About - Deep Space Network” Available: https://deepspace.jpl.nasa.gov/about/#.

1/16/2018 20

GLOBAL NAV SYSTEMS

Alex Blankenberger

Communications Infrastructure – Communications Rep.

January 16, 2018

1/15/2018 21

COM INFRASTRUCTURE

• Global Communications

• Ground Stations

• Earth-Mars

1/15/2018 22

GPS VS CELESTIAL NAVIGATION

Feature GPS Celestial

Low Mass Cost - +

Precision + -

Low Complexity - +

Versatility + -

1/15/2018 23

MITCH HOFFMANN

Communication and Control

Ground Transportation

City Infrastructure

1/15/2018 24

THE PROBLEM: PLANETARY NAVIGATION• No useful magnetic field

• Difficulty of remote construction

• Circle of position ambiguity

• Lack of daytime celestial references

1/15/2018 25

Image Source: NASA.gov

A SOLUTION: INERTIAL NAVIGATION AUGMENTED BY CELESTIAL OBSERVATIONS• Drift correction

• Solar observation• Known positions

• Precision: .3 mrad (1km)

• Proven Technology

• SMAP (Size, Mass, and Power)• Volume: 48 cm^3• Mass: 100 g• Power: 2 W peak

1/15/2018 26

REFERENCE SLIDE

• SMAP: Rockwell Celestial-Inertial Precision Pointing System

• Precision• Sextant Precision: 1 arc minute (.3mrad)

• Distance precision: .0003rad x Rm = 1km

1/15/2018 27

HUMAN AIR AND WATER REQUIREMENTS FOR GROUND

TRAVEL

By Nicole FutchGround Transportation (Human Factors)

January 16, 2018

1/16/2018 28

THE PROBLEM

1/16/2018 29

THE SOLUTION

• Breathing:• 0.035 kg O2 per person, per hour

• Equivalent to 0.024 m3 (standard atm)

• No current power data from precedents

• Water (drinking):• People need to drink 0.43 kg H2O per day

• Equivalent to 0.00043 m3 (standard atm)• Passive storage, 0 W

1/16/2018 30

ADDITIONAL INFORMATION

Oxygen Calculation:

Found: 0.84kg/person/day [NASA]

0.84kg/person/day*1d/24h=0.035kg/person/hr

31

ADDITIONAL INFORMATION

Rover stock photo:

http://www.alamy.com/stock-photo-curiosity-mars-rover-artwork-65215489.html?pv=1&stamp=2&imageid=A42C6C6B-19BF-45DC-91E6-0745C4B10A9B&p=175159&n=0&orientation=0&pn=1&searchtype=0&IsFromSearch=1&srch=foo%3dbar%26st%3d0%26pn%3d1%26ps%3d100%26sortby%3d2%26resultview%3dsortbyPopular%26npgs%3d0%26qt%3dthe%2520mars%2520rover%26qt_raw%3dthe%2520mars%2520rover%26lic%3d3%26mr%3d0%26pr%3d0%26ot%3d0%26creative%3d%26ag%3d0%26hc%3d0%26pc%3d%26blackwhite%3d%26cutout%3d%26tbar%3d1%26et%3d0x000000000000000000000%26vp%3d0%26loc%3d0%26imgt%3d0%26dtfr%3d%26dtto%3d%26size%3d0xFF%26archive%3d1%26groupid%3d%26pseudoid%3d%26a%3d%26cdid%3d%26cdsrt%3d%26name%3d%26qn%3d%26apalib%3d0%26apalic%3d%26lightbox%3d%26gname%3d%26gtype%3d%26xstx%3d0%26simid%3d%26saveQry%3d%26editorial%3d1%26nu%3d%26t%3d%26edoptin%3d%26customgeoip%3d%26cap%3d1%26cbstore%3d1%26vd%3d0%26lb%3d%26fi%3d2%26edrf%3d

Solution Information: https://www.nasa.gov/pdf/146558main_RecyclingEDA(final)4_10_06.pdf

32

SIZE AND POWER ESTIMATIONS FOR NECESSARY CITY BUILDINGS

Lucas Moyer

Human Factors and City

01/16/2018

1/15/2018 33

THE PROBLEM

• Requirements for necessary components (buildings) of the city need to be determined based off demographics

• These include homes, schools, hospitals, waste management, etc.

1/15/2018 34

Age % of Population

< 18 15

18-44 40

45-64 30

65+ 15

Fig. 1: Possible

Demographics of

Future Mars

ANALYSIS AND ESTIMATES

• Homes – 4200 homes/apartments, 2.24 million m^3, 377,000 kW*hr

• Based on demographics [1] and marriage rates [9], average home [6] and apartment [5] sizes in US, and average electricity cost [4] and usage [7] in US

• Schools – 14,944 m^2• Based on student demographics and average area needed per student in different

school classifications (elem., middle, high) of US [8]

• Hospital – 15.1 patients/day• Based on demographics and US hospitalization rates [3]

• Waste – 22,000 kg/day• Based on waste production per capita of first world countries [2]

1/15/2018 35

CODEclc

clear all

%Sizing and Power Estimations for Necessary City Buildings

% Demographics

population = 10000; % total population

male_pop = 0.5*population; % male population

fem_pop = 0.5*population; % female population

child_pop = .15*population; % population under age 18

adult_18to44 = 0.4*population; % population of ages 18-44

adult_45to64 = 0.3*population; % population of ages 45-64

eld_pop = .15*population; % population of ages 65+

% Hospitalization Rates (All rates taken Overview of Hospital Stays in the US, 2012)

birthrate = 50/1000; % birthrate per 1000 women

births = birthrate*adult_18to44*0.5; % number of births

rate_child = 20/1000; % hospitilization rate of children

rate_18to44 = 75/1000; % hospitilization rate of adults aged 18 to 44

rate_45to64 = 100/1000; % hospitilization rate of adults aged 45 to 64

rate_elderly = 250/1000; % hospitilization rate of elderly

total_visits_year = child_pop*rate_child + adult_18to44*rate_18to44 + adult_45to64*rate_45to64 + eld_pop*rate_elderly + births;

mean_stay = 5; % average days in hospital

total_days = total_visits_year*mean_stay; % total days in hospital for whole population

mean_patients = total_days/365; % avg number of patients in hospital on a given day

% School Sizing

students = child_pop - .25*child_pop; % number of students

students_school = students/3; % students per school (elem, middle, high)

elem_area = 11.15; % avg area needed per elem school student

middle_area = 13.56; % avg area needed per middle school student

high_area = 15.14; % avg area needed per high school student

schools_area = students_school*(elem_area + middle_area + high_area); % total area of all schools in m^2

1/15/2018 36

CODE% Homes

% Number of Homes

couples_rate_eld = .8; % marriage rate for elderly

couples_rate_18to44 = .6; % marriage rate for ages 18 to 44

couples_rate_45to64 = .7; % marriage rate for ages 45 to 64

total_married_pop = couples_rate_eld*eld_pop + couples_rate_18to44*adult_18to44 + couples_rate_45to64*adult_45to64; % total married population

singles = total_married_pop/2 - child_pop; % total single population

homes = singles + total_married_pop/2; % total homes needed

% Area of Homes Total

apt = 70; % avg size of 1 bedroom apartment in m^2

house = 229; % avg size of house in m^2

area_total = apt*singles + total_married_pop/2*house; % total area of all homes

ceiling = 3; % ceiling height in m

vol_total = area_total*ceiling; % volume of all homes in m^3

vol_total_km = vol_total*1e-9;

% Power of Homes Total

avg_bill = 147.06; % average monthly electricity bill for one bedroom apt

avg_eleccost = .13; % cost of electricity per kW*Hr

kw_person = avg_bill/avg_eleccost/30; % kW*Hr for one day

kw_total = kw_person*population; % total kW*Hr of electricity needed per day for homes

% Waste Collection/Removal

avg_waste = 2.2; % average waste generated per person per day, in OECD countries

waste_day = 2.2*population; % total waste generated per day

waste_density = 1000; % density of waste in kg/m^3

waste_vol = waste_day*waste_density; % volume of waste per day in m^3

1/15/2018 37

SOURCES[1] Meyer, Julie A. and Howden, Lindsay M. “Age and Sex Composition: 2010”, (2011), retrieved from https://www.census.gov/prod/cen2010/briefs/c2010br-03.pdf on 1/14/18

[2] Hoornweg, Daniel and Bhada-Tata, Perinaz, WHAT A WASTE A Global Review of Solid Waste Management, World Bank, 2012, pp. 8-13

[3] Weiss, Audrey J., Ph.D and Elixhauser, Anne, Ph.D, “Overview of Hospital Stays in the United States, 2012”, (2014), retrieved from https://www.hcup-us.ahrq.gov/reports/statbriefs/sb180-Hospitalizations-United-States-2012.pdf on 1/14/18

[4] U.S. Energy Information Administration, “Electric Power Monthly”, (2017), retrieved from https://www.eia.gov/electricity/monthly/epm_table_grapher.php?t=epmt_5_6_a

[5] Otet, Ama, “As US Apartments Get Smaller, Atlanata, Charlotte, Boston Rank among Top Cities with Largest Rental Units”, (2016), retrieved from https://www.rentcafe.com/blog/rental-market/us-average-apartment-size-trends-downward/ on 1/15/18

[6] Perry, Mike J., “New US homes today are 1,000 square feet larger than in 1973 and living space per person has nearly doubled”, (2016), retrieved from http://www.aei.org/publication/new-us-homes-today-are-1000-square-feet-larger-than-in-1973-and-living-space-per-person-has-nearly-doubled/ on 1/15/18

[7] DePietro, Andrew, “Here’s What an Average Apartment Costs in 50 U.S. Cities”, (2016), Retrieved from https://www.huffingtonpost.com/gobankingrates/heres-what-an-average-apa_b_10346298.html on 1/15/18

[8] Yurko, Amy; Brown, Peter, and Cary, Mary, “Calculating School Capacity: Local, State, & National Perspectives”, (2017), Retrieved from http://www.brainspaces.com/PRES/BrainSpaces-PRES_2007-1006_Capacity-CEFPI.pdf on 1/15/18

[9] Statistical Atlas, “Marital Status in the United States”, (2015), Retrieved from https://statisticalatlas.com/United-States/Marital-Status on 1/14/18

1/15/2018 38

Mobile Radiation Protection, Vehicle Temperature/Humidity Regulation,

and Cabin Pressure Control

Kyle Tincup

Ground Transportation – Human Factors

01/16/2018

1/16/2018 39

The Problem: Survivable Environment for any Manned Vehicle

Radiation• Limit Lifetime Exposure [5]

• Threats• Solar Particle Events (SPE)• Galactic Cosmic Rays (GCR)

Temperature and Humidity Regulation• Nominal Temperature Range: 18.3 to 26.7 Degrees Celsius • Relative Humidity: Approximately 60% [2]

Pressure Control• Nominal Pressure Range: 97.906 kPa (14.2 psi) to 102.732 kPa (14.9 psi) [2]

1/16/2018 40

Kyle Tincup: Human Factors

Career Exposure Limits for NASA Astronauts

Age 25 35 45 55

Male 1.50 Sv 2.50 Sv 3.25 Sv 4.00 Sv

Female 1.00 Sv 1.75 Sv 2.50 Sv 3.00 Sv

The Solution: Radiation Shielding and Habitat Control

1/16/2018 41

Kyle Tincup: Human Factors

Radiation• Radiation Protection Using Martian Surface Materials - Martian Regolith

• “Composites of LaRC-Si/regolith and polyethylene/regolith are shown to have good structural properties as well as being effective shields from GCR radiation” [4]

• Hydrogenated Boron Nitride Nanotubes (Hydrogenated BNNTs) [3]

Temperature and Humidity Regulation• Insulation

• Martian Carbon Dioxide Insulating Medium with a Multilayer Insulation Enclosure Separated by Mylar Stand-offs

• Aerogel Material Injected Into a Lightweight Glass Fiber Structure [1]• Active Thermal Control System (ATCS)

• Heat Pipe Radiator for Day Operations• Electric Heaters for Night Operations

Pressure Control• Atmospheric Management System (AMS)

42

Thickness

g/cm^2

C3H10T1/2

Cell Death

Rate, %

C3H10T1/2

Transformation

Rate, x10^-3 %

Excess Harderian

Gland Tumor

Prevalence, %

Martian Regolith

1 3.92 1.74 3.50

5 3.28 1.65 3.28

10 2.74 1.54 3.02

30 1.89 1.34 2.63

50 1.65 1.29 2.56

Aluminum

1 3.94 1.76 3.57

5 3.33 1.70 3.37

10 2.80 1.59 3.12

30 1.91 1.39 2.73

50 1.65 1.33 2.63

Kyle Tincup: Human Factors

Appendix: Predicted One Year GCR Exposure Comparison

Values Based on Kiefer, K., Ref 4

References

1. Birur, G., Stultz, J., Tsuyuki, G. “Novel Lightweight Thermal Insulation Types for the Martian Environment: Using Carbon Dioxide Gas and Aerogel in Lightweight Enclosures,” Mar 01, 2000

2. “Environmental Control and Life Support System (ECLSS)” ESA-HSO-COU-030 Feb, 2010

3. Garner, R., “How to Protect Astronauts from Space Radiation on Mars,” Aug 7, 2017

4. Kiefer, K., “Predictions for Radiation Shielding Materials” NASA CA NCC-1-327 Dec, 2002

5. Rask, J., Vercoutere, W., Navarro, B., Krause, A., “Space Faring: The Radiation Challenge,” 2008

43

Kyle Tincup: Human Factors

EARTH TO MARS TRANSPORTATION

Andrew Blaskovich

Space Transportation

01/15/2018

1/15/2018 44

THE PROBLEM

• Transportation between Earth and Mars

• Human transportation needs to be timely

1/15/2018 45

DIRECT HOHMANN TRANSFER

• Initial assumptions: circular, in plane orbits

• ΔV Efficient (~5.7 km/s)

• Long time of flight (~8.5 months)

• Can launch every 780 days

1/15/2018 46

1/15/2018 47

1/15/2018 48

PRELIMINARY ANALYSIS OF A MARS-CERES TRAJECTORY

John Cleveland

Mission Design and Space Transportation

01/16/2018

1/15/2018 49

THE PROBLEM

• Getting to Ceres

• Potential water and mineral source

1/15/2018 50

BASELINE HOHMANN TRANSFER

1/15/2018 51

• Minimum ∆v

• 4.946 km/s ∆v

• 574.1 days in flight

• 1161 days between windows

APPENDIX: ANALYSIS

1/15/2018 52

COMMUNICATIONS INFRASTRUCTURE

Ryan Duong

1/16/18

Mission Design Specialist: Designing Satellite Communication Systems

1/16/2018 53

THE PROBLEM

Communication must be maintained amongst the city, people, s/c missions, and Earth.

• Orbit Types?

• Quantity?

• Coverage Type?

• Ground Station Locations?

1/16/2018 54

CONSTANT COMMUNICATION

First Step – Constant Colony Coverage: Areosynchronous Orbit

1/16/2018 55

Reference* Mass [kg] 1817

Reference* Power [kw] 2.8

Reference* Volume [m3] 1.5m x 1.7m x 2.1m

Solar Panel Span [m] 19.3

Created in STK *Preliminary referenced from

the geosynchronous

communication satellite: Astra

1-A

Note: Mars will require different

power requirements.

APPENDIX – ORBIT DETERMINATION

1/16/2018 56

Created in STK

APPENDIX – REFERENCE

http://space.skyrocket.de/doc_sdat/astra-1a.htm

• The Luxembourg-based Societe Europeenne des Satellites (SES) provides telecommunications services to most of Europe via American-manufactured spacecraft.

• Astra 1A is based on Lockheed-Martin (GE Astro Space) spacecraft buses, a 1.0 metric ton AS-4000 series platform. Astra 1A measures 1.5 m by 1.7 m by 2.1 m with a solar panel span of 19.3 m and 2.8 kW capacity. The spacecraft carries 16 active 45 W Ku-band transponders.

1/16/2018 57

PHOBOS AND DEIMOSMISSION TRAJECTORY

Riley Viveros

Science Support Mission Design

January 16, 2018

1/15/2018 58

THE PROBLEM

• Science Support wants to Research Moons

• Go to Phobos and/or Deimos and return with samples

• Hohmann Transfer there and back

1/15/2018 59

ANALYSIS

• 150 kilometer parking altitude

• Phobos ΔV = 2.530075 km/s

• Deimos ΔV = 3.528340 km/s

• 10000 kilogram spacecraft

• Fuel is Liquid Methane

• 5768.32 kg propellant, 7.9199 m^3

• 6985.95 kg propellant, 9.5917 m^3

1/15/2018 60

OTHER VALUES

• Density of Liquid Methane: 422.62 kg/m^3

• LOX Oxidizer density: 1141 kg/m^3

• m0/mf (from rocket eqn):• Phobos – 2.36313

• Deimos – 3.317799

• Ox:Fuel Mass Ratio is 2:1

• Transfer Arc Period• Phobos – 4.38 hours

• Deimos – 13.23 hours

1/15/2018 61

ASSUMPTIONS

• Inplane: Moons only inclined 1 degree wrt Mars

• Circular Orbit: Phobos and Deimos has eccentricities of 0.0151 and 0.0002 respectively

• +/- 250 km

• 10000 kg initial spacecraft mass

• Isp of 300 seconds

1/15/2018 62

FUTURE ANALYSIS

• See if potential to find more optimal trajectory (Minimum energy lambert arc)

• Get better estimate for mass and Isp

• 3D & elliptical analysis

• Find more efficient fuel (hydrazine if available resources)

1/15/2018 63

ROVER: MOBILE LAB

Jonathan Bensman

Power and Thermal Management

Science Support

1/15/2018 64

BASIC REQUIREMENTS

• Battery Powered (No fossil fuels)

• Designed for half to full day trips• 12 to 16 hour days

• Used to help study the geological history of Mars

• RV style vehicle

1/15/2018 65

BATTERY CHOICE: TESLA’S P100D BATTERY

• One provides 100 kWh of energy [1]

• Tesla’s new semi using 12 of these [2]• Gives a range of 400 mi with 80,000 lbs

• Weigh approx. 1,200 lbs or 544.3 kg (each) [1]

1/15/2018 66

QUESTIONS?

1/15/2018 67

RV BASIC INFO [3] (EXTRA)

• Weight (GVWR): Approx. 40,000 lbs

• Includes space for:• 255-gallon liquid tanks

• 36-gallon gas tanks

• Half of what the Tesla semi would pull with all 12 batteries

1/15/2018 68

REFERENCES

1. Model S Specifications. (2017, September 25). Retrieved January 15, 2018, from https://www.tesla.com/support/model-s-specifications

2. Bower, G. (2017, April 10). Tesla Semi Truck Battery is How Big? Retrieved January 15, 2018, from https://insideevs.com/tesla-semi-truck-battery-is-how-big/

3. 2018 Tiffin RV Phaeton 40IH for Sale in Fort Worth, TX 76117 | JA117884. (n.d.). Retrieved January 15, 2018, from https://www.rvusa.com/rvs-for-sale/2018/tiffin-phaeton-40ih-class-a-new-fort-worth-texas-76117-2134882

1/15/2018 69

FISSILE MATERIAL ON MARS

Will Chlopan

Resource Extraction

Power and Heat

1/16/2018

1/15/2018 70

THE PROBLEM

• Nuclear fission reactor is potential power source

• LWR (Light Water Reactors) generate 400 million kWh of fuel per metric ton of LEU (Low Enriched Uranium) fuel

• 10 tons of uranium are needed to produce 1 metric ton of LEU

1/15/2018 71

URANIUM ON MARS

• Approximately 1.1 to 0.8 ppm in volcanic rocks

• Alternative: Thorium• 5 to 2.5 ppm in volcanic rocks

• Uranium 233 is synthesized from Thorium

• Cleaner, but requires more processing

• Relatively experimental technology

1/15/2018 72

SOURCES

Fetter, S., “How long will the world's uranium supplies last?,” Scientific American Available: https://www.scientificamerican.com/article/how-long-will-global-uranium-deposits-last/.

Bazilevskii, A. T., Moskaleva, L. P., Manvelian, O. S., and Surkov, I. A., “Evaluation of the thorium and uranium contents of Martian surface rock - A new interpretation of Mars-5 gamma-spectroscopy measurements,” 1981.

Mathieu, L., Heuer, D., Brissot, R., Garzenne, C., Le Brun, C., Lecarpentier, D., Liatard, E., Loiseaux, J. M., Meplan, O., and Merle-Lucitte, E., “The thorium molten salt reactor : Moving on from the,” Jun. 2005.

1/15/2018 73

Power Distribution for EARTH-MARS CYCLER

Faiz FerozPower & Thermal and Space Transport

January 16, 2018

1/11/2018 74

The Problem

Considering time, people, etc.,

Systems:• Life Support• Communication Systems• Avionics

1/11/2018 75

Providing/Consuming Power

Average Household: 897 kWh per month (electric bills)

Solar Arrays: 1 panel, 33 m^2, 1750-2450 W/m*2

Lithium-Ion Batteries:~20-30 Volts, size depends on application,

1/11/2018 76

CYCLER: MARS TRANSPORT

Tyler Duncan

Propulsion and Space Transportation

January 16, 2018

1/16/2018 77

THE PROBLEM

▪ Number of People Transporting

▪ Engine Type

▪ Transporter Connecting with the Cycler

1/16/2018 78

THE SOLUTION

• 100 People

• Propellant: LOX/Liquid Methane

1/16/2018 79

Propellant Mass [kg] 35,882

Propellant Volume [m3] 27,363

*Power [MW] 80

*Based off SpaceX Raptor Rocket

APPENDIX - CALCULATIONS

1/16/2018 80

APPENDIX - REFERENCES

• [1] “SpaceX Raptor – SpaceX | Spaceflight101,” SpaceXSpaceflight101 Available: http://spaceflight101.com/spx/spacex-raptor/.

• [2] Elert, G., “Mass of an Adult,” Mass of an Adult - The Physics Factbook Available: https://hypertextbook.com/facts/2003/AlexSchlessingerman.shtml

• [3] NASA Available: https://spaceflightsystems.grc.nasa.gov/education/rocket/specimp.html.

• [4] Gases - Density Available: https://www.engineeringtoolbox.com/gas-density-d_158.html.

• [5] Szondy, D., “Elon Musk presents updated plan for Mars colonization,” New Atlas - New Technology & Science News Available: https://newatlas.com/elon-musk-mars-update-mars/51558/.

1/16/2018 81

Mars Propellant Production

Diego A. MartinezResource Extraction - Propulsion

1/11/2018 82

The Problem

How do we provide propellant for rockets launched from Mars surface?• Mars Cycler• Launch Vehicle for satellite

missions (COMMs, resource extraction, science)

1/11/2018 83

Methane + LOX for Fuel/Oxidizer

Sabatier Reaction + 2 Reverse Water Gas Shift6𝐻2 + 3𝐶𝑂2 → 2𝐶𝑂 + 𝐶𝐻4 + 4𝐻2𝑂

Prop Production Rate: 1 kg/day per unitUnit Mass: 50 kgPower Consumption per unit: 700 W

Note: Numbers based on IMISPPS design (Zubrin, Muscatello, Berggren)

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PRELIMINARY COMMSPLACEMENT AND MOVEMENT

Presented by: Connor Lynch

Discipline: Propulsion

Team: Comms Infrastructure

January 16, 2018

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THE PROBLEM

• Satellite constellation necessary for global coverage

• Relays

1/16/2018 86Image courtesy of rebrn.com

MOVING FORWARD

• Launch from Earth

• Atlas V Launch Vehicle• 1st Stage: RD-180 engine, RP-1/LOX• 2nd Stage: RL10 engine, LH2/LOX

• RCS: R-4D quad thrusters, MMH/NTO

• Mass: 334,600 kg (per launch)

• Volume: 1178 m3 (per launch)

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Photo courtesy of Alan Walters

Image courtesy of Wikipedia

MORE DETAILED SPECS

• Atlas V• Mass: 334,423 kg• Volume: 1172.207 m3

• Height: 59.7 m• Diameter: 5 m

• RCS• Mass: 164 kg (100 kg prop, 4 quads of 16 kg)• Volume: ~ 2 m x 1.5 m x 0.5 m = 1.5 m3 each

quad, x4 = 6 m3

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Annie Ping

Science Support / Propulsion

January 16, 2018

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ENGINE TRADE STUDY FOR SCIENTIFIC MISSIONS

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THE PROBLEM

• Determine engine for scientific missions

• Provide initial propellant mass and volume estimations

• Assumptions:• Delta-V = 2.53 km/s for Phobos

• Initial mass of s/c = 10,000 kg

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ENGINE TRADE STUDY

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Engine Vehicle PropellantPropellant

Mass [kg]

Propellant

Volume [m3]

Raptor SpaceX ITS CH4 / LOX 9892.4 11.74

RL-10B-2

Delta III

Delta IV

SLS

LH2 / LOX 7476 20.66

J-2X SLS LH2 / LOX 7783.5 21.51

Engine Criteria:

• From the U.S.

• CH4 / LOX or LH2 / LOX

REFERENCES

• “Comparison of orbital rocket engines,” Wikipedia Available: https://en.wikipedia.org/wiki/Comparison_of_orbital_rocket_engines.

• Braeunig, R.A., “Rocket Propellants,” Basic of Space Flight Available: http://www.braeunig.us/space/propel.htm

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MASS AND VOLUME ESTIMATION

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Engine Vehicle PropellantPropellant

Mass [kg]

Propellant

Volume [m3]

Raptor SpaceX ITS CH4 / LOX 16094 19.10

RL-10B-2

Delta III

Delta IV

SLS

LH2 / LOX 11782 32.56

J-2X SLS LH2 / LOX 12318 34.05

Delta-V = 3.53 km/s for Deimos

ScienceAlaina Glidden

Science Support: Composition of Phobos and Deimos

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The Problem: What are they and where did they come from

Captured Asteroids● Reflectance spectra in the visible/IR spectrum of both moons

shows them either being brighter in the IR or visible○ Shows similarities with carbonaceous meteorites○ Does not give lead to composition, just slope in the spectra

● Low bulk density may suggest that they are very porous.○ Consistent with shattering and reassembling event.○ ~10% water composition

In Orbit Formation from Debris● Orbits are near-circular and near-equatorial whereas captured

asteroids should have elliptical, inclined orbits○ Tidal dissipation could account for the lower energy orbits

but is not likely● To get both moons this way, would need the accretionary disk to

extend past the synchronous orbit of Mars (6 RM)

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Alaina Glidden: Science

The Solution: Go there and get samples!

History and Origins● Having samples will tell us the relative abundances of common

meteoritic material and martian material● Knowing where they came from will tell us more about how

moons form in the solar system and in the universe

Usable Resources● Possibility of H2O and OH could provide water for humans or

hydrogen fuel for power● Other minerals and resources possibilities

Advantages of Sample Return● More accurate analysis● Controlled conditions in which to do experiments● Experiments can be easily repeated and modified

96

Alaina Glidden: Science

Captured Asteroids: Reflectance Spectra• Red unit (left) brighter in near-infrared• Blue unit (right) brighter in visual• Similar to D or T-type carbonaceous asteroids from the

outer belt and Trojans of Jupiter• Nice Model (Tsiganis et al. 2005) supports the

migration of outer belt asteroids inwards• Discrepancies between Phobos’ spectrum and the spectra

of D and T-type asteroids could be from weathering

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Alaina Glidden: Science

Captured Asteroids: Challenges• Spectra of moons does not match low-albedo carbonaceous

meteorites• CI/CM carbonaceous chondrites fit the blue unit spectrum of

Phobos but, the 3µm band is missing in Phobos’ spectrum.• Missing 3µm band means that Phobos is either non-

hydrated or has been dehydrated in the past• When testing current similar meteorites for space

weathering, their spectra had been altered to show a subdued 3µm band. Therefore, the absence of the 3µm band for Phobos could be from space weathering.

• When testing for weathering, the red unit spectrum could not be reproduced.

• Must conclude that there are currently no analogous materials to Phobos and Deimos in our current meteorite collection

98

Alaina Glidden: Science

Captured Asteroids: Porosity and Water Content

• Phobos is currently not big enough to compress the current analog material of D-type asteroids to Phobos’ bulk density.

• Therefore, Phobos cannot be a captured D-type asteroid.• Suggests the moons are gravitational aggregates of loosely

consolidated material (rubble piles)• Porosity could also increase the rate of tidal dissipation

(good for capture scenario)• Low density could also be explained by a higher water content.

• Could be 10%-35% water but closer to 10% • This water content is low because, objects near Jupiter’s

orbit should be about 1/3 water by mass

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Alaina Glidden: Science

In Orbit Formation: Their Orbits

100

Alaina Glidden: Science

Moon Phobos Deimos

Eccentricity

(elliptical/circular)

0.0549 0.0151 0.0005

Inclination from

Ecliptic

(tilt of orbit)

5.145º 26.04º 27.58º

Inclination from

Equator

18.28º-

28.58º

1.08º 1.79º

Data from https://nssdc.gsfc.nasa.gov/planetarry/factsheet/moonfact.html

*Note: We currently think that the Moon formed form a disk of debris around

the earth that formed from a giant impactor so it is reasonable to assume

that the orbital parameters of the Moon would give a good baseline to

compare the orbital parameters of Phobos and Deimos.

For a moon that formed from a

disk of debris, we would expect:

• Near-circular orbit (low

eccentricity)

• Near-equatorial orbit (low

inclination)

*Note: Remember that the tilt of the

Earth’s axis changes over time so the

inclination of the Moon relative to the

equator will also very a lot with time.

References

101

Alaina Glidden: Science

Murchie, S. L., Britt, D. T., and Pieters, C. M., “The value of Phobos sample

return,” Planetary and Space Science, vol. 102, Apr. 2014, pp. 176–

182.

NASA Available:https://nssdc.gsfc.nasa.gov/planet ry/factsheet/moonfact.html.

Pieters, C. M., Murchie, S., Thomas, N., and Britt, D., “Composition of Surface

Materials on the Moons of Mars,” Planetary andSpace Science, Vol. 102,

Nov. 2014, pp. 144–151.

Rosenblatt, P., “The origin of the Martian moons revisited,” The Astronomy

and Astrophysics Review, vol. 19, Aug. 2011, pp. 19–44.

POTENTIAL EFFECTS OF D/H RATIO OF WATER

Megan HarwellScience Support, Resource Extraction

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PROBLEM:• Will Deuterium/Hydrogen ratio in our

water source have adverse affects on inhabitants?

• Change in density of

Edolymph fluid in

inner ear changes

buoyancy of cupula

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POTENTIAL SOURCE OF DIZZINESS, NAUSEA

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• Earth’s water source

likely Chondritic

meteoroids

• Mars’ D/H ratio has

increased with

atmospheric loss

• Body equilibrates

in 5-6 hours

Planetary Body D/H ratio

Earth 1.5576×10-4

Oort-cloud comets (2.96±0.25)×10-4

Carbonaceous Chondrites (1.4±0.1)×10-4

67P/Churyumov–

Gerasimenko

5.3 ×10-4

Comet 103P/Hartley 2 (1.61±0.24)×10-4

SOURCES:[1] Hallis, L. J. “D/H Ratios of the Inner Solar System.” Philosophical transactions. Series A, Mathematical, physical, and engineering sciences 375.2094, 2017, 20150390.

[2] Altwegg, K. et al. “67P/Churymov-Gerasimenko, a Jupiter family comet with a high D/H ratio” Science, 1261952, Dec 2014

doi: 10.1126/science.1261952

[3] Money, K. E., Myles, W. S. “Heavy water nystagmus and effects of alcohol” Nature, Vol. 247, Feb. 1974, pp. 404-405.

doi:10.1038/247404a0

[4] Brandt, T. “Positional and positioning vertigo and nystagmus” Journal of the Neurological Sciences, Vol. 95, No. 1, Jan. 1990, pp. 3-28.

doi: 10.1016/0022-510X(90)90113-2

[5] Shubin, N. “The universe within: the deep history of the human body” 1st ed., Vol. 1, Vintage, New York, 1013, pp. 3–7

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BUILDING UNDERGROUND ON MARS

Halen Blair

City Infrastructure, Structures

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PRINCIPLES AND SPACE AVAILABLE• Gravity 37.8% of Earth, so estimate lava tube as

semicircle of radius 7.5 meters (50% larger than Earth)

• Stresses placed on building supports are going to be less

• Masses cause less force on structure than on Earth

• “Cost” of self supporting is less

• Limited vertical and horizontal space in tube

• Buildings must be either long or compartmentalized

• Ability to use weaker building materials like aluminum

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PROOF OF CONCEPT• Two story frame structure to fit in lava tube.

• 10 meter by 10 meter square floor with 3 meter walls.

• Conservatively estimating our loading, each of the four supporting legs must hold 60 kN of compressive force.

• Using the equations for buckling of a fixed end aluminum beam, and of the second moment of inertia assuming a square cross section, we can find a required side width of 4 cm.

• Using the density of aluminum and the volume of the required beams, we find the building frame has a mass of 622 kg

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FOOD STORAGE

Swapneel Kulkarni

Food Production

Structures

January 16, 2018

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Requirement

• Grain – Large Farm Bins, Warehouse Units, Underground Storage

• Animal/Bug – Aviary, Barn, Coop, Dairy

• Water – Large Water Tanks

• Plants – Greenhouses

Factors of Influence• Martian Environment

o Atmospheric Pressure – 600 Pa

o Gravitational Force – 0.376g

o Gaseous composition of Environment – 95% Carbon Dioxide

o Temperature Extremes and Fluctuations – 215 K to 293 K

• Frequency of dust storms, tremors and other natural phenomena

• Rock Formations, Aridity of land, proximity to volcanic areas, etc.

• Required volume and quantity

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Basic Materials• Concrete

o 2400 kg per cubic meter density and 40 Mpa compressive strength

o 50% Sulphur and 50% Martian Soil, max. aggregate size of 1 mm

o Compressive Strength in excess of 50 Mpa

o Can be recycled by heating

• Steelo 8050 kg per cubic meter density and 250 Mpa compressive strength

o 0.05% and 2.1% Carbon

o Abundance of CO2 and Iron on Martian surface

• Glasso 2500 kg per cubic meter density and 1000 Mpa compressive

strength

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INITIAL ANALYSIS OF GROUND BASED

COMMUNICATION STRUCTURES

Stuart McCrorieStructures

Communications Infrastructure1/16/2018

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THE PROBLEM

• Communication on the entirety of Mars’ surface for Science Teams

• Multiple methods• Continuous satellite coverage• Ground-based towers• Fiber-optic Cable

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GROUND-BASED TRANSMISSION TOWERS

Physical Towers to provide universal coverage

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Estimated Number of Long

Range Towers

44 towers

Estimated Number of Short

Range Towers

712 towers

Required Mass 334,000 kg (28,350 kg

just Long Range Towers)

Required Volume 41,500 m3 (3,500 m3 just

Long Range Towers

Required Power 7,120 kW per hour

STRUCTURAL DESIGN FOR GROUND TRANSPORTATION

Eric Thurston

Ground Transportation – Structures

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THE PROBLEM – IMPLICATIONS OF VEHICLE CHOICE

• Rail, rover or other?

• Manned or Unmanned?

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OPTIONS FOR VEHICLE STRUCTURES

• Shielded vehicles ~ 1500 kg/person

• Titanium & Aluminum frame• Curiosity rover = 899 kg

• Steel rails ~ 60 kg/m

• Local, low-tech alternatives• Mars bricks

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APPENDIX - CALCULATIONS

• Rail Mass• Steel density = 7.85 g/cm^3

• Cross-section area = 40 cm^2 * 2 rails

• Mass = 7.85*80 = 628 g/cm = 62.8 kg/m

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APPENDIX - SOURCES1. Bell, T., “Metals on the Mars Rover Curiosity,” The Balance Available:

https://www.thebalance.com/metals-on-the-mars-rover-curiosity-2340049

2. “Rail Profile,” Rail System Available: http://www.railsystem.net/rail-profile/

3. “Rover - Mars Science Laboratory,” NASA Available: https://mars.nasa.gov/msl/mission/rover/

4. “Surface Exploration Vehicle Concept” Available: https://www.nasa.gov/pdf/464826main_SEV_FactSheet_508.pdf

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FUTURE RESEARCH

• Types of materials available vs. useable materials

• Detailed study for mass of human rated vehicle

• Develop ideas for reliable vehicle manufacturing and maintenance on Mars

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