GROUP 2 PRESENTATIONS

February 27th, 2018

2/27/2018 1

FINALIZING PROJECT DESIGN

Ricardo GomezAssistant Project Manager

Feb 27th, 2018

2/27/2018 2

PROBLEM: FINDING FOCUS

• It can be easy to focus on optimizing small details within each system instead of solving the main unresolved design changing aspects of the system

• Solving the issues that affect other systems for last can cause other teams to miss their deadlines

• Periods of decreased productivity can arise after finishing CDR due to the satisfaction of finishing an arduous task

2/27/2018 3

• Science Support:• Redesign rovers for science missions• Find Resources required for labs• Make final selection of science sites

• Ground Transport:• Finish analysis of total rail

infrastructure and replenishing rates• Coordinate with resources and

manufacturing to assure amounts of resources and materials can be transported.

• Space Transport:• Conduct analysis for smaller launch

vehicle• Finalize total number of launches per

year and resources required• Comms Infrastructure:

• Finalize station keeping analysis and size propellant tanks accordingly

• Work with space transport to coordinate number of launches required2/27/2018 4

SOLUTION: CLARIFYING PRIORITIES• City:

• Finish power analysis• Finalize required resources to maintain

city• Make city a joy to live in

• Food:• Finish mushroom mechanisms and

corresponding resources• Finalize outputs to other systems

• Resources:• Finalize lifecycle requirements and

materials required to maintain system• Coordinate with manufacturing to

assure provided rates match required manufacturing output

• Manufacturing:• Continue analysis on manufacturing

processes• As other systems finalize design, start

to finalize manufacturing requirements for different materials

WATER PIPELINE DESIGN AND ANALYSIS

Islam NazmyCOMMS

Resource Extraction02/27/2018

2/27/2018 5

PIPELINE REQUIREMENTS

• Designing a water pipeline to transport water from Martian icecaps to our city

• 200 km pipeline [Stephen Kubicki, JMARS]• 800m downhill [Stephen Kubicki, JMARS]

• Water is entering at 700 Pa, 5 ºC [Will Chlopan]• Flow rate: 3.27 kg/s [HF Requirements]

Water must come into a closed system at ambient pressure (100 kPa), and temperature must remain above 0 ºC throughout the pipeline.

• Pressure losses from friction.• Temperature loss to atmosphere.

2/27/2018 6

PIPELINE DESIGN AND ANALYSIS

2/27/2018 7

• Diameter = 0.5m• Re = 5499.9 (turbulent>4000)• V = 0.0167 m/s

• PVC lining (0.0015 mm)• Heat tracing to heat flow.

Temperature Change [ºC]

-0.01445

Pressure Change [kPa] 3005.76

Table 1: Analysis of pipeline for an insulated 0.5m diameter pipeline using Aspen Plus [3].

Per station Full pipeline

Pressure in [kPa] 430.094 0.700

Pressure out [kPa] 100.0 100.0

Power produced [kW] 1.0794 7.556

Temperature change [ºC] 0.0789 0.5520

Table 2: Performance of each turbine for seven turbine/heating stations along pipeline, every 28.6km.

Figure 1: Rendering of heat tracing around pipe [Adit Khajuria].

Figure 2: Rendering of pipe turbine blades [Adit Khajuria].

REFERENCES[1] “Hydropower” Available: https://www.engineeringtoolbox.com/hydropower-d_1359.html.

[2] “Reynolds Number & Pipe Flow,” Turbulent FlowAvailable: https://ocw.mit.edu/courses/mechanical-engineering/2-000-how-and-why-machines-work-spring-2002/study-materials/TurbulentFlow.pdf.

[3] Robert Econs, personal communication, Februrary 24, 2018.

[4] “Water - Viscosity table and viscosity charts,” ViscopediaAvailable: http://www.viscopedia.com/viscosity-tables/substances/water/.

2/27/2018 8

APPENDIX A – ICE CAP WELL

2/27/2018 9

Water Collection pipelineTotal Flow: 3.27 kg s-1

CAD images made by Adit Khajuria

APPENDIX B – ADVICE FROM CHEMICAL ENGINEERS [3]

• Due to such a high pressure increase, we should spread out the turbines along the pipe.

• Temperature losses are close to negligible because of the extremely thin atmosphere.

• Consider using iron as radiation shielding; carbon-carbon bonds break easily from GCR.

• Keep velocity low to reduce pressure losses from friction, but high enough for turbulent flow.

• Turbulent flow causes mixing; we can assume consistent temperature across our pipe.

• Turbulent flow is inevitable; may as well use it.

2/27/2018 10

APPENDIX C – PIPELINE SIMULATIONzero dz

Units WATERIN WATEROUTFrom SAMSPIPE

To SAMSPIPESubstream: MIXEDPhase: Liquid LiquidComponent Mole FlowWATER KMOL/HR 653.4453 653.4453Mole Flow KMOL/HR 653.4453 653.4453Mass Flow KG/HR 11772 11772Volume Flow L/MIN 193.673 193.673Temperature C 5 5Pressure BAR 1 0.9801453Vapor Fraction 0 0Liquid Fraction 1 1Solid Fraction 0 0Molar Enthalpy CAL/MOL -68613.9 -68613.9Mass Enthalpy CAL/GM -3808.65 -3808.65

Enthalpy Flow CAL/SEC -12454000 -12454000

Molar Entropy CAL/MOL-K -40.17895 -40.17895Mass Entropy CAL/GM-K -2.23027 -2.23027

Molar Density MOL/CC 0.0562327 0.0562327Mass Density GM/CC 1.013048 1.013048

Average Molecular Weight 18.01528 18.015282/27/2018 11

APPENDIX C – PIPELINE SIMULATION

2/27/2018 12

with dz

Units WATERIN WATEROUT

From SAMSPIPE

To SAMSPIPESubstream: MIXEDPhase: Liquid LiquidComponent Mole FlowWATER KMOL/HR 653.4453 653.4453Mole Flow KMOL/HR 653.4453 653.4453Mass Flow KG/HR 11772 11772Volume Flow L/MIN 193.673 193.673Temperature C 5 5Pressure BAR 1 80.45699Vapor Fraction 0 0Liquid Fraction 1 1Solid Fraction 0 0Molar Enthalpy CAL/MOL -68613.9 -68613.9Mass Enthalpy CAL/GM -3808.65 -3808.65

Enthalpy Flow CAL/SEC -12454000 -12454000

Molar Entropy CAL/MOL-K -40.17895 -40.17895Mass Entropy CAL/GM-K -2.23027 -2.23027

Molar Density MOL/CC 0.0562327 0.0562327Mass Density GM/CC 1.013048 1.013048

Average Molecular Weight 18.01528 18.01528

Note: this pressure gain is for Earth gravity. Multiply by 3.711/9.81 to change to Martian gravity.

APPENDIX D – POWER DESIGN CODE

2/27/2018 13

Polyvinyl (PVC) Manufacturing

William AdamsStructures Discipline

Resource Extraction and Manufacturing2/27/18

2/27/2018 14

The Problem

• PVC will be needed for use in construction and piping• Resources water pipe will require 70 kg/year (Islam

Nazmy)• Food production will require 180,700 kg (Jonathan

Rowher)

• Finding a feasible process that works on Mars as well as the materials needed• Ethylene • Chlorine (Resource Extraction produces 4.9 Mg/day)

• Health and safety aspects of production• Toxic chemicals like dioxin, hydrochloric acid, and vinyl

chloride are a byproduct

2/27/2018 15

The Solution• Suspension polymerization• Ethylene and chlorine react to form ethylene

dichloride• This is heated into a vinyl chloride monomer gas (VCM)

• Polymerization links VCM molecules into chains of PVC

• Additives are mixed to the PVC resin• Plasticizers, stabilizers, lubricants, fillers

2/27/2018 16

Mass Inputs: 2.9 Mg Chlorine2.24 Mg Ethylene

Power: 47 MJRate: 2 hours

Production of 1 Mg of PVC

CAD By Adit Khajuria

Appendix – Waste Emissions

17

Carbon Dioxide (CO2) 12.239 kgCarbon Monoxide (CO) 14.386 kgMethane (CH4) 14.141 kgHydrogen (H) 22.784 kgNitrogen (N) 3.524 kg

Waste output per 1 kg of produced PVC

References

• [1] “About PVC & The Industry,” Fendeck and Rail Available: http://www.pvcfencing.co.za/about-pvc-the-industry/.

• [2] “Eco-Profiles of the European Plastic Industry,” PlasticsEurope Available: http://www.inference.org.uk/sustainable/LCA/elcd/external_docs/epvc_31116f09-fabd-11da-974d-0800200c9a66.pdf.

• [3] Morawicki, R. O., ”Working on the Impacts,” Handbook of Sustainability for the Food Sciences, Somerset: Wiley, 2011, p. 295.

• [4] “PVC Production,” APM Solutions Available: http://apm-solutions.com/industries/pvc-production/.

• [5] “What is Polyvinvyl Chloride?,” Lenntech Water Treatment & Purification Available: https://www.lenntech.com/polyvinyl-chloride-pvc.htm.

18

LOOKING TO METEORITES FOR RESOURCES

Megan HarwellScience

Resource ExtractionFebruary 27, 2018

192/27/2018

PROBLEMAre meteorites a reliable solution for resource requirement gaps?• Many of the required rare-Earth elements have an unknown abundance in

the Martian soil• Meteorites populate the surface of Mars [1]• Minimal weathering on surface of Mars leads to a higher likelihood of useful

samples [1]Approach• Constrain distribution of meteorites on the surface

• 500 – 50,000 meteorites/km^2 of meteorites 10 g or greater on the surface of Mars [1]• Colder, thinner atmosphere has slowed chemical weathering [1]

• Extrapolate composition of meteorites on surface from asteroid belt• Chondritic (~75%), Stony (~17%), Iron (~3%), HED (~5%)

• Determine contribution of micrometeorites to surface soil• 1.2% C1 chondrite composition as a uniform surface soil layer [2,3,4]2/27/2018 20

SOLUTION: METEORITE AT SITES

21

~750 km

Material Required by whom

Amount needed (Mg/day)

Expected Yield (Mg/day)

Met?

Molybdenum (Mo) Manufacturing, Food

6.19E-07 1.1025E-07 X

Chromium (Cr) City, GT, ST, Manufacturing

0.00656 2.3625E-06 X

Plantinum (Pt) GT, ST 0.005 2.47E-09 X

Beryllium (Be) City, GT, SC, Food 0.005 2.06E-05 X

Lithium (Li) City, GT 0.166 0.0032 X

Vanadium (V) City, GT 0.096 0.117 ✔

Cobalt (Co) ST, Food 0.039 1.167 ✔

2/27/2018

Using the dragline excavator already in use at resource extraction sites will not output enough meteoritic material yield to fill the gap.

APPENDICES

22

Assumptions: • meteorite flux material is of the same average composition as the asteroid

belt/known asteroids. • Accumulation of meteorites in Bland & Smith (2000) is within the top meter of soil

on Mars. Assume resulting craters have widely been erased by aeolian processes• Chemical Weathering of meteorites on Mars occurs on a 10^9 year timescale

(Bland & Smith, 2000)• Assume uniform weathering rate for Stony, iron, and chondritic meteorites

2/27/2018

Type % in main belt low high middle ground m/sq m m/m^3

5.00E-04 5.00E-01 0.2 kg

Carbonaceous 0.75 3.75E-04 2.81E-04 0.000328 6.56E-08 6.5625E-08

Stony 0.17 8.50E-05 6.38E-05 7.44E-05 1.49E-08 1.4875E-08

Iron 0.03 1.50E-05 1.13E-05 1.31E-05 2.63E-09 2.625E-09

HED 0.05 2.50E-05 1.88E-05 2.19E-05 4.38E-09 4.375E-09

For iron wt % Mg/dayMo 0.0007 1.8375E-10Cr 0.015 3.9375E-09Pt 9.42E-05 2.47275E-11

For chondrites wt % Mg/day

Se 0.00214 1.40438E-08

V 0.0045 2.95313E-08

WEIGHT % CONTRIBUTION IN SOIL

2/27/2018 23

microg/g weight % Soil weight %Li 1.44 0.00000144 0.000296 3.55277E-06Be 0.0225 2.25E-08 4.63E-06 5.55121E-08P 989 0.000989 0.203339 0.002440064K 519 0.000519 0.106707 0.001280479Sc 5.8 0.0000058 0.001192 1.43098E-05Ti 447 0.000447 0.091903 0.00110284V 52.3 0.0000523 0.010753 0.000129035Mn 1878 0.001878 0.386117 0.004633408Co 519 0.000519 0.106707 0.001280479Cu 127 0.000127 0.026111 0.000313335Zn 298 0.000298 0.061269 0.000735227Ga 9.42 0.00000942 0.001937 2.32411E-05Rb 2.23 0.00000223 0.000458 5.50186E-06Sr 7.61 0.00000761 0.001565 1.87754E-05Y 1.54 0.00000154 0.000317 3.79949E-06Zr 3.49 0.00000349 0.000718 8.61054E-06Nb 0.292 2.92E-07 6E-05 7.20423E-07Cs 0.182 1.82E-07 3.74E-05 4.49031E-07Ba 2.48 0.00000248 0.00051 6.11866E-062/27/2018

SOURCES[1] Bland, P.A., Smith, T.B., “Meteorite Accumulations on Mars,” Icarus, vol. 144, 2000, pp. 21-26. Doi: :10.1006/icar.1999.6253[2] Yen, A. S., Gellert, R., Schröder, C., Morris, R. V., Bell III, J. F., Knudson, A. T., Clark, B. C.,, Ming, D W., Crisp, J A., Arvidson, R E., Blaney, D,, Brückner, J,, Christensen, P R., DesMarais, D J., de Souza Jr, P A., Economou, T E., Ghosh, ,, Hahn, B C., Herkenhoff, K E., Haskin, L A., Hurowitz, J A., Joliff, B L., Johnson, J R., Klingelhöfer, G, Madsen, M B, McLennan, S M., McSween, H Y.,Richter, Lutz, Rieder, Rudi, Rodionov, Daniel, Soderblom, Larry, Squyres, Steven W., Tosca, Nicholas J., Wang, Alian, Wyatt, Michael, Zipfel, Jutta. “An integrated view of the chemistry and mineralogy of martian soils,” Nature. Vol. 436, 2005, 49.doi: 10.1038/nature03637[3] Flynn, G. J., McKay, D. S. “An assessment of the meteoritic contribution to the martian soil. “J. Geophys. Res. 95, 14497–14509 (1990)[4] Yen, A. S. “Composition and color of martian soil from oxidation of meteoritic material.” Lunar Planet. Sci. Conf. XXXII, 1766 (2001)[5] Youngmin JeongAhn, Renu Malhotra, “The current impact flux on Mars and its seasonal variation,” Icarus, 2015, 262, 140[6] Barrat, J.B., Zanda, B., Moynier, F., Bollinger, C., Liorzuo, C., Bayon, G. "Geochemistry of CI chondrites: Major and trace elements, and Cu and Zn Isotopes," Geochimica et Cosmochimica Acta, Elsevier. Vol. 83, 2012, pg. 79-92. [7] Beaulieu, P. L., Moore, C. B., “Chromium and silicon in iron meteorites,” Meteoritics, vol. 4, 1969, pp. 259-260.[8] Dreibus, G., Palme, H., Spettel, B., Zipfel, J., & Wanke, H., „Sulfer and selenium in chondritic meteorites,“, Meteoritics, vol. 30, 1995, pp. 439-445.[9] Nichiporuk, W. & Bingham, E. „Vanadium and Copper in Chondrites,” Meteoritics, vol. 5, 3, 1970, p. 3.

242/27/2018

TRANSPORTING RESOURCES

Adit KhajuriaCAD

Resource Extraction, ManufacturingFebruary 27, 2018

2/27/2018 25

PROBLEM

• Problem(s): • Design and power a water facility capable of extracting water

from underneath Martian regolith (Resources)• Design a way to make extracted steel usable (Manufacturing)

2/27/2018 26

SOLUTION

Water Extraction System (top)

● Extraction rate of 1.09 kg/s per well (3 for the city)

Electric Arc Furnace (right)● Fed Iron Oxide, converts

into metallic Iron, melts into usable liquid steel inside EAF

BACKUP - WATER● Water Extraction Well

○ Modeled after a “Rod Well” -Used in Antarctica

○ Top of well located at roughly 20m from Martian surface

○ Length of well itself about 150m

BACKUP - WATER Boiler and Pump facilities

● Boiler (right) boils water to SHV and sends down to the well

● SHV melts ice and also expands well slowly

● Pump (left) pumps water out of well

○ Feeds some water back into boiler

● Water sent off to city at a rate of 1.09 kg/s per well (3 wells in total for a total flow rate of 3.27 kg/s)

BACKUP - MANUFACTURING

Water Tower● Contains water fed by pump

○ Also acts as a back-up in case of failure

● Height of tower useful in driving water via pressure

BACKUP - MANUFACTURING

Pipeline Heating Facility● Placed along pipeline to

prevent water from freezing● Uses resistance to heat pipe

via wire

BACKUP - MANUFACTURING

Schematic by Will Adams

BACKUP - MANUFACTURING

Electric Arc Furnace● Steel exterior, ceramic interior● Graphite electrodes melt material into

usable liquid steel● 2.5m radius, 2m height

○ V = 40 m^3

POWER FOR AEROPONIC WATERING SYSTEM

Jonathan RohwerDiscipline Group: Human Factors

Vehicle & Systems Group: Food Production2-27-2018

2/26/2018 34

PROBLEM• Problem: Quantifying power for Food Production’s watering system

• Moving water to and from tanks• Moving irrigation system • Mixing water in tanks

2/26/2018 35

• Requirements• Provide water at the proper amount

and pressure for system to work• Move irrigation system • Reclaim water that is not absorbed• Homogenous mixture in tanks

• Assumptions• Amount of reclaimed water is the

amount sprayed as a factor of safety• Vigorous mixing is not required in

tanks• Adiabatic • Day to reclaim water accumulated

System Power [kW] Mass of Pumps or Motors [Mg]

Pumping Water 9.56 1.337Moving Irrigation 7.08 3.12E-3Reclaiming Water 4.68E-3 0.335Stirring Tanks 339 0.1496Total 355 1.825

2/26/2018 36

SOLUTION

• Conclusions• 355 kW is small compared to the 3 GW being

produced by city• 1.825 Mg of material added to the structure of

aeroponics is small compared to water being stored ~ 3840 Mg

APPENDICES

2/26/2018 37

PUMP/MOTOR SIZING

• Zytek 170kW Motor has a mass of 75 kg [1]• Used this power to mass ratio to size our motors

• Franklin Electric Turf Boss 160 GPM 5 HP [2]• Produces Max operating pressure of 76 psi

• Our operating pressure is 80 to 100 psi• Weights 134 lb which equates to 60.76 kg

• Assumed 22 pumps, 1 per crop per building

• Flotec FP5112 - 10.3 GPM 1/2 HP [3]• Has high enough gpm for our reclaiming process• Weights 16.8 lb which equates to 7.62 kg

• Assumed 44 tanks, 1 per crop per floor except floor 1 since its above the tanks

2/26/2018 38

SOURCES

• [1] “Zytek 170kW 460Nm Electric Traction Motor,” Zytek Available: http://www.zytekautomotive.co.uk/products/electric-engines/170kw/.

• [2] “Franklin Electric Turf Boss 160 GPM 5 HP Self-Priming Cast Iron Sprinkler Pump,” Water Pumps DirectAvailable: https://www.waterpumpsdirect.com/Franklin-Electric-FTB5CI-Water-Pump/p50330.html.

• [3] “Flotec FP5112 - 10.3 GPM 1/2 HP Portable Transfer Pump,” Water Pumps Direct Available: https://www.waterpumpsdirect.com/FloTec-FP5112-08-Water-Pump/p72399.html.

2/26/2018 39

CODE% Name: Jonathan Rohwer

% Class: AAE 450

% Assignment: Power

% Description: Power needed for water supply

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

clear

clc

%% Coversions

atm_pa = 101325; % Conversion from atm to Pa 1atm = 101325Pa

%% Known

water_day = 170000/2; % Water needed per day [kg]

A_total = 809000; % Total plant area [m^2]

A_mod = 266.6; % Module growth area [m^2]

mod_floor = 180; % Modules per floor

nozzle_mod = 14; % Nozzles per module

mod_time = 180/(30/3.25); % Modules on at any given time

nozzle_time = mod_time*nozzle_mod; % Nozzles on at any given time

2/26/2018 40

CODE CONT.floors = 9; % Number of floors

L_floor = 300; % Length of floor [m]

W_floor = 280; % Width of floor [m]

rho_water = 1000; % Density of water [kg/m^3]

g = 3.711; % Acceleration due to gravity on Mars

p_atm = 81060; % Atmospheric pressure [Pa]

dH = 3; % Height change from floor to floor

rho_inv = 1.0020 / 1000; % specific volume at at 21 C [m^3/kg] [58]

%% Assumptions

D_pipe = 0.05; % Diameter of main line

A_pipe = pi*D_pipe^2/4; % Area of main line

D_tank = 4; % Diameter of tank

H_tank = 4; % Height of tank

fos = 1.1; % Factor of safety

%% Gerenal Calculations

water_pp = water_day / A_total; % Water per area per day [kg/m^2]

water_mod = water_pp * A_mod; % Water per modules per day [kg]

2/26/2018 41

CODE CONT.water_dot = water_mod / (60*60*24); % Water flow into the module [kg/s]

%% Inlet pressures

p(2) = 0.8 * atm_pa + rho_water*g*H_tank/2; % Pressure at base of tank (B2 floor) [Pa]

p(1) = p(2) - rho_water*g*dH; % Pressure at B1 floor [Pa]

p(3) = p(2) + rho_water*g*dH; % Pressure at B3 floor [Pa]

p(4) = p(3) + rho_water*g*dH; % Pressure at B4 floor [Pa]

p(5) = p(4) + rho_water*g*dH; % Pressure at B5 floor [Pa]

p(6) = p(5) + rho_water*g*dH; % Pressure at B6 floor [Pa]

p(7) = p(6) + rho_water*g*dH; % Pressure at B7 floor [Pa]

p(8) = p(7) + rho_water*g*dH; % Pressure at B8 floor [Pa]

p(9) = p(8) + rho_water*g*dH; % Pressure at B9 floor [Pa]

%% Flow Properties

r_2 = 0.365e-3/2; % outlet radius [m]

A_2 = r_2^2 * pi; % outlet area [m^2]

p_2 = 0.689e6; % outlet pressure [Pa]

Q = 2.366e-6; % Volumetric flow rate of one nozzle [m^3/s]

2/26/2018 42

CODE CONT.Q_f = Q * nozzle_time; % Volumetric flow rate per floor [m^3/s]

dh = rho_inv * (p - p_2); % change in enthalpy [J/kg] [58]

m_dot_2 = Q_f / rho_inv; % Mass flow rate at exits [kg/s]

m_dot_1 = m_dot_2; % Mass flow rate at inlet

V_1 = m_dot_1 * rho_inv ./ A_pipe; % inlet velocity

V_2 = m_dot_2 * rho_inv / (A_2*nozzle_time); % outlet velocity

P = m_dot_1 * (dh + (V_1.^2 - V_2^2)/2); % Power per floor [W]

P_water_total = sum(P) * 2; % Total Power usage for both buildings [W]

%% Irrigation

rho_PVC = 1300; % Density of PVC pipe [kg/m^3]

t_PVC = 0.01; % Thickness of PVC pipe

D_PVC = D_pipe + 2 * t_PVC; % Outer diameter of pipe

A_PVC = pi * D_PVC^2/4 - A_pipe; % Cross sectional area of pipe [m^2]

L_PVC = 20; % Length of each pipe in the module [m]

V_PVC = A_PVC * L_PVC; % Volume of each pipe in the module [m^3]

m_PVC = V_PVC * rho_PVC; % Mass of each pipe in the module [kg]

V_water = A_pipe * L_PVC; % Volume of water in each pipe [m^3]

2/26/2018 43

CODE CONT.m_water = V_water * rho_water; % Mass of water in each pipe [kg]

m_total = m_water + m_PVC; % Total mass moving in each module

f = 0.3; % friction coefficient of plastic on plastic

F_total = m_total * g; % Weight of pipe with water

F_friction = F_total * f; % Force required to move pipe

W_pipe = F_friction * L_PVC * 2; % Work done to move pipe to end and back

P_pipe_total = W_pipe * mod_time*floors*2/(3.25*60); % Power done by system to irrigate

%% Reclaiming Water

water_extra = water_mod * fos - water_mod; % Max water needed to be reclaimed per module [kg]

water_extra_floor = water_extra * mod_floor; % Water reclaimed per floor [kg]

m_reclaim = 0; % initialize for loop

for i = 1:8

m_reclaim = m_reclaim + water_extra_floor * i;

end

2/26/2018 44

CODE CONT.W_reclaim = m_reclaim * dH * g; % Work to move all the water up to the tanks

P_reclaim = W_reclaim / (24*60*60)*2; % Power required to move the reclaimed water up over a day for both buildings

%% Mixing Tank

C_d = 1.28; % Drag coefficient of a flate plate

omega = 0.1047; % Angular velocity [rad/s]

R_in = 0.5; % Inner radius of plate [m]

R_out = 1.5; % Outer radius of plate [m]

A_plate = 1; % Area of one plate [m^2]

V_avg = omega/2 * (R_in + R_out); % Average velocity of the plate

D_total = C_d * rho_water * V_avg^2 * A_plate / 2 * 2; % Total drag on both plates

T_total = D_total * (R_in + R_out) / 2; % Total Torque on the plates

W_rot = T_total * 2 * pi; % Work required to rotate a full circle

P_rot = W_rot * 2*pi/omega; % Power required to rotate a full circle

P_rot_total = P_rot * 64; % Total Power for all 64 tanks

%% Output

P_total = P_pipe_total - P_water_total + P_rot_total + P_reclaim; % Total Power needed

2/26/2018 45

ADDING COMFORT(AND MUSHROOMS!)

Kelsey DelehantyHuman Factors

Food ProductionFebruary 27, 2018

2/27/2018 46

THE PROBLEMSRequirements

1. Keep our citizens healthya. Missing one crucial

vitamin: vitamin D (deficiency leads to rickets, porous brittle bones, osteoporosis) [8]

b. Comes from exposing skin to UV, eating meat or certain plants exposed to UV

c. Radiation, components for UV lights (Mercury, Xenon)

2. Keep our citizens happya. Limited food choicesb. Leisure activities

2/27/2018 47

Constraints1. 800 m2 extra

a. 1600 m2 for compact foods

Lower Levels 1 and 2 (Kelsey Delehanty)

Farming Levels (Subhiksha Raman)

THE SOLUTIONSMushrooms

Prep: slice, expose to sunlight with gills upMethod: one flatbed/day to surface, 8 m2 area covered

Mushroom consumption: 39 g/day (⅜ cup)Vitamin D: 0.015 mg, with 1 hr sun exposure [3]Minimum: 0.015 mg [4]Toxicity: ~12 mg from diet [4]

Agricultural space: 242 m2

(includes 13% extra yield and walking space)Food from refuse: 390 kg/day (wheat straw) (6% of total refuse)

48

HerbsHarvest: Basil, mint, oregano, rosemaryRationale: fastest growth time [9]Uses: tea, seasonings, medicinal

Growing method: hydroponics [9]Herb consumption: ½ tsp per week of each of the four herbs

Water: 61 kg water/day [9]Agricultural space: 1,356 m2

Power for lights: 138 kW (Matt Prymek)

PaintsHues: Red (strawberries), green (kale, spinach), blue (blueberries), black (charcoal) [19]

Ingredients: 1 cup of paint = 1 cup fruit + 1 cup water + 0.25 tsp flour

Extra food used for paint production: 0.5%Red: 14.63 cups/dayGreen: 22.75 cups/dayBlue: 9.75 cups/day

Wheat: 11.8 tsp/day (0.04% daily extra)Water: 13 kg/day

Other systems: City (power for lights, mushrooms to the surface), Resource Extraction (water)

2/27/2018

APPENDIX

492/27/2018

MUSHROOMS AND VITAMIN D [1-8]Mars receives only 44% of UV on the surface that Earth does. (Matt Prymek)Mars is, on average, 50% further from the sun:

50

Sun Exposure (hr) Daily Amount (kg) Vitamin D (mg) Crop Area (m2) Refuse (kg)

8 0.013 0.066 135 130

4 0.013 0.033 135 130

2 0.026 0.033 269 260

1 0.026 0.016 269 260

1 0.039 0.025 404 390

1 0.023 0.015 242 390

[3]

I’ve assumed this scales linearly with time.

Mushrooms need 1 lb fuel for 1 lb mushrooms. [2]

2/27/2018

HERBS: WATER AND SPACE NEEDS [9-15]

51

Spearmint Oregano Basil Rosemary Total

Yield (kg/m2) 0.0168 0.23 0.6 0.55 ~Density (kg/met. cup) 0.027 0.07 0.035 0.055 ~

Met. cup to tsp 50 50 50 50 ~m2 for tsp per person 0.032 0.006 0.001 0.002 ~

tsp per person 0.071 0.071 0.071 0.071 ~m2 for tsp for 10000 people 22.959 4.348 0.833 1.429 ~

Growth time (days) 30 30 30 42 ~

Total area (m2) 689 130 25 60 904

Plants per m2 4 4 4 4 ~

Water per cup (kg) 0.946 0.946 0.946 0.946 ~Water per cup per month (kg) 0.473 0.473 0.473 0.473 ~Total water per month (kg) 1303.2 246.8 47.3 113.5 1711

2/27/2018

PAINTS [16-19]

52

Example: StrawberriesVolume of plant (cup) 1Volume of wheat flour (tsp) 0.25Volume of water (cup) 1Plant Density Conversion (kg/cup) 0.16Mass plant need to make cup of paint (kg) 0.16Flour Density Conversion (kg/cup) 0.127Mass flour need to make cup of paint (kg) 0.03175

[17] [19]

2/27/2018

SOURCES

532/27/2018

SOURCES

Mushrooms

[1] Svane-Knudsen, D., “UV light turns mushrooms into vitamin D bombs,” sciencenordic Available: http://sciencenordic.com/uv-light-turns-mushrooms-vitamin-d-bombs.

[2] “GOURMET MUSHROOMS,” Profitable Plants Digest Available: https://www.profitableplantsdigest.com/mushrooms/.

[3] Stamets, P., “Place Mushrooms in Sunlight to Get Your Vitamin D,” Fungi Perfecti Available: http://www.fungi.com/blog/items/place-mushrooms-in-sunlight-to-get-your-vitamin-d.html.

Vitamin D

[4] “How Much Vitamin D Should You Take For Optimal Health?,” Healthline Available: https://www.healthline.com/nutrition/how-much-vitamin-d-to-take#section8.

[5] “Vitamin D,” Linus Pauling Institute Available: http://lpi.oregonstate.edu/mic/vitamins/vitamin-D#.

[6] Tripkovic, L., Lambert, H., Hart, K., Smith, C., Bucca, G., Penson, S., Chope, G., Hypponen, E., Berry, J., Vieth, R., and Lanham-New, S., “Comparison of vitamin D2 and vitamin D3 supplementation in raising serum 25-hydroxyvitamin D status: a systematic review and meta-analysis,” American Journal of Clinical Nutrition, vol. 95, May 2012, pp. 1357–1364.

[7] “What is the Difference Between Vitamin D2 and D3?,” BioNatures Available: https://bionatures.com/blogs/news/what-is-the-difference-bewteen-vitamin-d2-and-d3.

[8] Berdanier, C. D., Dwyer, J. T., and Heber, D., eds., Handbook of Nutrition and Food, Boca Raton, FL: CRC Press, 2014.

542/27/2018

SOURCES, CONT.

Herbs

[9] Main, E., “How To Grow Thriving Houseplants In Water,” Rodale's Organic Life Available: https://www.rodalesorganiclife.com/garden/easy-houseplants-that-grow-in-water.

[10] Saha, S., Monroe, A., and Day, M. R., “Growth, yield, plant quality and nutrition of basil (Ocimum basilicum L.) under soilless agricultural systems,” Annals of Agricultural Sciences, vol. 61, Dec. 2016, pp. 181–186. Available: https://www.sciencedirect.com/science/article/pii/S0570178316300288#f0015

[11] The Editors of Encyclopædia Britannica, “Growing season,” Encyclopædia Britannica Available: https://www.britannica.com/topic/growing-season.

[12] “Mint,” Specialty CrOPPORTUNITIES Available: http://www.omafra.gov.on.ca/CropOp/en/herbs/culinary/mint.html.

[13] Nurzynska-Wierdak, R., “Herb yield and chemical composition of common oregano (Origanum vulgare L.) essential oil according to the plant’s developmental stage,” HerbapolonicaAvailable: http://herbapolonica.pl/magazines-files/370662-Pages%20from%20Herba_3-6.pdf.

[14] Wikifarmer Editorial Team, “Rosemary Plant and Essential Oil Yield,” Wikifarmer Available: https://wikifarmer.com/rosemary-plant-and-essential-oil-yield/.

[15] Arsenault, R., “How to Propagate a Rosemary Plant from Stem Cuttings,” Grow a Good LifeAvailable: https://growagoodlife.com/propagate-rosemary-plant-from-stem-cuttings/.

Paints

[16] Finch, H., “How to Make Paint From Berries,” eHow Available: https://www.ehow.com/how_4884547_make-paint-berries.html.

[17] Mann, H., “Paint Made From Berries & Nature,” Instructables.com Available: http://www.instructables.com/id/Paint-Made-from-Berries-Nature/.

[18] “Can You Make Paint Out of Berries?,” Wonderopolis Available: https://wonderopolis.org/wonder/can-you-make-paint-out-of-berries.

[19] “Make natural paint with leftover fruits and veggies,” VerMints Inc Available: http://www.vermints.com/blog/make-natural-paint-with-leftover-fruits-and-veggies/.

552/27/2018

FLOOR LAYOUT

Subhiksha RamanCAD

City Infrastructure and Food ProductionFebruary 6, 2018

2/27/2018 56

PROBLEM

• Too many buildings in current city layout

• Assumptions• Each building is a rectangular prism• Habitable volume: 100 m3/person (Longuski)• Floor area: 400 m2

• Floor height: 2.75 m• Floor thickness: 0.25 m

• Need to determine• Number of apartments/floor• Number of people/apartment• Buildings to keep/remove

• Requirements • More aesthetic layout• Include wall thickness

2/27/2018 57

SOLUTION• 4 apts/floor, 2 people/apt

• Can have maximum of 3 people/apt if needed

• Apartment floor area: 80 m2 (Volume: 220 m3)• Interior wall: 0.165 m [1], Exterior: 0.3 m• Hallway: 1 m• Elevators: 1.5 m x 1.5 m• Kitchen: 12 m2 [2]• Living and dining: ~28 m2

• Bedrooms: ~16 m2 each• Bathroom: 7.5 m2 [3]

• Toilet, sink, bathtub and/or shower

• Placement of buildings• Depends on trusses (Chris Johnson)

• Next Steps: • Finalize city layout• Make buildings nicer to look at

2/27/2018 58

KITCHEN SIZE CALCULATION

59

10% to 15% of total living space [1]

Total living space: 80 m2

80*.1 = 8 m2

80*.15 = 12 m2

In diagram: ~12 m2

PRELIMINARY BUILDING CALCULATIONS

Ideally would want people towards the middle of width of tube.

22 floors/building x 8 people/floor x 10 buildings = 1760 people18 floors/building x 8 people/floor x 20 buildings = 2880 people21 floors/building x 8 people/floor x 4 buildings = 672 people

Total: 5312 people/module -> half of the population

60

REFERENCES

[1] “Home Guides,” SF Gate. Available: homeguides.sfgate.com/instructions-building-interior-wall-24777.html

[2] Wallender, L. “Average Kitchen Size? Well, Its Complicated...,” The Spruce. Available: https://www.thespruce.com/average-kitchen-size-1822119.

[3] “Small Bathroom Floor Plans,” House Plans Helper. Available: https://www.houseplanshelper.com/small-bathroom-floor-plans.html.

61

SUPPORTING THE LAVA TUBE

Christopher JohnsonStructures

City InfrastructureFebruary 27, 2018

2/27/2018 62

PROBLEMProblem: The concrete lining isn’t enough to support the entire weight of the lava tube. Flex of 8 m

Assumptions: 1. Approximate rock pressure as

linearly constant along tube surface

2. Flat roof with 50 m roof thickness

3. Extra support supports only surface above it

Requirements1. Extra support must alleviate stress

on the concrete lining

2. Extra support must reduce the deformation of the concrete lining

3. Entire structure must be able to hold up the roof in case of failure

2/27/2018 63

SOLUTIONAdd trusses

1. Total weight of rock: a.36 MN

2. Use buckling analysis to size truss columnsa.70 cm thicknessb.4 by 10 000 Mgc.Square cross sectionsd.Factor of safety of 8

3. Verify findings with Ansysa. Maximum flex of 45 cmb. Maximum stress of 36

MPac. Minimum stress of 17

MPa

2/27/2018 64

APPENDIX (P = 3.05E5 PA)

2/27/2018 65

APPENDIX (P = 3.05E5 PA)

2/27/2018 66

APPENDIX (P = 3.05E5 PA)

2/27/2018 67

APPENDIX (P = 3.05E5 PA)

2/27/2018 68

APPENDIX (P = 1.52E5 PA)

2/27/2018 69

APPENDIX (P = 1.52E5 PA)

2/27/2018 70

APPENDIX (P = 1.52E5 PA)

2/27/2018 71

APPENDIX (P = 1.52E5 PA)

2/27/2018 72

APPENDIX (TRUSS)

2/27/2018 73

LAVA TUBE ECLSS (AIR LOSS)

Connor FoleyHuman Factors

City InfrastructureFebruary 27, 2018

2/27/2018 74

THE PROBLEM

ProblemCement structure around the city leaks a considerable amount of air daily (1%-4% daily), so we need to find a material to mitigate that loss [CDR Feedback]

Requirements• Material manufacturable on Mars

Assumptions• Thickness of coating: 1 cm (ease

of manufacturing)• 100-year manufacturing life cycle

2/27/2018 75CAD model by Subhiksha Raman

THE SOLUTION

• Polyethylene (HDPE) coating1 cm thickCovers entire area surrounding lava tube (1.05e+06 m2)Total volume of material: 1.05e+04 m3

Total mass of material: 1.01e+04 Mg100-year life cycle: Need 102 Mg/yearAir loss: 2.2 kg/day (1.3e-5% daily air loss)

• Update on ECLSSMass: 17,000 MgPower: 25 MW

2/27/2018 76

APPENDIX: LAVA TUBE ECLSS

2/27/2018 77

APPENDIX: ECLSS DETAILS

Water Recovery System:1. Water Processor Assembly: removes free gases and solid materials, electrical sensors check the purity of the water2. Urine Processor Assembly: low pressure vacuum rotating distillation to collect water from urineProcess 264 Mg water/day, 90% efficiency (Nicole Futch), so need 26.4 Mg/day from human resources

Carbon Dioxide Reduction AssemblyZeolite, formed from volcanic rocks and ash, very porous, scrubs carbon dioxide from air, sends to UMAWPS

Air Temperature/Pressure/Humidity Control:Maintain pressure at 81.1 kPa, control humidity by removing condensation

Waste Management:Process 4.5 Mg solid waste/day, isolate nutrients for food production

2/27/2018 78

APPENDIX: COLLABORATION WITH RESOURCES EXTRACTION GROUP

2/27/2018 79

To UMAWPS*:10.4 CO2 Mg/day

From UMAWPS:14.3 O2 Mg/day19.5 N2 Mg/day

*UMAWPS = Universal Martian Atmospheric and Water Processing System

Diagram produced by Diego Martinez

APPENDIX: FICK’S FIRST LAW

2/27/2018 80

• Fick’s First Law (Mass Diffusion):

Ni = - Di ∇ciNi: Molar Flux [mol/m2/s]Di: Diffusion Coefficient [m2/s]ci: Concentration [mol/m3]

Note 1: get the proper units in “Molar Flux” by dividing “Concentration” by the thickness of the material

Note 2: Assistance on Mass Diffusion from Halen Blair

APPENDIX: PRESSURIZATION CODE (ADDED TO HF CITY CODE)

• % CONNOR -- daily pressurization leakage

•

• % Fick's First Law -- mass diffusion

• h = 100; % height of tunnel in middle, units: [m]

• w = 300; % width of tunnel, units: [m]

• l = 1500; % length of tunnel in meters, units: [m]

• a_tunnel = h*w/2*pi/2; % cross section of tunnel if assumed half an ellipse, units: [m^2]

• D = 5.1e-9; % Diffusion Coefficient of toluene in HDPE [cm^2/s]

• D = D/10000; % Convert to [m^2/s]

• p = 81.1e+3; % Pressure of lava tube air, units: [Pa]

• T = 21+273.15; % Temperature of lava tube, units: [K]

• R = 8.314; % Ideal gas constant, units: [J/mol/K]

• n_V = p/(R*T); % density of air in lava tube, units: [mol/m^3]

• V = a_tunnel*l; % Volume of tunnel interior, units: [m^3]

• n = n_V * V; % Number of moles of air in the lava tube, units: [mol]

• C = n_V; % Concentration of air on the inner wall of the tube, units: [mol/m^3]

• thickness = 0.01; % Thickness of polyethylene in wall, units: [m]

• N = D*C/thickness; % Molar Flux of air in lava tube, units: [mol/m^2/s]

• circumf = 793.27; % Approximate circumference of an ellipse, units: [m]

• Area = 300*1500 + circumf/2 * 1500; % Area of interior walls enclosing lava tube, units: [m^2]

• AirLeakage = N*Area; % total leakage of air in lava tube, units: [mol/s]

• % Convert [mol/s] to [Mg/day]:

• mol2Mg = (mass_Mg_oxy_range(3) + mass_Mg_nit_range(3))/n; % Conversion, units: [Mg/mol]

• AirLeakage = AirLeakage*3600*24*mol2Mg % total DAILY leakage of air in lava tube, units: [Mg/day]

•

2/27/2018 81

APPENDIX: PRESSURIZATION CODE (ADDED TO HF CITY CODE) – CONT.

• % Mass, Volume, and Manufacturing Rate of HDPE:

• area_HDPE = Area;

• vol_HDPE = area_HDPE*thickness; % units: [m^3]

• density_HDPE = 970; % Density of polyethylene (HDPE), units: kg/m^3

• TotalMass = density_HDPE*vol_HDPE/1000 % Total mass of polyethylene coating, units: [Mg]

• Daily_Manufacturing = TotalMass/100/365 % Manufacturing mass requirement, units: [Mg/day]

2/27/2018 82

APPENDIX: REFERENCES[1] Schaezler, R., Cook, A., Leonard, D, and Ghariani, A., “Trending the Overboard Leakage of ISS Cabin Atmosphere,” American Institute of Aeronautics and Astronautics, [online], https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20110012997.pdf

[2] “International Space Station: Environmental Control and Life Support System,” National Aeronautics and Space Administration, [online], FS-2008-05-83-MSFC, https://www.nasa.gov/sites/default/files/104840main_eclss.pdf

[3] “Crisp, Clean Clothes without the Waste,” Alliance for Water Efficiency, [online],https://www.home-water-works.org/indoor-use/clothes-washer

[4] Ming, D. and Gooding, J., “Zeolites on Mars: Possible Environmental Indicators in Soils and Sediments,” NASA Johnson Space Center, [online], https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19890008967.pdf

[5] Han, B., “Measurements of True Leak Rates of MEMS Packages,” Sensors, 2012, No. 12, pp. 3082-3104.

[6] Prasad, T., Brown, K., and Thomas, J., “Diffusion Coefficients of Organics in High Density Polyethylene (HDPE),” Waste Management & Research, Vol. 12, No. 1, 1994, pp. 61-71, doi: 10.3390/s120303082.

2/27/2018 83

REACTOR DESIGNAleksander Gardner

Power/ThermalCity/Food2/10/2018

2/20/2018 84

PROBLEM

• 3 GW of Power Required• Manufacturing power still being estimated but assumed 1GW (Amy

Comeau• Ground Transport needs 1 GW for the rail line (Stephen Kubiki)• 100 MW of Power for City needs such as lighting for crops and

streets (Jonathan Rower• Other options

• Solar: Too heavy for city expansion• Geothermal: No heat high enough, would need to drill on Mars to

know if it is viable• Thorium is very abundant on Mars’s surface, but uranium is not

Image Credits: Subiksha Raman

85

SOLUTION

• Around 60000 M2 of area required for reactor building and some waste pools [1]

• Need to be underground to protect from radiation and allow for maintenance

• Can schedule inspections every 2 years to check core for embrittlement

• Breeder Reactors, make more fissile material than they use• Can be pulled from reactors and stockpiled for a new reactor

• 7% extra fissile material per year [1]• Self stopping in event of supercriticality

86

Concrete Hastelloy-N LiF BeF2 Water Piping and Turbines

Thorium Uranium

Mass (Mg)

16000 1100 1070 30 9000 11000 260 0.7

APPENDIX

Mass estimates of other Methods

2/20/2018 87

Option Mass (Mg) Power Output (MW)

Potential Problems

Solar (in space) 9,660,000 3000 Rockets to get them in place

Solar (on ground)

19,800,000 3000 60 Day dust storms

Geothermal 480,000 3000 45 km drill depth

Nuclear 120,000 3000 Scarce materials

APPENDIX

Kasten, P. R., Bettis, E. S., and Robertson, R. C., “Design Studies of 1000-Mw(e) Molten-Salt Breeder Reactors,” Central Research Library.

IADC Drilling Manual (1.1th ed.). (n.d.). Houston, TX: Technical Toolboxes, Inc.

Sam Noynaert, Professor at Texas A&M in Petroleum Engineering

U.S. Nuclear Propulsion (n.d.). In Forecast International.

Nieminen, A. J., “Molten Salt Reactors The new frontier of nuclear reactors,” thesis, 2017.

88

RAIL POWER CONSUMPTION REFINEMENT AND CREWED

VEHICLE HEAT LOSSStephen Kubicki

Power and ThermalGround Transportation

February 27th, 2018

2/27/2018 89

• How much time/power do the railcars require to reach each destination?• How much heat loss will the rovers and personnel railcars experience?

Requirements:• The personnel railcars shall be able to complete all round trips in less

than 133 hours. (Customer)• Crewed vehicles shall maintain a cabin temperature of 20°C in all

environmental conditions.

Assumptions:• Railcars accelerate constantly over one hour to top speed.• Electric traction motors scale linearly. • Motor efficiency is constant with scaling.

Need to Determine:• Railcar electric traction motor sizing.• Updated roundtrip travel times for each destination.• Rover and personnel car heat loss rates.

THE PROBLEMS

2/27/2018

Electric Traction Motor CAD (Sean Thompson)

2

THE SOLUTIONS

2/27/2018 91

• Refined model to include drag resistance and electric motor efficiency

• Included analysis for railcar acceleration period

• Ensured maximum power draw for motor sizing

• Heat Transfer Analysis included:

• Conductive losses through aluminum and polyethylene layers

• Natural convective losses to the atmosphere

• Radiative losses to the surroundings

92

ROUTE SLOPE DATA AND MOTOR POWER CALCULATIONS

2/27/2018

Elevation data obtained using Mars Orbiter Laser Altimeter

(MOLA) data via JMars software Motor Power Calculations:● Maximum time of one-way travel for

personnel car driven by radiation standards and 1 day for maintenance at resource sites

● Average travel velocity computed using time limits and distance to farthest resource site (Thorium = 8503 km)

● Motor mass and power guessed, then code iterates to find updated personnel car mass. Updated total mass used to find new motor power and mass, iterate until error is <0.1 kg

● Motor mass and power scaled based on Zytek Electric Traction Motor 7

TRAVEL TIMES - EARTH AVERAGE RADIATION STANDARD

93

Information sourced in code for these computations:• Rolling Resistance of Steel Wheels on Steel Rails 1• Drag Coefficient of a Passenger Railcar 2• Atmospheric Density on the Martian Surface 3

2/27/2018

94

TRAVEL TIMES - NASA RADIATION STANDARD

2/27/2018

TRAIN MASSES FOR DIFFERENT RADIATION STANDARDS

952/27/2018

HEAT TRANSFER ANALYSIS - THERMAL RESISTANCE NETWORK

962/27/2018

HEAT TRANSFER ANALYSIS – CODE (PT. 1)

97

Information sourced in this code:• Emissivity of HDPE 4• Thermal Conductivity of HDPE 5• Convective Heat Transfer Coefficient 6

2/27/2018

98

HEAT TRANSFER ANALYSIS – CODE (PT. 2)

2/27/2018

APPENDIX: SOURCES

2/27/2018 99

TRAIN ROUTE MAPPING

Ana Paula Pineda BosquePropulsion Group

Ground Transport GroupFebruary 27, 2018

2/27/2018 100

PROBLEM

2/26/2018 101

Needs Requirements

Must avoid high slopes ideal: slope < 10°, max: slope< 20°

No sharp turns ideal: rcurve > 2000 m , min: rcurve = 250 m

Avoid natural obstacles (crater, canyons) ideal: dcrater = 0; max: dcrater = 1 km

Minimize rail used ideal: distance = 11540 km

What routes will the trains follow? How will that affect our mass, power and volume requirements?How can the total distance be minimized?

Assumptions:● Craters under 1 km in diameter can be built over or around. ● Rail must lie on ground (no bridges, tunnels, etc.)

Needs to be determined: ● Inclination● Changes to necessary material production

SOLUTIONRoute Changes

Site Category Details

Landing Site

Original Length [km] 40

Route Length [km] 56

Max Inclination [deg] 0.052

Water Glaciers

Original Length [km] 280

Route Length [km] 522

Max Inclination [deg] 3.6

Iron Deposit

Original Length [km] 660

Route Length [km] 1054

Max Inclination [deg] 3.86

Nitrate Deposit

Original Length [km] 3118

Route Length [km] 4224

Max Inclination [deg] 8.32

2/26/2018 102

Approximate Model:Length = 1.4*(direct length)

New System Requirements

Concrete Mass [Mg]

Starting 12,732,000

Yearly 11,574

Steel Mass [Mg]

Starting 3,535,000

Yearly 88

LANDING SITE

2/26/2018 103

WATER GLACIERS

2/26/2018 104

IRON DEPOSIT

2/26/2018 105

NITRATE DEPOSIT

2/26/2018 106

CALCULATING ENVIRONMENTAL

SPACECRAFT TORQUESSamuel Albert

Communications InfrastructureCommunications & Control

02/27/2018

2/27/2018 107

THE PROBLEM• Need to determine external torques acting on spacecraft in order to size attitude control

system• External torques attitude control additional propellant mass

• Focus on Mars Communications Network (MNet)

• Include torques due to:• Gravity gradient, solar radiation, reflected solar radiation [2]

• Neglect torques due to:• Particle collision, magnetic forces, non-propulsive mass expulsion, spacecraft radiation, fuel slosh, structural flexing [2]• These torques are either much smaller ormuch more difficult to estimate initially

• Requirement: pointing accuracy of 0.1º or better

for antenna pointing• Antenna will also have ability to gimbal for precision• Note: this requirement would be much more strict foroptical communications - see Appendix C

2/27/2018 108

CAD from Sam Zemlicka-Retzlaff(Communications Infrastructure, CAD)

THE SOLUTIONEstimated average external spacecraft torques:

• Torques are dependent on orientation• Aligning principal moments of inertia with orbital axes would remove gravity gradient torque

• Based on simplified spacecraft model – see appendix A• Cyclic and secular torques

• Use reaction control wheels to counteract oscillatory torques• Need to react against secular torques as well, and dump angular momentum from saturated

reaction wheels• Magnetic torque rods are sometimes used, but Mars’s magnetic field is too weak for this to

work

• requirement for 3-axis stabilization in order to counteract above torques

2/27/2018 109

Torque Type Estimated Value [Nm]Solar Radiation 1.8 x 10-4

Gravity Gradient 1.9 x 10-6

Reflected Solar Radiation 5.84 x 10-7Hall thruster model

CAD from Sam Zemlicka-Retzlaff(Communications Infrastructure, CAD)

APPENDIX A: CALCULATIONS (1/2)

2/27/2018 110

APPENDIX A: CALCULATIONS (2/2)

2/27/2018 111

APPENDIX B: MATLAB CODE (1/2)

2/27/2018 112

APPENDIX B: MATLAB CODE (2/2)

2/27/2018 113

APPENDIX C: RF VS OPTICALTradeoff Between Radio Frequency (RF) and Optical Communication Systems for

Mars-Earth High Data Link (MEHDL)

• Motivation: MEHDL requires high data rate transmission over long distances. How can we effectively communicate back to Earth?

• Background: Optical communication is a growing technology which uses lasers to transmit at very high data rates with 50% mass reduction, 65% power reduction3. Deep Space Optical Communications will soon have a TRL of 6 after use on the Psyche mission in 20224.

• Requirement: Primary requirement is to transmit 42 Mbps to Earth continuously – lower than initially thought.

• Analysis: While it is true that optical communications offers high performance, the manufacturability and complexity of the system is problematic. Key concerns include:

• Extremely high-precision pointing required, on the order of one micro-radian or better5

• Lifetime of active laser components may be limited to 6 years5

• Surface finish within 1 nanometer requirement6

• Conclusion: Since we are optimizing for complexity and manufacturability, instead of for mass and power, RF is a better choice in this case.

2/27/2018 114

APPENDIX D

References1Harris, M., and Lyle, R., “Spacecraft Gravitational Torques,” NASA SP-8024, May 19692Longuski, J.M., Todd, R. E., and Konig, W. W., “Survey of Nongravitational Forces and Space Environmental Torques: Applied to the Galileo”, AIAA Jounral of Guidance, Control, and Dynamics, Vol. 15, No. 3, May-June 1992, pp. 545-5533Wertz, J. R., Everett, D. F., and Puschell, J. J., Space mission engineering: the new SMAD, Hawthorne: Microcosm Press, 2015.4Grayzeck, E., “Mars Fact Sheet”, Lunar and Planetary Science, NASA GSFC <https://nssdc.gsfc.nasa.gov/planetary/factsheet/marsfact.html>

2/27/2018 115

MARS COMMUNICATIONS NETWORK SOLAR ARRAYS

Sam Zemlicka-RetzlaffCommunications Infrastructure

CAD02/27/2018

2/27/2018 116

THE PROBLEM

2/27/2018 117

MNet- HD Communication• Support 10 W Transmitting Power• Frequency - 8.4 GHz (X-band)• One 0.3 m dish, communicate with

rovers and ground stations• Two 6 cm antenna, crosslink

communication

Credit: Power and Frequency Values, Sam Albert Propulsion Values, Connor Lynch

To Earth

THE SOLUTIONSolar Array RequirementsTotal Panel Area 17.02 m2

Panel Material Silicon, Plastic, Steel

Effective Solar Flux

71.76 W/m2

Credit: Models Created in Autodesk Inventor

Solar Panel Values, Duncan Harris

Materials required, Faiz Feroz

APPENDIX

Hand Written Calculations: Circular Solar Panel Sizing for each Satellite

THERMAL MANAGEMENT OF COMMUNICATION SATELLITES:

SOLAR PANELSDuncan Harris

Power and ThermalCommunications Infrastructure

2/27/2018

2/27/2018 120

THE PROBLEM: HOW SHOULD HEAT BE DISSIPATED FROM EACH SPACECRAFT?

2/27/2018 121

Mars Communication Satellite - Sam Zemlicka-Retzlaff

Spacecraft must reject heat accumulated from environmental sources and internal electronics

RequirementsThermal control system must keep components between operating temperatures• Solar panels: [-150 °C, 100 °C] [1] (Presentation topic)• Battery: [-20 °C, 55 °C] [2]

• Propellant: below -186 °C (Connor Lynch)• Reaction wheels: [-25 °C, 70 °C] [3]

• Computer system: [0 °C, 50 °C] [1]

Assumptions• Solar panel backside temperature is 40 °C [4] nominally, typical

value• Solar panels always oriented with collectors facing sun• Heat transmitted instantaneously between front and back side of

solar panel• Negligible internal heat generation inside solar panels

MEHDL: Mars Earth High Data LinkMNet: Mars Communication Network

Albedo flux

Solar flux

Radiator flux Mars IR flux

THE SOLUTION: COATING BACK SURFACE WITH WHITE PAINT

Solar panels typically are coated with white paint to emit radiation from the body[4]

Taking into consideration planetary albedo, infrared radiation, and solar flux:

Used properties of S13G-LO[4] assuming a coat thickness of 0.254 mm[5]

Produced radiation fluxes within reason to literature[4], order of 450 W/m2

Further analysis will focus on chassis internal components

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Satellite Name Painted Area (m2) Mass (kg)

MNet 1.03 0.351

MEHDL Relay 14.7 5.00

MEHDL Mars Terminal 14.2 4.83

MEHDL Earth Terminal 30.8 10.5

APPENDIX: REFERENCES[1] Zemlianoy, P., “Thermal Control of Space Electronics.” September 1996. https://www.electronics-cooling.com/1996/09/thermal-control-of-space-electronics/#

[2] Liu, G., Ouyang, M., Lu, L., Li, J., Han, X. “Analysis of the heat generation of lithium-ion battery during charging and discharging considering different influencing factors.” Published online 31 January 2014.

[3] Rockwell Collins, “HT-RSI High Motor Torque Momentum and Reaction Wheels 14 – 68 Nms with integrated Wheel Drive Electronics”, 2007. http://www.electronicnote.com/RCG/HT-RSI_A4.pdf

[4] Gilmore, D. “Spacecraft Thermal Control Handbook, Volume I: Fundamental Technologies”, Published 2002.

[5] Wilkes, D., Thermal Control Surfaces Experiment,” NASA, January 1999. https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19990021250.pdf

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APPENDIX: CALCULATIONS

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From reference [4]

silicon properties white paint properties

α ε α ε

0.1 0.8 0.2 0.85

APPENDIX: MATLAB SCRIPTclear;clc

eta = 0.5; %optimal efficiency of a heatpipe/radiator combinationepsS = .8; %emmitance of quartz alphaS = .1;boltz = 5.6703e-8; %Watt/m^2/K^4Tb = 273.15 + 40; %assumption based on "typical values"fluxout = eps*eta * boltz*Tb^4; %W/A

%% Solar panels - MNet - Painted on back side to get rid of heat solar_area = 17.0913; %[m^2]

%Assumpitons- active face of solar panels always facing sun, other side%pointed at space or planetsunIR = .47* 589; %W/m^2 mean solar flux at mars distance times amount of IRmarsIR = 390; %W/m^2 - at surface marsAlbedo = .3* 589; % at surface - W/m^2 amount of solar flux reflected off of martian surface

%assuming planetary effects decrease with distance from surfaceMNetIR = marsIR*(3396.19/32500)^2;MNetAlbedo = marsAlbedo*(3396.19/32500)^2 ;%finding albedo at distance from surface

Qinternal = 0;

%temperaturestemp = 273 + 40; %assuming nominal radiator temperature of 60 C

%assuming eta and alpha:epsW = .85; %lowest value found for white paint, emittancealphaW = .20; %absorbance of white paint MNet_radiator_flux = epsW * boltz * temp^4%radiator areaMnet_radiator_area = solar_area * alphaS * sunIR / (epsW * boltz*temp^4 - epsW * MNetIR - alphaW * MNetAlbedo)MNet_radiator_power = MNet_radiator_flux * Mnet_radiator_area

%% Solar panels - MEHDL Mars Terminal - Painted on back side to get rid of heat solar_area = 232.7135; %[m^2]

%Assumpitons- active face of solar panels always facing sun, other side%pointed at space or planetsunIR = .47* 589; %W/m^2 mean solar flux at mars distance times amount of IRmarsIR = 390; %W/m^2 - at surface marsAlbedo = .3* 589; % at surface - W/m^2 amount of solar flux reflected off of martian surface

%assuming planetary effects decrease with distance from surfaceMTermIR = marsIR*(3396.19/20427.7)^2;MTermAlbedo = marsAlbedo*(3396.19/20427.7)^2; %finding albedo at distance from surface

Qinternal = 0;

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%temperaturestemp = 273 + 40; %assuming nominal radiator temperature of 40 C

%assuming eta and alpha:epsW = .85; %lowest value found for white paint, emittancealphaW = .20; %absorbance of white paint MTerm_radiator_flux = epsW * boltz * temp^4%radiator areaMTerm_radiator_area = solar_area * alphaS * sunIR / (epsW * boltz*temp^4 - epsW * MTermIR - alphaW * MTermAlbedo)MTerm_radiator_power = MTerm_radiator_flux * MTerm_radiator_area

%% Solar panels - MEHDL Earth Terminal - Painted on back side to get rid of heat solar_area = 232.7135; %[m^2]

%Assumpitons- active face of solar panels always facing sun, other side%pointed at space or planetsunIR = .47* 1284.4; %W/m^2 mean solar flux at mars distance times amount of IREarthIR = 252; %W/m^2 - at surface EarthAlbedo = .3* 1284.4; % at surface - W/m^2 amount of solar flux reflected off of martian surface

%assuming planetary effects decrease with distance from surfaceETermIR = EarthIR*(6378/42164)^2;ETermAlbedo = EarthAlbedo*(6378/42164)^2; %finding albedo at distance from surface

Qinternal = 0;

%temperaturestemp = 273 + 40; %assuming nominal radiator temperature of 40 C

%assuming eta and alpha:epsW = .85; %lowest value found for white paint, emittancealphaW = .20; %absorbance of white paint ETerm_radiator_flux = epsW * boltz * temp^4%radiator areaETerm_radiator_area = solar_area * alphaS * sunIR / (epsW * boltz*temp^4 - epsW * ETermIR - alphaW * ETermAlbedo)ETerm_radiator_power = ETerm_radiator_flux * ETerm_radiator_area

%% Solar panels - MEHDL Relay - Painted on back side to get rid of heat solar_area = 245.15210; %[m^2]

%Assumpitons- active face of solar panels always facing sun, other side%pointed at space or planetsunIR = .47* 589; %W/m^2 mean solar flux at mars distance times amount of IR

Qinternal = 0;%temperaturestemp = 273 + 40; %assuming nominal radiator temperature of 60 C

%assuming eta and alpha:epsW = .85; %lowest value found for white paint, emittancealphaW = .20; %absorbance of white paint relay_radiator_flux = epsW * boltz * temp^4%radiator arearelay_radiator_area = solar_area * alphaS * sunIR / (epsW * boltz*temp^4)relay_radiator_power = relay_radiator_flux * relay_radiator_area

END-OF-LIFE OPERATIONS FOR MARS-EARTH HIGH DATA LINK

(MEHDL) SATELLITESHenry Heim

Mission DesignScience Support

2/6/2018

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THE PROBLEMWhat do we do when MEHDL satellites reach the end of their 15-year lifespan?

• Leave them where they are?

• De-orbit them?• Some are in Solar orbits

• Move them to a graveyard orbit?

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Mars-Earth High Data Link has:

• 2 heliocentric relay satellites

• 3 aerostationary transmit/receive satellites

• 3 geostationary transmit/receive satellites

All use Argon Hall thrusters

Empty mass (Mg)

Semi-major axis (km)

Eccentricity

Heliocentric 2.795 227,900,000 0.064

Aerostationary 2.834 20,430 0

Geostationary 1.134 42,160 0

No matter what we do, we should passivate the satellites if we can to prevent accidental energy

discharge

SOLUTION

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De-Orbit (m/s) Graveyard (m/s) Graveyard size (km)Heliocentric - 0.5304 10,000

Aerostationary 293.6 5.112 145

Geostationary 214.3 10.88 300

Delta v:

De-Orbit (kg) Graveyard (kg)Heliocentric - 0.1417

Aerostationary 80.42 1.385

Geostationary 23.42 1.180

Propellant Mass*:

*Includes 50% factor of safety

Recommendation:

Move any outdated satellites to graveyard

orbits

APPENDIX – EQUATIONS/DATA

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GM for Sun 1.327 x1011 kg3 m-2

GM for Mars 4.283 x104 kg3 m-2

GM for Earth 3.986 x105 kg3 m-2

Helio. transfer a 2.279 x108 kmHelio. dV1 0.2482 m s-1

Helio. dV2 0.2821 m s-1

Aero. dV1 2.646 m s-1

Aero. dV2 2.641 m s-1

Geo. dV1 5.626 m s-1

Geo. dV2 5.615 m s-1

Lambda 0.9De-orbit altitude 50,000 kmHall thruster Isp 1600 s

APPENDIX - CODEclear;close allclc;

uSun = 132712200000;uMars = 42828.371901284;uEarth = 398600.4418;

rMars = 3396.19;rEarth = 6378.137;

%% Graveyard orbits

Helio_a = 2.27937e8;Helio_e = 0.064;Helio_m = 2.795e3;Aero_a = 20428;Aero_e = 0;Aero_m = 2.834e3;Geo_a = 42164;Geo_e = 0;Geo_m = 1.134e3;

%%% This is how much higher the graveyard orbit is than the regular orbitHelio_buffer = 10000;Aero_buffer = 150;Geo_buffer = 310;%%%

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Helio_a_transfer = Helio_a + Helio_buffer / 2;Helio_a_new = Helio_a + Helio_buffer;Aero_a_new = Aero_a + Aero_buffer;Geo_a_new = Geo_a + Geo_buffer;

% The Helio orbit isn't circular so it's more complicated to find dVHelio_p = Helio_a * (1 + Helio_e) * (1 - Helio_e);Helio_rp = Helio_a * (1 - Helio_e);Helio_ra = Helio_a * (1 + Helio_e);Helio_vpm = sqrt(2 * uSun / Helio_rp - uSun / Helio_a);Helio_vpp = sqrt(2 * uSun / Helio_rp - uSun / Helio_a_transfer);Helio_vam = sqrt(2 * uSun / Helio_ra - uSun / Helio_a_transfer);Helio_vap = sqrt(2 * uSun / Helio_ra - uSun / Helio_a_new);Helio_dV = abs(Helio_vpm - Helio_vpp) + abs(Helio_vam - Helio_vap);

% The other ones are easier since they're circular[Aero_dV1, Aero_dV2] = Hohmann(Aero_a, Aero_a_new, uMars);[Geo_dV1, Geo_dV2] = Hohmann(Geo_a, Geo_a_new, uEarth);

Aero_dV = Aero_dV1 + Aero_dV2;Geo_dV = Geo_dV1 + Geo_dV2;

disp('Graveyard delta-vs (m/s)');disp([Helio_dV; Aero_dV; Geo_dV] * 1000);

%% De-orbitingdeorbit_alt = 50000;

Mars_dV = Hohmann(Aero_a, rMars + deorbit_alt, uMars);Earth_dV = Hohmann(Geo_a, rEarth + deorbit_alt, uEarth);

disp('De-orbiting delta-vs (m/s)')disp([Mars_dV; Earth_dV] * 1000);

%% Masslambda = 0.9;Isp = 1600 * 9.81;

% GraveyardHelio_mp = Propellant_Mass_new(Helio_dV, Isp, Helio_m, lambda) * 1.5;Aero_mp = Propellant_Mass_new(Aero_dV, Isp, Aero_m, lambda) * 1.5;Geo_mp = Propellant_Mass_new(Geo_dV, Isp, Geo_m, lambda) * 1.5;

APPENDIX - SOURCESMEHDL empty masses: Duncan Harris

MEHDL orbital elements: Ryan Duong

De-orbit altitude: Eliot Toumey and Andrew Blaskovich

Propellant mass equation: Michael Rose

Lambda values: Earthlink (2009). Rocket Mass Characteristics V4.6. Online. Accessed February 2, 2018 from http://home.earthlink.net/~apendragn/atg/coef/Structural_Coef.pdf

Earth geo. graveyard: Johnson Space Center (n.d.). Orbital Debris Mitigation Standard Practices. Online. Accessed February 2, 2018 from https://orbitaldebris.jsc.nasa.gov/library/usg_od_standard_practices.pdf

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ROVER SPECTROMETER DESIGN

Nick DwyerVehicle and Systems: Science SupportDiscipline: Communication and Control

02/27/2018

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THE PROBLEM

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Requirements and Constraints● Must be manufacturable on Mars● Must fit within rover MPV constraints● 300 nm - 1000 nm spectrum range (Alaina Glidden)● 0.6 nm spectrum precision (Alaina Glidden)

Goal

Desired ‘Luxury’ Features● Perform spectroscopy from a distance on material

not accessible by rover drill● Minimal sample loss

● Determine chemical breakdown of collected samples onboard science rovers or probes

● Especially necessary in the following missions:○ Signs of past life on Mars○ Study Martian impact craters○ Create geologic history of Mars○ Study Phobos

THE SOLUTION

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Method:Laser-Induced Breakdown Spectroscopy (LIBS)• Uses ~1 W, 1064 nm laser to turn very

negligible amount of sample to plasma• This method can be used from roughly

5 m away, depending on the quality of the optics

Design:• One spectrometer is used for both

internal and external spectroscopy• Spectrometer design is a Mars-adapted version of the StellarNet Blue-Wave

○ 200 nm - 1050 nm range ○ 0.2 nm resolution (2048 pixel CCD)

Bottom Line:Mass: 3.2 kg Power: 42.7 W (peak) Volume: 245 cm3

APPENDIX I: BREAKDOWNS

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MassComponent Approximate Mass

Spectrometer, Laser, Lens, and Casing

1.1 kg

Spectrometer boom and motor 1.6 kg

Sample arm, motors, and shaft 2.1 kg

PowerComponent Peak Power Consumption

Spectrometer and laser 12 W

Spectrometer motor 16.3 W

Sample arm motors/actuators 14.4 W

APPENDIX II: MANUFACTURING

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● Laser: Method covered by Mitch Hoffman for fiber optics● CCD Sensor: Nearly identical process and similar

materials to computer chip design (CDR)● Optical Elements: Requires arc furnace for casting and

precision grinder. Carbon polish. ● Monochromator: Laser etched silicon. High precision.● Casings, hardware, boom: No milling required,

extrusion/casting acceptable. Drilling required. Aluminum or equivalent.

SOURCES

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[1] “BLUE-Wave Miniature Fiber Optic Spectrometer Data Sheet” Stellar Net Available:https://www.stellarnet.us/wp-content/uploads/StellarNet-BLUE-Wave-SPEC.pdf

[2] Castle, B. C., Talabardon, K., Smith, B. W., and Winefordner, J. D., “Variables In¯ uencing the Precision of Laser-Induced Breakdown Spectroscopy Measurements,” Handbook of Laser-Induced Breakdown Spectroscopy, vol. 52, 1998, pp. 649–657.

[3] “Crouzet 80547024 Data Sheet” Crouzet Motors Availablehttp://media.crouzet.com/datasheets/english/synchronous-motors-reversible-synchronous-geared-motors-5-nm-3-5-and-7-2-watts-7-2-watts-Part%20number-80547024.pdf

[4] “Crouzet DC Motors Selection Guide” Crouzet Motors Availablehttps://media.digikey.com/pdf/Data%20Sheets/Crouzet%20PDFs/Crouzet%20DC%20Motors%20catalog%20download.pdf#page=36

[5] Hussain, T., and Gondal, M. A., “Laser induced breakdown spectroscopy (LIBS) as a rapid tool for material analysis,” Journal of Physics: Conference Series, 2013.

[6] Palmer, E. W., Hutley, M. C., Franks, A., Verrill, J. F., and Gale, B., “Diffraction gratings (manufacture),” Reports on Progress in Physics, vol. 38, Apr. 1975.

[7] Rai, V. N., “Laser-Induced Breakdown Spectroscopy,” Raja Ramanna Centre for Advanced Technology, 2007.

[8] Thompson, J. R., Wiens, R. C., Barefield, J. E., Vaniman, D. T., Newsom, H. E., and Clegg, S. M., “Remote laser-induced breakdown spectroscopy analyses of Dar al Gani 476 and Zagami Martian meteorites,” Journal of Geophysical Research, vol. 111, 2006.

SEISMIC STATION NETWORK

Nick JancichScience

Science Support2-27-18

2/27/18 138

MISSION• Want to map the interior of

Mars• Better understanding of its formation/layers

• Is the core offset?

• Requirements to start• Need around the scale of 145+ stations

around the entire surface• Needs to be placed on bedrock

• Some surface bedrock, but needs drilling in areas to get below the soil to the bedrock.

• Try to be ~ 1.5 radii away from craters • Rover

• In the process of scaling up rover size• Able to drill boreholes to place on subsurface

bedrock • Can traverse globally

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Seismograph CAD Model created by Logan Kirsch

WHAT TO MONITOR • Considering impacts as a seismic source

• Impact rate >200, almost entirely small asteroids or bits of comets per year that form craters at least 4 meters across. [5]

• These small impacts are not enough to generate seismic energy through most of the interior. Can give regional seismic activity that could give data on the crust and upper mantle.

• An impact with seismic activity being measured globally occurs once a year (optimistic) to possible once every ten years. (moment magnitude 10^14 J, giving a magnitude of 3.5) [1]

• Considering marsquakes as a seismic source• For maximum magnitude

• Compare to intraplate oceanic earthquakes• Away from plate boundaries and lithosphere is cooling

• Largest estimated marsquake possible is magnitude 7 [2]• For average magnitude

• Lithospheric stresses caused by cooling usually generate events up to a magnitude of 6. [2]

Next step is to figure out how much material is needed, how to send the data collected from the sites, and how these stations will be set up.

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APPENDIX I – FINDING MAGNITUDES

Gutenberg-Richter magnitude energy M = 0.67 x log10(mag[J]) – 5.87 [3]

M is the seismic magnitude and E is the kinetic energy release of the impactor in Joules.

The table below is from N.A. Teanby, J. Wookey, 2011 [1], and it models the cratering rate on Mars, the amount of energy released by each impact (J), the magnitude of each impact, and the diameter of the impact crater (m).

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APPENDIX II - STATION DISTRIBUTION• Surface Area (SA) of Earth ~510e6 km2

• USGS Global Seismic Network (GSN) has ~ 150 stations globally• If evenly distributed 1 station / 3.4e6 km2

• Approx. SA of land mass on Earth is ~30% of total SA, so ~ 150e6 km2, 150 stations

• If evenly distributed 1 station / 1e6 km2

• SA of Moon ~ 38e6 km21• Had 5 separate seismometers (1 / 7.6e6 km2)

• Was able to provide a detailed look at the Moon’s interior

• SA Mars ~ 145e6 km2

• If there was 40 stations evenly distributed there would be 1 station / 3.6e6 km2

• If there was 145 stations evenly distributed there would be 1 station / 1e6 km2

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APPENDIX III – AREA FOR 1 STATION

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For 145 stations relatively evenly spaced globally gives 1 station / 1e6 km2.The red box is the region under 1 station.

APPENDIX IV – OBSERVED BEDROCK

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Green areas are identified bedrock on the surface that we can use. Uses a thermal inertia > 1200 J m-2 K-1 s-1/2 as bedrock. [4]

REFERENCES[1] Teanby, N. A., Wookey, J., “Seismic detection of meteorite impacts on

Mars,” Physics of the Earth and Planetary Interiors. vol. 186, 2011, pp. 70-80.

[2] Golombek, M. P., ‘Constraints on the Largest Marsquake,” Abstracts of the 25th Lunar and Planetary Science Conference, 1994, pp. 441-442.

[3] Collins, G. S., Melosh, H. J., Marcus, R. A., “Earth Impact Effects Program: Aweb-based computer program for calculating the regional environmental consequences of a meteoroid impact on Earth,” Meteoritics & Planetary Science, vol. 40, 2005, pp. 817-840.

[4] Edwards, C. S., Bandfield, J. L., Christensen, P. R., Fergason, R. L., “Global distribution of bedrock exposures on Mars using THEMIS high-resolution thermal inertia,” Journal of Geophysical Research, vol. 114, 2009, pp. 1-18.

[5] “NASA Probe Counts Space Rock Impacts on Mars,” NASA Available:https://www.jpl.nasa.gov/news/news.php?release=2013-162

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LANDING SITE FOR REENTRY SPACECRAFT

Michael RoseMission Design

Science Support2/27/2018

146

THE PROBLEM

Objective: • Determine landing location for cycler taxi

so Ground Transport can develop retrieval system accurately

• Determine landing ellipse for moon missions so Science Support can develop retrieval systems for the payload accurately

Requirements: • There should be no major large craters

within 1 km of the landing site• Landing site needs to be a safe distance

away from city, but closeConsiderations:

• To reduce complexity, assume same targeted landing site for all reentry vehicles

• Use Monte Carlo simulation of 2000 runs, with a 3-𝛔𝛔 ellipse

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Satellite CAD Model of moon mission created by Logan Kirsch

THE SOLUTION

148

• Cycler taxi ellipse is 50 m x 50 m and is centered at (89.283oE, -36.471oN) at 16.9 km from the city

• Phobos mission ellipse is centered at the same location and is 84.2 km x 13.8 km, with a minimum distance of 10 km from the city, and a maximum distance of 24.6 km from the city.

• Deimos mission ellipse is centered at the same location and is 78.6 km x 13.6 km, with a minimum distance of 10 km from the city, and a maximum distance of 23.8 km from the city. 148

Image credit and landing site collaborated with Alaina Glidden

A-1: SIMULATION OF RESULTS

Monte Carlo Simulation of 2000 runs. Each ellipse is a 3-𝛔𝛔 ellipse (989 out of 1000 trajectories will land inside the ellipse). The majority of trajectories are near the targeted landing site (center of ellipse)

149Figure 2: Phobos landing analysis

Figure 1: Deimos landing analysis

Mission Lander Semimajor axis a [km]

Semiminor axis b [km]

Phobos 42.1 6.9

Deimos 39.3 6.8

A-2: MODEL ASSUMPTIONS

• Cycler Lander can land in a 50x50 meter ellipse with Terrain Contour Matching (TERCOM, credit: Annie Ping) and human piloting (credit: John Cleveland)

• Cycler lander, Phobos lander, and Deimos lander can get in correct inclination before re entry to land in correct location

• CD is constant for Phobos and Deimos lander reentry ellipse analysis• flight path angle = -14o at an altitude of 80 km for Phobos Lander [6]• Wind effects are ignored in calculating landing ellipse• Propulsion system on the Phobos and Deimos Lander, similar to the one used on the Taxi

Lander, starts retrograde thrust at around an altitude = 10 km• Span on Phobos and Deimos Lander does not have a huge impact on landing ellipse (see

slide A-4)• A minimum distance of 10 km from the city to the nearest point on the landing ellipse is a

safe distance away for the landing site• For modelling ellipse, the best ellipse is the one with the minimum amount of area

150

A-3: ERROR ASSUMPTIONS

The following are assumptions used in spacecraft parameter errors the in the Monte Carlo Simulation of 2000 runs [6]. These error values use a Gaussian distribution.

151

⍴ error 7% [1], [4], [5]

V error 100 m/s

CD error 4.062% [2]

Mass error 2 kg [6]

𝝲𝝲 error .6 [6]

152

A-4: Analysis of Span on landing

• Unsure about span of reentry vehicle• The table below shows effect of span on landing ellipse• Monte Carlo Simulation of 2000 trajectories • 3-𝞂𝞂 ellipse (98.9% of trajectories land within the ellipse) [3]• Center of Ellipse is the targeted, optimal trajectory [3]• These values and figures are for the Phobos mission.

Conclusion:

● Span has little effect, use S = 10 m2 for Phobos and Deimos spacecraft

152

Span S (m2) semimajor axis a (km) semiminor axis b (km)

3 45.8 7

5 43.4 7.1

10 42.1 6.9

20 45.2 6.4

Figure 3: S = 10 m2

Figure 4: S = 5 m2

A-5: REFERENCES[1] Schilling, G.F., “Limiting Model Atmospheres of Mars,” The Rand Corporation [online],

https://www.rand.org/content/dam/rand/pubs/reports/2009/R402.pdf [retrieved 18 Feb. 2018][2] Saltzman, E. J., Wang K. C., and Iliff K. W., “Aerodynamic Assessment of Flight-Determined

Subsonic Lift and Drag Characteristics of Seven Lifting-Body and Wing-Body Reentry Vehicle Configurations,” Nasa [online], https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20030003696.pdf [retrieved 18 Feb. 2018]

[3] Lakdawalla, E., “Landing ellipses,” The Planetary Society [online], http://www.planetary.org/blogs/emily-lakdawalla/2008/1425.html [retrieved 18 Feb. 2018]

[4] Glenn Research Center, “Mars Atmosphere Model,” Nasa [online], https://www.grc.nasa.gov/www/k-12/airplane/atmosmrm.html [retrieved 18 Feb. 2018]

[5] Martinez I., “Thermal Characteristics of the Space Environment,” Space Environment [online], http://webserver.dmt.upm.es/~isidoro/tc3/Space%20environment.pdf [retrieved 18 Feb.

2018][6] Scott A. Striepe, D. W. Way, A. M. Dwyer, and J. Balaram. "Mars Science Laboratory Simulations

for Entry, Descent, and Landing", Journal of Spacecraft and Rockets, Vol. 43, No. 2 (2006), pp. 311- 323. https://doi-org.ezproxy.lib.purdue.edu/10.2514/1.19649

Data for the Phobos and Deimos missions (entry velocity, entry mass, etc) is provided by Riley Viveros

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A-6: CODE FOR LANDING ELLIPSE% This script calculates the landing trajectory of a given spacecraft onto% the martian surface. It then does a Monte Carlo Simulation to calculate% the smallest 3-sigma (98.8% accuracy) Landing ellipse (landing footprint)%% By Michael Rose, last modified 2017-02-16

clear;close all; clc;%% basic inputst0 = 0; %initial start time [sec]tf = 5000; %final end time [sec]dt = t0:.1:tf;num_MCS = 2500; %number of iterations used for monte carlo simulationacc = .989; %accuracy for the ellipse (using 3-sigma accuracy = .988)%% variations (errors) in initial conditions. density error not included yetincl_error = .2; %inclination error [deg]gamma_error = .2; %flight path angle error[deg]V_error = 100; %spacecraft velocity error[m/s]pos_error = 0; %spacecraft position error[m];C_D_error = .0528; %drag coeff errorMass_error = 600; %mass of spacecraft error [kg];

154

%% The Ideal conditions. From these, we can produce the ideal trajecotry% and landing location. This location is used for the center of the% landing ellipse

g = 3.73; %gravity constatnt [m/s^2]C_D_id = 1.3;M_id = 3066;gamma_id = -5; %degrees;incln_id = 45; %degrees;S_id = 3; %m^2x_0_id = 0;y_0_id = 0;z_0_id = 80000; %metersV_mag_id = 4186; %m/sVz_0_id = V_mag_id*sind(gamma_id);Vx_0_id = V_mag_id*cosd(gamma_id)*cosd(incln_id);Vy_0_id = V_mag_id*cosd(gamma_id)*sind(incln_id);u02_id = [x_0_id,y_0_id,z_0_id,Vx_0_id,Vy_0_id,Vz_0_id];

warning('off','all')

A-6: CODE FOR LANDING ELLIPSExoverFcn = @(t_id,x_id) HitSurfaceFcn(t_id,x_id,R); %stops integration when spacecraft reaches altitude of 0 meteresoptions = odeset('Events',xoverFcn,'RelTol',1e-11,'AbsTol',1e-11);[t_id,x_id]=ode45(@(t_id,x_id)landing_location_ODE(t_id,x_id,C_D_id,S_id,M_id,g),dt,u02_id,options);

end_point = numel(x_id(:,1));x_pos_id = x_id(end_point,1); %ideal x position [m]y_pos_id = x_id(end_point,1); %ideal y position [m]

%% max amount of g's experiencedV =sqrt(x_id(:,4).^2+x_id(:,5).^2+x_id(:,6).^2);for i = 2:(size(t_id))

g_force(i-1) = ((V(i)-V(i-1))/(t_id(i)-t_id(i-1)))/9.81;endmax_g = max(abs(g_force))

%% This section is the same logic as the ideal condition, only we now apply% A Monte Carlo simulation onto the trajecotry.tic

155

for index = 1:num_MCS%%% assume coeff could be anywhere

randomly between the ideal case and +-%%% the errorC_D = C_D_id+C_D_error*randn;M = M_id+Mass_error*randn;gamma = gamma_id+gamma_error*randn;

%degrees;incln = incln_id+incl_error*randn;

%degrees;S = S_id;

x_0 = 0;y_0 = 0;z_0 = z_0_id; %meters

V_mag = V_mag_id+V_error*randn; %m/sVz_0 = V_mag*sind(gamma);Vx_0 = V_mag*cosd(gamma)*cosd(incln);Vy_0 = V_mag*cosd(gamma)*sind(incln);

u02 = [x_0,y_0,z_0,Vx_0,Vy_0,Vz_0];ww = randn;xoverFcn = @(t,x)

HitSurfaceFcn(t,x,R);options =

odeset('Events',xoverFcn,'RelTol',1e-11,'AbsTol',1e-11);

A-6: CODE FOR LANDING ELLIPSE[t,x]=ode45(@(t,x)landing_location_ODE_MCS(t,x,C_D,S,M,g,ww),dt,u02,options);

end_point = numel(x(:,1));

x_pos(index) = x(end_point,1); %x position of each of the random trajecotries

y_pos(index) = x(end_point,2); %y position of each of the random trajecotries

end%% This section converts the x axis to the planar down range motion, and% y axis to be the cross-range motiontocx_pos_ell_id = cosd(incln_id).*x_pos_id+sind(incln_id).*y_pos_id;y_pos_ell_id = -sind(incln_id).*x_pos_id+cosd(incln_id).*y_pos_id;

x_pos_ell = (cosd(incln_id).*x_pos+sind(incln_id).*y_pos)-x_pos_ell_id;y_pos_ell = -sind(incln_id).*x_pos+cosd(incln_id).*y_pos-y_pos_ell_id;

156

%%%converts positon from meters to kmx_pos_ell_id = x_pos_ell_id/1000;y_pos_ell_id = y_pos_ell_id/1000;x_pos_ell = x_pos_ell/1000;y_pos_ell = y_pos_ell/1000;

figure(1)hold onplot(x_pos_ell,y_pos_ell,'r*');plot(0,0,'b*','MarkerSize',20);axis squareaxis equal

%% this section determines the minimum value for the semimajor/minoraxis% (a,b respectively) that meets the accuracy requirment.index = 1;tic

A-6: CODE FOR LANDING ELLIPSEfor b = 1:.1:1.5*max(abs(y_pos_ell))

for a = 1:.1:1.5*max(abs(x_pos_ell))num_in_bounds =

(x_pos_ell.^2)/a^2+(y_pos_ell.^2)/b^2 <=1;if sum(num_in_bounds) >= acc*num_MCScheck_num(index) =

sum(num_in_bounds);a_min(index) = a;b_min(index) = b;index = index+1;endend

end

for a = 1:.1:1.5*max(abs(x_pos_ell))for b = 1:.1:1.5*max(abs(y_pos_ell))

num_in_bounds = (x_pos_ell.^2)/a^2+(y_pos_ell.^2)/b^2 <=1;

if sum(num_in_bounds) >= acc*num_MCScheck_num(index) =

sum(num_in_bounds);a_min(index) = a;b_min(index) = b;index = index+1;end

endendtocArea_ell = pi.*a_min.*b_min;min_loc = (find(min(Area_ell))); 157

true_a = a_min(min_loc(1))true_b = b_min(min_loc(1))Min_area = Area_ell(min_loc(1))

check_num_min = check_num(min_loc(1))%% This section plots the landing ellipsee = sqrt(1-(true_b/true_a)^2); %eccentricityTheta_star = 0; %true anomaly

P = true_a*(1-e^2);n = 1;while Theta_star <=360*(pi/180)

R = (P)/(1+e*cos(Theta_star)); %calculates R for ellipse at different angles

e_dir(n) = R*cos(Theta_star); %calculates e_hat dir for ellipse

p_dir(n) = R*sin(Theta_star); %calculates p_hat dir for ellipse

Theta_star = Theta_star+.001;n = n+1;

endfigure(1)hold onplot(e_dir+true_a*e,p_dir)title('Landing Ellipse');xlabel('distance [km]');ylabel('distance [km]');

A-7: CODE FOR LANDING ODE% This script integrates the EOM's for the landing_ellipse_final.m script% By Michael Rose, last modified 2017-02-16function f= landing_location_ODE_MCS(t,x,C_D,S,M,g,ww)h = x(3);xp = zeros(6,1);V=sqrt(x(4)^2+x(5)^2+x(6)^2);%% Denisty model for mars based on altitude. Still need to incorporate% variations of density for Monte Carlo simulationif x(3) > 7000

rho = (.699*exp(-.00009*h))/(.1921*(-23.4-.00222*h+273.1));

rho = rho+.07*rho*ww;else

rho = (.699*exp(-.00009*h))/(.1921*(-23.4-.00222*h+273.1));

rho = rho+.07*rho*ww;end

158

xp(1) = x(4);xp(2) = x(5);xp(3) = x(6);%% These are the equations of motion for the spacecraftxp(4) = -((rho*C_D*S)/(2*M))*V*x(4);xp(5) = -((rho*C_D*S)/(2*M))*V*x(5);xp(6) = -((rho*C_D*S)/(2*M))*V*x(6)-g;

f=[xp(1);xp(2);xp(3);xp(4);xp(5);xp(6)];

end

Terraforming Mars

Brandon SmithScience

Science Support2/27/18

2/27/2018 159

The ProblemConsiderations- One of the primary goals for the project- “The people of Mars have embarked on a

long-term project of terraforming. They envision a day in the far future where the solar system contains two blue marbles. What does the terraforming project look like at this point?” [1]- Ambitious- Never been done before- Will take a relatively long time to accomplish.- 2 stage problem- Rebuild the Martian magnetosphere- Rebuild the Martian atmosphere- Knowns- Rate of atmospheric loss:

3156 Mg/year - To solve- What is the MPV for each sub-solution?- What are the benefits/drawbacks of each sub-solution?

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Requirements: - A Magnetosphere tail that

envelops all of the Martian system (Mars, satellites, etc).

- The atmospheric loss rate is severely reduced, to about Earth levels, if possible

- The process creates a stable atmosphere, with similar composition to that of Earth.

SOLUTION1. Rebuilding theMagnetosphere

161

2. Rebuilding theAtmosphere

1A. L1 Magnetic “Shield”- Benefits

Materials are not that hard to obtainRequires no power input to work

- DrawbacksRequires it to be built in spaceRequires transport to the L1 pointCostly, in terms of materialsWill take a long time to produce

Impacting the Surface- Impacting the surface would

release volatiles within the Martian crust

- Every so often (2-3 years), we would launch to the asteroid belt, obtain some asteroids, and launch them into the Martian poles

- After this, we can start to vent out any remaining gasses we need in order to recreate Earth’s atmosphere (Oxygen, Carbon Dioxide, etc.)

- Total mass to release volatiles in the Martian poles: 1016 kg (Megan Harwell)

Conclusions: Both processes for rebuilding the Magnetosphere require tremendous amounts of resources. However, the ring system requires rarer minerals that may take a longer amount of time to obtain and refine. As such, given the choice between the two systems, I recommend the colony begin to set aside excess Iron and Nickle to begin production of the L1 Magnetic Shield in order to star the process of terraforming.

2A. Planetary Ring System- BenefitsOn MarsLow volume (0.24 km3)- DrawbacksMaterials needed are rare on Mars Costly, in terms of minerals

Will take a long time to produce

APPENDIX 1: L1 LAGRANGE “SHIELD”

162

L1 Lagrange “Magnetic Shield” Source: Green, J. L., Hollingsworth, J., Brain, D., Airapetian, V., Glocer, A., Pulkkinen, A., Dong, C., and Bamford, R., A Future Mars environment for science and exploration, 2017.

APPENDIX 2: CROSS SECTION OF RING

163

Cross Section of ring Source: Motojima, O., and Yanagi, N., “Feasibility of Artificial

Geomagnetic Field Generation by a Superconducting Ring Network,” National Institute for Fusion Science, Japan, 2008.

APPENDIX 3: COMPARISON OF L1 SHIELD AND RING SYSTEM

164

POSSIBLEWAYS TO REBUILD MAGNETOSPHERE

L1 “Magnetic Shield”

Ring System (120 rings)

TOTAL MASS 6.11 X 1019 Mg 7.982 X 107 MgTOTAL POWER 0 W ~ 10 GW TOTAL VOLUME 7.61 X 109 km3 0.24 km3

REQUIREDMATERIALS

Iron, Nickle Yttrium, Barium, copper oxide

DISTANCE FROM MARS

~ 1 X 106 km 0 km (On Mars)

CHOICE X

APPENDIX 4: CALCULATING THE L1 “MAGNETIC SHIELD”

• Example “Magnetic Shield”: Recreate Earth’s core• Radius of Earth’s Inner Core: 1220 km• Volume of the inner core: 4/3 pi (1220)3

= 7.61 X 109 km3

• Volume of Iron: 0.85 X (7.61 X 109 km3)= 6.47 X 109 km3

• Mass of Iron: (6.47 X 1018) * 7870 kg/m3 = 5.09 X 1022 kg• Volume of Nickel: 0.15 X (7.61 X 109 km3) = 1.14 X 109 km3

• Mass of Nickel: (1.14 X 1018) * 8908 kg/m3 = 1.02 X 1022 kg • Total Mass of “Magnetic Shield: 1.02 X 1022 + 5.09 X 1022

= 6.11 X 1022 kg = 6.11 X 1019 Mg

165

CITATIONS

[1] Longustki, J., Minton, D., Lecture #1: Project Future Mars, 2018[2] Motojima, O., and Yanagi, N., “Feasibility of Artificial

Geomagnetic Field Generation by a Superconducting Ring Network,” National Institute for Fusion Science, Japan, 2008.

[3] Green, J. L., Hollingsworth, J., Brain, D., Airapetian, V., Glocer, A., Pulkkinen, A., Dong, C., and Bamford, R., A Future Mars environment for science and exploration, 2017.

166

THE STRUCTURE OF ISOLATED SHELTERS ON MARS

Trevor WaldmanStructures Discipline Group

Science Support Vehicle & Systems GroupFebruary 27, 2018

2/27/2018 167

THE PROBLEM

• Shelters away from the main city• Any crewed missions (Sci., potentially Res. Ex.)• Storage facilities

• Shelter construction:• 18 m3/person [2] • Aboveground dome; bury under 4 m rock [3]

• Requirements• Radiation dose ≤2.4 mSv/yr. (Longuski) [1]• 3 people + facilities + storage (Sci., potentially Res.

Ex.)

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SOLUTION

• 2.95 m inner diameter• 4 cm Al “1060 Alloy” wall*• 4.6 m long tunnel• 14.4 Mg Al• FEA in appendices• Heat loss: 6.4 kW

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HEAT TRANSFER CODE

6.36 kWHeat loss

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FEA - SOLIDWORKS

• 4 cm Al “1060 Alloy” – 14.44 Mg• Above dome: cyl. of basaltrock:

D = 3 m, H = 7 m• with 3 m tall cone cut out of bottom

• Above tunnel: Rect. prism: H = 4 m • Also: Caterpillar D9 (49.0 Mg)

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FEA - STRESS

2/27/2018 172

FEA – DISPLACEMENT (MM)

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FEA - STRAIN

2/27/2018 174

FEA - STRESS, W/O DOZER

2/27/2018 175

SOURCES[1] “Natural Background Radiation,” Nov. 2014. Retrieved from

http://nuclearsafety.gc.ca/eng/resources/fact-sheets/natural-background-radiation.cfm

[2] Whitmire, A., Leveton, L., Broughton, H., Basner, M., Kearney, A., Ikuma, L., and Morris, M., “Minimum Acceptable Net Habitable Volume for Long-Duration Exploration Missions,” NASA Human Research Program, Apr. 2015. Retrieved from https://ston.jsc.nasa.gov/collections/trs/_techrep/TM-2015-218564.pdf

[3] Hassler, D. M., Zeitlin, C., Wimmer-Schweingruber, R. F., Ehresmann, B., Rafkin, S., Eigenbrode, J. L., Brinza, D. E., Weigle, G., Böttcher S., Böhm, E., Burmeister, S., Guo, J., Köhler, J., Martin, C., Reitz, G., Cucinotta, F. A., Kim, M., Grinspoon, D., Bullock, M. A., Posner, A., Gomez-Elvira, J., Vasavada, A., Grotzinger, J. P., “Mars’ Surface Radiation Environment Measured with the Mars Science Laboratory’s Curiosity Rover,” Science.

[4] “Table of Total Emissivity,” Omega Retrieved from: https://www.omega.com/temperature/Z/pdf/z088-089.pdf.

[5] “Thermal Conductivity of common Materials and Gases,” Engineering Toolbox Retrieved from: https://www.engineeringtoolbox.com/thermal-conductivity-d_429.html.

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VIABILITY OF CYCLER VEHICLE AS A RELAY

Eliot Toumey

Mission Design

Space Transportation

2/27/2018

2/27/2018 177

PROBLEM: CAN THE CYCLER BE USED AS AN EARTH-MARS RELAY?

2/27/2018 178

Context:• Continuous Earth-Mars communication

required by customer• Solar Conjunction between Earth and Mars

occurs twice per synodic period requiring additional link

Requirements:• Sun-Earth-Cycler and Sun-Mars-Cycler

Angular separation greater than 3 degrees during periods of solar conjunction (Ryan Duong and Noah Gordon)

Assume:• 3 degrees sufficient to avoid interferenceProblem: • Can the cycler be used as an Earth-Mars

relay during conjunction of Sun-Earth-Mars?

SOLUTION

2/27/2018 179

Worst case:Link >3°

E →M

C1→E

C1→M

C1→C2

C2→E

C2→M

Results: Cycler vehicle cannot be used

as a relay during solar conjunction once every 15 years

All other instances of solar conjunction (2 per synodic period) can be avoided using the cycler

MPV Implications: At least one additional relay required to maintain continuous communication.

Cycler only Coms

Cycler as Relay

Power (kW) 3.5 40

Antenna Diameter (m)

25 25

Communication link data from Noah Gordon

APPENDIX A: 2 SYNODIC PERIODS

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APPENDIX B: SCRIPT LISTING

2/27/2018 5

APPENDIX B: SCRIPT LISTING

2/27/2018 6

APPENDIX C: METHOD

2/27/2018 7

Angular separation calculated using the relation:

• Inertial state vector of cycler provided by Rob Potter. • Lagrange interpolation with order 5 used to increase the resolution of the angle

data. • Mars and Earth state vectors generated using Earth and Mars ephemerides

included in MATLAB R2016a

APPENDIX D: REFERENCES

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ROTATIONAL CONTROL OF CYCLER

Christopher HunnewellPropulsion

Space Transport2/27/2018

2/27/2018 185

PROBLEM

Cycler must maintain .1 G of acceleration during entire trip (Customer)

Vehicle must rotate at .1651 radians per second during flight (Clevland)

Vehicle must not be rotating during docking with taxi (Toumey)

2/27/2018 186

SOLUTION

8 Monopropellant thrusters around outer ring of cycler

Total mass including propellant 6.905 Mg

Total power draw 1470 W

Hydrazine system

Time to accelerate or decelerate fully is 558 seconds

2/27/2018 187

Image by Anad Iyer

CYCLER DETAILS AND REQUIREMENTS

Cycler moment of inertia is 526882427 kg-m2

(Iyer)

Total angular momentum when rotating is 1.3845 * 107 N-m-s

Outer radius of 36 m (Iyer)

188

THRUSTER ANALYSIS

MR-80B by Aerojet Rocketdyne

ISP of 225

Max thrust of 3100 N

Mass per thruster is 8.51 kg

Propellant mass required of 6.386 Mg

Power per thruster is 183.5 W

189

REACTION WHEELS

Largest available is Rockwell Collins RDR 68

One unit can hold 68 N-m-s

Power draw at max draw is 90 W per unit

Power draw during steady state operation is 5 W per unit

Mass is 7.6 kg per unit

190

COMPARISON

191

Number Needed

Mass [Mg]

Power max [W]

Power at steady state [w]

Reaction Wheels

2.036 * 105 1547 1.8324 * 107

1.018 * 106

MonopropellantThrusters

8 6.905 1470 0

CALCULATIONS

192

REFERENCES[1] “RDR 68 Momentum and Reaction Wheels,” RDR 68 Momentum and Reaction WheelsAvailable: https://www.rockwellcollins.com/Products_and_Services/Defense/Platforms/Space/RDR_68_Momentum_and_Reaction_Wheel.aspx.

[2] “Monopropellant Rocket Engines,” Monopropellant Rocket Engines | Aerojet RocketdyneAvailable: http://www.rocket.com/propulsion-systems/monopropellant-rockets.

193

CYCLER VEHICLE RADIATION SHIELDING

Jacob RoeStructures

Space Transportation2/27/18

2/5/2018 194

RADIATION SHIELDING

The Problem: Mitigate effects of radiation to prevent passengers from increased risk of health issues including cancer.Requirements:• Match annual limit of 500 mSv for 310 day trip (Pharazyn, Toumey)

Assumptions:• Only need to shield parts of habitable ring (Pharazyn)• Unshield dose equivalent rate of 1.84 mSv/day [2]

Need to Determine• Mass of shielding• Materials used

195

POLYETHYLENE BRICKS

• Effectiveness of radiation shielding proportional to number of nuclear interactions [3]

• Light materials with smaller nuclei, such as hydrogen, provide the best shielding [3]

• Liquid hydrogen best, but hard to store

• Polyethylene (CH2)provides similar shielding

• Total mass of 80 Mgto cover inhabited areasof cycler

• Difficult to decrease doselimit further

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RADIATION SOURCES

[1] Rask, J., Vercoutere, W., Navarro, B.J., and Krause, A., “Space Faring The Radiation Challenge,” NASA EP–2008–08–116–MSFC

[2] Zeitlin, C., Hassler, D.M., Cucinotta, F.A., Ehresmann, B., Wimmer-Schweingruber, R.F., Brinza, D.E., Kang, S., Weigle, G., Böttcher, S., Böhm, E., Burmeister, S., Guo, J., Köhler, J., Martin, C. Posner, A., Rafkin, S., and Reitz, G.,“Measurements of Energetic Particle Radiation in Transit to Mars on the Mars Science Laboratory,” Science, Vol. 340, No. 6136, 2013[3] Cucinotta, F.A., Kim, M.Y., Chappell, L.J., “Evaluating Shielding Approaches to Reduce Space Radiation Cancer Risks,” NASA TM-2012-217361

197

MATLAB CODE

198

MATLAB CODE

199

MATLAB OUTPUT

200

IMPROVING OXYGEN PRODUCTION ON THE

CYCLERAndrew PharazynHuman Factors

Space TransportationFebruary 27, 2018

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PROBLEM

Problem: Passengers aboard the cycler need to have a readily available and replenishing supply of oxygen to survive, and currently the system requires a 15.0 Mg water resupply

Requirements:• Must eliminate the need for a water

resupply at the end of each journey• Must turn oxygen production into a

closed-loop process

Assumptions: • Fifty people on cycler• 13 Mg of oxygen need for entire journey• Cabin is pressurized to 101.3 kPa

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SOLUTION

The addition of the “sabatier reaction” and pyrolysis can completely eliminate the need for the water resupply needed for electrolysis.

Sabatier Reaction:• By heating CO2 and two H2 atoms to 400°C, water and methane are

formed [1]• Water is used for oxygen production, and methane goes through

pyrolysis

Pyrolysis of Methane:• Heating methane to 1200°C produces the products carbon and H2 [2]• Carbon is disposed as waste and the H2 is sent back to the sabatier

system

203

APPENDIX• [1] Junaedi, C., Hawley, K., Walsh, D., Roychoudhury, S., Abney, M., and Perry,

J., “Compact and Lightweight Sabatier Reactor for Carbon Dioxide Reduction,” 41st International Conference on Environmental Systems, 2011.

• [2] Sharma, P. K., Rapp, D., and Rahotgi, N. K., “METHANE PYROLYSIS AND DISPOSING OFF RESULTING CARBON.,” Jan. 1999.

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