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GROUP 1 PRESENTATION
March 27th, 2018
3/27/2018 1
INTEGRATING CAD AND STORYBOARD
Ricardo GomezAssistant Project Manager
March 27th, 2018
3/27/2018 2
CYCLER
3/27/2018 3
CAD credit: Anand Iyer
3/27/2018 4
MINING SITE
CAD credit: Logan Kirsch, Sean Thompson, Anand Iyer, Adit Khajuria
3/27/2018 5
MARS COMMS NETWORK
CAD credit: Ryan Duong and Sam Zemlicka-Retzlaff
3/27/2018 6
AIRLOCK TO CITY
CAD credit: Sean Thompson, Logan Kirsch
3/27/2018 7
CITY
CAD credit: Subhiksha Raman
3/27/2018 8
SCIENCE
CAD credit: Logan Kirsch
3/27/2018 9
LAUNCH PAD
CAD credit: Logan Kirsch
HOUSING BUILDING EXTERIORS
Halen BlairStructures
City Infrastructure3/6/18
3/27/2018 10
PROBLEM– BUILDINGS ARE JUST FRAMES
• Initial structure analysis of housing buildings (Apartment, Hospital, Gym, Grocer) only consists of building frame and forces on interior
• Need to address outer covering of buildings
• Main purpose is to simply serve as a barrier to prevent falls
3/27/2018 11
CAD by Subhiksha Raman,
SOLUTION – THIN STEEL AND WINDOWS
• Building exteriors will be covered in a very thin 0.5 mm thick sheet of A36 structural steel with
• 36 meters squared of 1 mm thick windows per 20 m long section of wall, resulting in three or four windows per side of every floor depending on building dimensions.
• Simply take surface area using dimensions of buildings, and subtract from that the surface area of windows. Multiply each of these by their respective thicknesses and densities to receive mass of each required for the city.
3/27/2018 12
Mass of steel for building skin
[Mg]Mass of glass for windows [Mg]
Total City Usage 908 5,100
APPENDIX – STEEL AND GLASS DATA
Individual Buildings City Totals
# of Apartment
Floors
Mass of Steel for
building skin [Mg]
Mass of Glass for
building windows
[Mg]
Mass of Steel for
building skin [Mg]
Mass of Glass for
building windows
[Mg]
Individual
Buildings
13 Floors 8.92 50.9 125 713
18 Floors 12.3 69.1 246 1,380
21 Floors 14.4 80.6 230 1,290
22 Floors 15.1 84.5 242 1,350
Hospital 3.09 17.3 12.4 69.2
Gym 4.63 25.9 27.8 155
Restaurant
/Grocer3.09 17.3 24.7 138
3/27/2018 13
LIGHTINGMatt Prymek
ScienceCity / Food Production
3/27/18
2/13/2018 14
ProblemThe City is underground and lacks any natural light sources.
● Require high-intensity, high-efficiency light sources for crops● Require lighting appropriate for both individual apartments, large public spaces● Light can’t make people hate themselves - live with flickering fluorescents?
However, Nearly every form of conventional lighting requires minerals that are difficult to produce on Mars:
Lighting System Material (per bulb)Material
ProductionLifespan (hours)
Efficiency (lm/W)
Incandescent < 1 g Tungsten [1]0.891 g
Tungsten~1,000 -
3,000[2][3] 8
Fluorescent
1-3 mg Mercury [4]< 1 mg Europium,
Lanthanum, Yttrium [5]
3.56 mg Mercury
0.890 mg Europium ~15,000 [4] ~81.3
Electron-Stimulated Luminescence
< 0.5 g Europium, Cadmium, Yttrium
[6]
0.890 mg Europium14.3 mg
Cadmium11,000 ~ 8
LED0.22 mg Gallium0.236 mg Arsenic
3.56 mg Gallium2.28 mg Arsenic >150,000 111
SOLUTIONThe Sulfur Plasma Light Engine
+ Light piping for light distribution within apartments
Lighting SystemMass (kg)
Volume (cm3)
Power (W)
Brightness (lm)
Efficiency (lm/W)
Ceravison ionCORE [9] 1.9 4,400 400 26,000 65
Plasma-i AS1300 [10] 9.0 8,200 1360 163,000 120
System(City)
Av. Lighting [Lux]
Power[MW]
Volume[m3]
Mass[Mg]
Farming ~16,300 81.5 671 728
Residential ~200 2.46 27.1 25.0
Office ~500 0.684 7.52 3.25
Manufacturing 750-1,500 3.99 24.3 26.1
Public 100-700 0.344 2.10 4.55
TOTAL: ~ 89.0 732 787 Image: Subhiksha Raman.
APPENDIXSystem Lux
Public areas with dark surroundings 20 - 50
Simple orientation for short visits 50 - 100
Working areas where visual tasks are only occasionally performed 100 - 150
Warehouses, homes, theaters, archives 150
Easy office work, classes 250
Normal office work, PC work, study library, groceries, show rooms, laboratories
500
Normal drawing work, detailed mechanical workshops, operation theatres
750
Detailed drawing work, very detailed mechanical works 1,000
Tasks of low contrast and very small size for prolonged periods of time 1,500 – 2,000
Very prolonged and exacting visual tasks 2,000 – 5,000
Very special visual tasks, extremely low contrast, small size 10,000 –20,000
APPENDIX
System Av. Lighting [Lux]
Power[MW]
Volume[m3]
Al[Mg/yr]
Cu[Mg/yr]
CaO2[kg/yr]
SiO2[kg/yr]
S[g/yr]
Ar[g/yr]
Farming ~16,300 81.5 671 12.2 1.840 26.9 10.1 140 14.9
Residential ~200 2.46 27.1 0.917 0.108 0.539 10.8 28.7 3.07
Office ~500 0.684 7.52 1.02 0.120 0.600 2.82 7.79 0.833
Manufacturing 750-1,500 3.99 24.3 8.74 0.514 1.03 4.83 13.4 1.43
Public 100-700 0.344 2.10 0.755 0.0444 0.0887 0.416 1.15 0.123
TOTAL: ~ 89.0 732 23.6 2.63 29.2 29.0 191.0 20.4
Material Replacement Rates
APPENDIX
Image credit:[11] Image credit:[10]
SOURCES[1] “How to Make Money Recycling Tungsten from Old Light Bulbs”, Specialty Metals, http://www.specialtymetals.com/blog/2018/1/22/how-to-make-money-recycling-tungsten-from-old-light-bulbs. Accessed March 26, 2018.
[2] “What Does Average Rated Life Mean?”, Bulbs, https://www.bulbs.com/learning/arl.aspx. Accessed March 26, 2018.
[3] “40-Watt Incandescent G25 Globe Double Life Soft White Light Bulb (3-Pack)”, Home Depot, https://www.homedepot.com/p/GE-40-Watt-Incandescent-G25-Globe-Double-Life-Soft-White-Light-Bulb-3-Pack-40G25W-2L-TP3-6/203909191. Accessed March 26, 2018.
[4] “T8 Watt-Miser™ - G13 Cap“, GE Lighting Europe: E-Catalog, https://catalog.gelighting.com/lamp/linear-fluorescent/t8-tubes/f=t8-watt-miser-g13-cap/. Accessed March 26, 2018.
[5] “Fluorescent Lamp Phosphors”, LampTech - The Museum of Electric Lamp Technology, http://www.lamptech.co.uk/Documents/FL%20Phosphors.htm. Accessed March 26, 2018.
[6] Jankowiak, P., “Cathode Ray Tube Phosphors Of Interest To The Experimenter”, 2010, http://www.bunkerofdoom.com/tubes/crt/crt_phosphor_research.pdf. Accessed March 26, 2018.
[7] “R30 65 Watt Replacement Interior Flood”, Vu1, http://www.vu1corporation.com/products/index.html. Accessed March 26, 2018.
[7] Melcer, L. G, “Light-Emitting Diode (LED)”, MadeHow, http://www.madehow.com/Volume-1/Light-Emitting-Diode-LED.html. Accessed March 26, 2018.
[8] Nelson, J. A., & Bugbee, B. “Economic Analysis of Greenhouse Lighting: Light Emitting Diodes vs. High Intensity Discharge Fixtures”, PLOS ONE, Vol. 9, No. 6, 2014. Retrieved from https://doi.org/10.1371/journal.pone.0099010.
2/10/18 20
SOURCES[9] “ionCORE™ Light Engine”, Ceravision, http://www.ceravision.com/products. Accessed March 26, 2018.
[10] “Plasma-i AS1300 Light Engine”, Plasma International, http://www.plasma-i.com/plasma-i-products.htm. Accessed March 26, 2018.
[11] [1] A. J. Both, L. D. Albright, C. A. Chou, and R. W. Langhans, “A Microwave Powered Light Source For Plant Irradiation,” in III International Symposium on Artificial Lighting in Horticulture, 1997, pp. 189–194.
2/10/18 21
CITY ENTERTAINMENT
Lucas MoyerHuman Factors
City InfrastructureMarch 27, 2018
3/27/18 22
THE PROBLEM
• The citizens of Mars need a sufficient amount of entertainment within the city.
• There is a very limited amount of space and resources within the city for us to provide extra things such as entertainment for the citizens.
Requirements:• Select entertainment that appeals to all of the
population.• Allocate unassigned space for the citizens to use.• Ensure that entertainment is properly scaled due to
Martian gravity.• Incorporate physical activity into the entertainment
because the citizens need plenty of exercise.
3/27/18 23
THE SOLUTIONOutdoor Recreation (Per Module):
3/6/18 24
Image created by Subhiksha Raman
Indoor Recreation (Per Module):
Size of Space # of AreasUse for Space
20 m x 20 m 4 Unassigned
40 m x 40 m 2Sand
Volleyball/wallyball
20 m x 60 m 2 Basketball
20 m x 40 m 2 Basketball
TOTAL: 10
Earth size
(m)
Mars size (m)
Dimension: l x w x h l x w x h
Basketball hoop height 3.05 3.88
Basketball court 25.6 x 15.2 25.6 x 15.2
Volleyball/Wallyball net
height2.43
3.27
Wallyball court 12 x 6 x 6 23.80 x 11.90 x 11.90
Volleyball court 18 x 15.2 35.70 x 30.14
Size of Space # of AreasUse for Space
20 m x 40 m 2Movie Theater/Unassigned
20 m x 20 m 1Computer Lab/Unassigned
TOTAL: 3
APPENDIX: CAD
25
Image created by Logan KirschImage created by Logan Kirsch
APPENDIX
Additional Information:
• Movie theaters – Continuously add to their libraries by downloading new movies from Earth.
• Computer labs - Citizens can download things such as news, TV, movies, music, eBooks, etc.
• One floor in each apartment building is a designated “lounge area.”• There are enough computers for 1 out of every 25 people to use at any
given time (200 per module). (Manufacturing)• Each indoor recreation building has a total of 13 floors. Movie theaters
take up the bottom 6 floors in their buildings, with the 7 leftover floors unassigned. Computer labs take up the bottom 3 floors in their buildings, with the 10 leftover floors unassigned.
Comms Data Limits (per person) (Sam Alpert):• 1 hr news broadcast each day• 5 hrs of tv or movies/month • 10 Gb of internet/month
26
APPENDIX
Additional Information:
• A total workforce of 20 people are needed for general upkeep of outdoor recreation areas in the city.
• A total workforce of between 234 to 780 people are needed for all indoor recreation buildings in the city.
• Between 500 kW and 1 MW total is needed to power all indoor recreation buildings.
• Basketball and wallyball courts have a concrete base.
• Volleyball courts need a total of 1.49*103 Mg of sand.
27
REFERENCES
[1] Tyson, Jeff “How Movie Projectors Work”, HowStuffWorks (2018) https://entertainment.howstuffworks.com/movie-projector.htm
[2] (n.a.) “Basketball,” Sports Court Dimensions (2015),https://www.sportscourtdimensions.com/basketball/
[3] (n.a.) “The Standard Dimensions and Measurements of a Volleyball Court,” Sports Inspire (2018), https://sportsaspire.com/volleyball-court-dimensions
28
3/27/2018 29
AEROPONIC SUPPORT COLUMNS
Swapneel KulkarniStructures
Food Production3/26/2018
PROBLEM: SUPPORTING MASS OF CITY, CROPS, WATER TANKS ON AEROPONIC SYSTEM
Spacing Requirements: • Volume available per aeroponic building: 2.43 x 106 m3
• Total number of floors: 9• Each floor has an area of 90,000 m2
• Each floor is 2.75 m tall (except for water tanks floor)• Total number of Farming modules: 3232• Two such aeroponic buildings
Mass Requirements:• City mass atop each Aeroponic system (Halen Blair): 2,4996 Mg• Farming Mass per floor (Kelsey Delahanty): 716 Mg• Mass of water and tanks per floor (Jonathan Rohwer): 4,710 Mg
Constraint:• Support structures must not take more than 1% of area in each farming module
30
SOLUTION: STRUCTURAL STEEL COLUMNS
Input into code (Halen Blair) [1]: • Dimensions of each building: 300m x 280m x 27m
• Total weight to be supported: 29,706 Mg / Building
• Total number of support columns: 500
• Material: A36 Structural Steel (E = 200 GPa)
• Factor of safety: 10
Output:• Total mass of structure: 5.464 x 105 Mg
• Square beam side length required: 0.5665 m
• Total volume of structural elements: 70,055 m^3
Results from Stress Analysis:• Total mass of structural steel: 33,010 Mg
• Structural Life of one steel beam: 50 years
3/27/2018 31
FEM Analysis done by Swapneel Kulkarni
Images created by Kelsey Delahanty
APPENDIX: INPUT FOR CODE [1] AND STRESS ANALYSIS
3/27/2018 32
APPENDIX B: MODIFIED CODE
3/27/2018 33
APPENDIX: MODIFIED CODE (CONT’D)
3/27/2018 34
OVERVIEW OF THE MANUFACTURING SYSTEM
Eric ThurstonStructures Discipline
Ground Transportation and Manufacturing Groups3/27/18
35
THE PROBLEM- BUILDING ON MARS
What kind of factories are there? What kind of goods are manufactured on Mars, and how do the factories get their resources?
• Mission Specifications:• Everything used on Mars must be built or maintained with Mars resources
• Assumptions• Complex machines would originally come from Earth as part of the start-up
process• Considering only a steady-state system• Power comes from the city’s grid• All materials come from resource extraction• Martian citizens provide the labor required for manufacturing
• Functional Requirements:• Manufacturing must be able to produce everything designed by V&S groups
(materials and processes)• Must be able to produce materials at rates required by system lifetimes (flow rates)
36
THE SOLUTION – THE MANUFACTURING ECOSYSTEM
37
Manufacturing Lava Tube
Vehicle Assembly Building/Launch Site
Resource Extraction Sites
City Lava Tube
We’ve designed a manufacturing operation that fulfills the requirements of the rest of the civilization
Raw materials, old vehicles and equipment
New vehicles, equipment
Old rocketsRocket components
Components for city, food and comm’sManufacturing personnel, power, old TUV’s
APPENDIX I – V&S GROUP FLOW RATES
38
APPENDIX II – EXTRACTION RATES
39
APPENDIX III – MATERIAL BREAKDOWN
40
APPENDIX IV – MATERIAL BREAKDOWN
41
APPENDIX V – MATERIAL BREAKDOWN
42
APPENDIX VI – STEEL BREAKDOWN
43
APPENDIX VII – ALUMINUM BREAKDOWN
44
APPENDIX VIII – CONCRETE BREAKDOWN
45
APPENDIX IX – DATA FOR CHARTS
46
MANUFACTURING LAVA TUBE LAYOUT
Stuart McCrorie
Structures Discipline
Communications Infrastructure and Manufacturing Teams
3/27/2018
3/27/2018 47
Problem:● We want a way to define where everything will be located in the manufacturing lava
tube○ Floor space allocations for multiple processes○ Determine flow through plant○ Personnel requirements at each point
Considerations:● Flow of materials through the plant● Personnel requirements at each point
Steel Flow Path
THE PROBLEM
3/27/2018 48
● Large scale production closer to the door, reduces need to carry raw material far distances
● Separate tube by sections, allows room for expansion
○ Can help isolate sensitive processes (silicon growing, computer assembly) from large-scale industrial processes
SOLUTION
3/27/2018 49
Production Process Floor Space Required (m2)
Steel 120,000
Aluminum 20,000
Polyethylene 5,000
PVC 25,000
Sulfur Concrete 10,000
Glass 3,000
Ent
ranc
e/U
nloa
ding
Arc FurnacesPlastic Forming
Extrusions
Transportation Rail
Vehicle and Part Assembly Heat Ovens
Cement Casting
Pulling
Rolling
PV
C
Metal ProcessPlastic ProcessAssemblyCementTransportation
APPENDIX A: MATERIAL REQUIREMENTS
3/27/2018
Desired Material
Processes Power Required, kW
Personnel Requirements
Material Output, Mg/year
Steel Arc Furnace, Extrusion, Pulling, Rolling, Heat Ovens, Casting
1324.8 18 - Forming 9214.0
Aluminum Arc Furnace, Extrusion, Rolling, Heat Ovens
365.4 8 - Forming 238.0
Polyethylene Non-heated mixing, heat ovens
6.241 12 - Forming 93.0
PVC Polyethylene heating, casting
13 5 - everything 217.0
Concrete Arc Furnaces, Casting
1.808 8 - everything 517.5
*Values found by all members of the manufacturing team
APPENDIX B: Material Flow Paths
3/27/2018
Desired Material Required flow rate (Mg/year) [Thurston, Nazmy]
Process Power Required (kW-h) [1,2,3]
Work Required per Year (kW-h per annum)
Operating Power Required (kW)
AISI 4130 Steel 1085 715.10 77803.0 ---
Stainless Steel 316L 137 791.55 3332.4 ---
A36 Structural Steel 7992 748.23 2967981.5 ---
Sum of Metals 4120.25 --- 3078249.0 1324.8
Aluminum 6061-T6 238.0 718.14 29132.1 365.4
Sulfur Concrete 517.5 0.845 7920.47 1.808
[1] [NA], “Time Required to Melt 1000kg of Cast Iron Using A Induction Furnace”, Electronic Induction, http://www.electroheatinduction.com/time-required-to-melt-1000kg-of-cast-iron-using-a-induction-furnace/[2] [NA], “Rolling Aluminum: From the Mine to the Mill”, The Aluminum Association Third Edition, 2007,http://www.aluminum.org/sites/default/files/Rolling_Aluminum_From_The_Mine_Through_The_Mill.pdf[3] Wan, Li; Wendner, Roman; Cusatis, Gianluca, “A Novel Material For In Situ Construction on Mars: Experiments and Numerical Simulations”, Construction and Building Materials, https://arxiv.org/pdf/1512.05461v1.pdf
APPENDIX C: REFERENCES
3/27/2018
COMPUTER MANUFACTURING ON MARS
Riley ViverosMission DesignManufacturing
3/27/2018
3/27/2018 53
COMPUTER REQUIREMENTS
3/27/2018 54
• Problem• Many of our city’s systems needs computers to operate• Computers needed for automation, calculations, manufacturing, etc.
• Goal• Design computer chips to meet the computing needs for each vehicle and
system group and determine resource input and output
• Requirements• Computer chips must be manufacturable on Mars
• Assumptions• Design one Standard Computer (SC) that will be a generic model that can
perform various tasks based on individual system requirements• Our computers can use parallelization with more computer chips to increase
computing power
COMPUTER CHIP MANUFACTURING
3/27/2018 55
Vehicle/System Group # of Standard
Computers (SCs)
Space Transport 25
Ground Transport 840
Resource Extraction 690
Manufacturing 30
Science Support 700
Communications
Infrastructure
60
Food Production 20
City Infrastructure 2500
TOTAL 4865
• Computers will be 32 bit, 233 MHz with 350 nm transistor size. Defined as 1 Standard Computer
• Most feasible for humans to make by hand• Modern has 10 nm transistors, but those require
very precise measurements and machinery [1]• Each computer is approx. 5 kg and a 5 year lifespan
• Can vary based on specific system requirements• Each computer is almost entirely silicon and copper
with tiny amounts of Boron, Phosphorus, and Gold [1]• Silicon must be used in a pure form, chemical reaction
with Magnesium separates SiO2 into pure silicon [2]• Computers are made by hand in a clean room• 7521 kJ of energy and 32 m3 manufacturing area
• 783 Watts over 8 hour work day
Total number of SCs needed by each system (defined in Appendix)
Material Mass (Mg/year)
Silicon Dioxide 9.382
Copper 0.486
Magnesium 7.600
Gold/Boron/ Phosphorus
Negligible(~grams/year)
APPENDIX• 4865 computers replaced every 5 years.• 973 computers per year, 4.5 kg silicon/computer, 0.5 kg copper/computer• 4378.5 kg pure silicon/year, 486.5 kg copper/year
SiO2 + 2Mg –> Si + 2MgO
• Used molar masses to find required amount of Silicon Dioxide and Magnesium
• Used Specific heat to find energy (power) required
3/27/2018 56
MASS CALCULATION
3/27/2018 57
ENERGY CALCULATION
3/27/2018 58
NOTES ON COMPUTER MANUFACTURING FROM PROFESSOR GEORGE ADAMS
3/27/2018 59
SYSTEM COMPUTER NEEDS (BLAKENBERGER, DWYER, BLASKOVICH)
3/27/2018 60
• Space Transport• Requires16 SCs for the crew capsule, 3 for the launch vehicle and 6 for the lander.
• Ground Transport• Requires 4 SCs for communication, 8 SCs per crewed rail car, 8 SCs for each rover
• Resource Extraction• 10 SCs per mining truck, 5 SC per dragline excavator, 10 per processing facility
• Manufacturing• Requires 3 SCs per CNC station and estimate of 10 stations total
• Science Support• Will need 10 SCs per rover and there will be 70 rovers at all times
• Communication • Each satellite requires 5 SCs for control and communications for each of the 12 satellites
• Food Production• 20 SCs needed for timing and control of irrigation system
• City Infrastructure• 1 SC will be provided for every 4 people for general recreation, work, record keeping, etc.
REFERENCES
3/27/2018 61
• [1] Professor George Adams Interview. (2018).• [2] “Silicon dioxide react with magnesium,” SiO2 Mg = Mg2Si MgO |
Chemical reaction and equation Available: https://chemiday.com/en/reaction/3-1-0-7242.
• Heat, Work and Energy Available: https://www.engineeringtoolbox.com/heat-work-energy-d_292.html.
• 2.1 Silicon Dioxide Properties Available: http://www.iue.tuwien.ac.at/phd/filipovic/node26.html.
RAIL SYSTEM TRADE STUDY
Kyle TincupHuman Factors
Ground Transportation3/27/2018
3/27/2018 62
SYSTEM REQUIREMENTS AND ASSUMPTIONS
3/27/2018 63
System Requirements:● Transport necessary resources from
resource extraction sites● Transport maintenance crews to and
from resources extraction sites
Assumptions:● Steady-state problem● Track is already established● Resource location sites are independent
of ground transportation material needs● Rovers are capable of traversing
designated rail routes
CAD Drawing from Sean Thompson
64
RAIL SYSTEM JUSTIFICATION
Resource Efficiency:
● Rail = 168 Mg of Resources● Rover = 8.3 Mg of Resources● Would Require 20 times more rovers than resource rail cars (5546 total resource rovers)
Power:
● The rail system is approximately 4 times as power efficient as the rover based solely on the amount of wheel sinkage vs the coefficient of rolling resistance.
● Battery powered rovers would be incapable of transporting resources from thorium and copper extraction sites (Stephen Kubicki)
Communication:
● Each rover would require an additional 2 standard computers and a 0.3 m diameter satellite dish to communicate with MNET (Mitch Hoffman)
● The autonomous rovers would drastically increase every aspect of the communication infrastructure’s mass, power, and volume (Ryan Duong)
3/27/2018
RAIL SYSTEM JUSTIFICATION
3/27/2018 65
Power Requirements:
Plots generated from Stephen Kubicki’s Slope_Power Matlab code
66
RAIL SYSTEM JUSTIFICATION
System Rank Reasoning
Train 5 1.3 units weight of resources carried per unit weight of infrastructure
Rover 1 0.014 units weight of resources carried per unit weight of infrastructure
Hopper 2 0.4 units weight of resources carried per unit weight of infrastructure
Resources Efficiency Given Current Rover Design
Table from Ana Paula Pineda Bosque’s long distance transport trade study
3/27/2018
RESOURCE EXTRACTION INTEGRATION
Sean ThompsonCAD
Ground Transport3/27/2018
3/27/2018 67
PROBLEM
• How will our designs be used to extract resources?
Requirements:• One resource cart per day per site
• Resource Extraction• Maintenance carts six time per year
To Determine:• The interaction between the mining sites and
our carts3/27/2018 68
SOLUTION
69View of Mining Site in collaboration with Logan Kirsch and Anand Iyer
APPENDIX
3/27/2018 70
Second View of Mining Site
APPENDIX
Vehicle Material Mass [Mg] Power [kW] or Energy Capacity[kWh]
Volume [𝒎𝒎𝟑𝟑] or Surface Area [𝒎𝒎𝟐𝟐]
Personnel Rail Cart
Aluminum & Steel
13.01 147 45
ResourceRail Cart
Steel 22.11 (Empty)168.3 (Full)
127 114
Flatbed Rail Cart
Steel 28.67 127 40 (Surface Area)
Crewed Rover
Aluminum 3.71 41.6 (EnergyCapacity)
10.5
Tube Utility Vehicle
Aluminum 0.12 21.7 (Energy Capacity)
7 (Surface Area)
3/27/2018 71
Mass (Eric Thurston), Power (Stephen Kubicki), and Volume (Eric Thurston) of Each Vehicle
APPENDIX
Rail Part Length [m] Width [m] Height [m]Concrete Slab 6.5 2.62 0.1Concrete Substrate
6.5 2.92 0.15
3/27/2018 72
Length of Rail [km] Total Mass of Rails [Mg]13444 1.811*107
Vehicle Amount of Vehicles Personnel Rail Cart 10Resource Rail Cart 274Flatbed Rail Cart 35Crewed Rover 20Tube Utility Vehicle 50
APPENDIX
3/27/2018 73Steel Rail Dimensions
WATER SYSTEM DESIGN INTERACTIONS
Nicole FutchHuman Factors
Ground Transport/ Space Transport/ City Infrastructure3/27/18
3/27/2018 74
THE PROBLEM
How do the water systems and carrying vessels fit into the overall design?
Requirements• Reclaim at least 90% of all wastewater in the recyclers.• Provide potable water to all citizens and tourists.
Ground Transport:• Provide life support to a maximum of 3 people in the rovers.• Provide life support to a maximum of 4 people in the rail vehicles.
City Infrastructure:• Provide life support to 10,000 people in the city.
Space Transportation:• Provide life support for a maximum of 310 days• Provide life support to 50 people.
3/27/2018 75
Ground Transport:
- Supports maintenance and supervisory missions
- Requires manufacturing, resource extraction
THE SOLUTION
3/27/2018 76CAD images courtesy of Sean Thompson.
City Infrastructure:
- Has the potential to supply food production
- Interfaces with resource extraction
- Requires manufacturing
Space Transport:
- Has the potential to supply Sabatier reactions
- Interfaces with resource extraction
- Requires manufacturing
APPENDICES, CITYCity Water System, 1 system per module
77
Mass 1520 Mg
Power 5.06 MW
Volume 1840 m3
Computers 2
Specifications
City (per year)
Steel (Mg) (2%) 3.181
Polyethylene (Mg) (5%) 2.272
Activated Carbon (Mg) (1%)
2.272
Manufacturing
CAD images courtesy of Sean Thompson.
APPENDICES, SPACE TRANSPORTSpace Transport Water System
78
Mass 1520 Mg
Power 5.06 MW
Volume 1840 m3
Computers 2
Initial water (Mg) 3.87
Specifications
Cycler (per trip)
Steel (Mg) (2%) 0.111
Polyethylene (Mg) (5%) 0.013
Activated Carbon (Mg) (1%)
0.0013
Manufacturing
CAD images courtesy of Sean Thompson.
ADDITIONAL INFORMATION
Simplified recycling system schematic:
79
Image redrawn by Nicole Futch; based off of image by D. Layne Carter [1]3/27/2018 79
APPENDICES, CARBON SCRUBBING
80
Space Transport:
Frequency:Once per cycle
CO2 production:0.13 Mg
Energy Required:6.27 kW
City Infrastructure:
Frequency:3 months
CO2 production:152 Mg
Energy Required:8.82 MW
ADDITIONAL INFORMATION
Activated Carbon for water filtration; including revitalization process [4]
81Image drawn by Nicole Futch; based off of JTOP Co. design [3]3/27/2018
ADDITIONAL INFO, RECYCLER SIZING
This code takes historical data and interpolates appropriately sized water recyclers.
823/27/2018
ADDITIONAL INFO, CI RECYCLER SIZE
Sample output for recycler sizing for the city, which was calculated based on water that must be taken by the system per day.
833/27/2018
ADDITIONAL INFO, ST RECYCLER SIZE
Uses ‘people’ option of code on slide 8 since the system will be used in an environment that more closely resembles ISS.
843/27/2018
ADDITIONAL INFO, ST INITIAL WATER
This code computes the initial/ongoing water need for the recyclers that will be used in the city and on the cycler.
A sample output for the cycler is shown below.
3/27/2018 85
APPENDICES, GTGround Transport water and food, personnel rail vehicles
86CAD images courtesy of Sean Thompson.
Water tank Food bin
Mass (kg) 12
Power (kW) 0
Volume (m3) 0.0503
Mass (kg) 16.4
Power (kW) 0
Volume (m3) 0.2
APPENDICES, GT
87
Ground Transport water and food, rover vehicles
87CAD images courtesy of Sean Thompson.
Water tank Food bin
Mass (kg) 3.41
Power (kW) 0
Volume (m3) 0.0078
Mass (kg) 1.71
Power (kW) 0
Volume (m3) 0.0068
ADDITIONAL INFO, GT CARRY
This code computes how much food and water will need to be carried by a vehicle for its missions, and computes the amount and specs of material needed to make the containers.
Inputs: number of days, number of people, preferred height of tank.
3/27/2018 88
ADDITIONAL INFO, GT FOOD/WATER CARRY
Water and food carrying code continued.
3/27/2018 89
ADDITIONAL INFO, GT CARRY
Water carrying code end.
Sample output for 4 person train traveling for 5 days with tank height of 0.4 m:
3/27/2018 90
SOURCESSources
[1] Carter, D. L. “Status of the Regenerative ECLSS Water Recovery System” NASA Technical Reports Server. 23 Jan 2009.R Rept. 2009-01-2352. https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20090033097.pdf
[2] “Environmental Control and Life Support System”, NASA G-281237, 23 Aug 2017. https://www.nasa.gov/sites/default/files/atoms/files/g-281237_eclss_0.pdf
[3] “Water Recycle Treatment System”, JTOP Co., Ltd, 2015. Osaka, Japan. Accessed 4 Mar 2018,
http://www.kankeiren.or.jp/kankyou/en/pdf/en026.pdf
[4] Special thanks to Mr. D. Layne Carter of NASA Marshall Space Flight Center.
913/27/2018
REMOTE COMMUNICATION SYSTEM OVERVIEW
Mitch HoffmannCommunication and Control
Ground TransportationCity Infrastructure
3/6/2018
3/27/2018 92
REMOTE COMMUNICATION SYSTEM: MITCH HOFFMANN
Needs/Requirements
• Transmit 6 continuous HD video and controls feeds to each resource site for teleoperation. 60 Mbps
• Relay all data from ground station to users within the city. 53 Mbps
• Enable communication between ground vehicles to facilitate switching and timing of rail cars
Assumptions
• Fiber optic signal is usable up to 13 km without repeaters. [1]
• Comms antennas on rovers and railcars are 2 m high
• Maintenance vehicles are located a maximum of 2 km perpendicular distance from the tracks.
3/27/2018 93
The Problem: Sharing Information between the city, outposts, and ground transportation vehicles.
Image Credit: Pau Pineda (both)
REMOTE COMMUNICATION SYSTEM:MITCH HOFFMANN
• A trunk of optical fiber runs the entire length of the train routes
• At each site along the route, a branch point (yellow) muxes and demuxes data for the site from the trunk
• Stationary access points interface with end users (maroon)
• Power for repeaters is drawn from the rail power supply
• Remote Communication Outlets collocated with repeaters (orange) broadcast radio signals to nearby vehicles
• Power requirements: 94.8 kW Nominal263.9 kW Peak
3/27/2018 94
The Solution: Hybrid optical and radio communication system connecting remote outposts.
User Max Data Requirement [Mbps]
System Maximum[Mbps]
Req. Met
Remote sites 360 1000 Yes
Ground Station 53 1000 Yes
STATIONARY ACCESS POINTS
3/27/2018 95
RCOS
3/27/2018 96
BRANCH POINTS
3/27/2018 97
REFERENCES[1] A. Services, “Fiber Optic Systems Technical Overview Student Guide.” Ameritech Services, 1999.
3/27/2018 98
MARTIAN ATMOSPHERIC PROCESSING SYSTEM
Diego A. MartinezPropulsion
Resource Extraction03/26/2018
03/26/2018 99
THE PROBLEM
• Objective: To provide various gases to all vehicle and systems group with minimal waste products, prioritizing low power solutions
03/26/2018 100
ResourceDaily
Requirement (Mg)
Oxygen 1.82Nitrogen 0.227
Carbon Dioxide 5.82Argon 0.063
Methane 2.79*Fractional Distillation CAD provided by Adit Khajuria
THE SOLUTION
03/26/2018 101
Notes About System• Large amount of
excess oxygen and small amount of nitrogen for reserves and terraforming
• Nitrogen: 0.11 Mg/day
• Oxgyen: 28 Mg/day• With safety factor for
production, we store gases to supply needs for 30 days
• New power requirement includes storage of extra gasSystem Sizing
Mass 3700 MgPower 25 MWVolume 5000 cubic meters
REQUIREMENTS VS PRODUCTION
3/27/2018 102
ResourceDaily
Requirement (Mg)
Daily Production (Mg)
RequirementSatisfied?
Oxygen 1.82 30.956 Yes
Nitrogen 0.227 0.34 Yes
Carbon Dioxide 5.82 5.82 Yes
Argon 0.063 0.34 Yes
Methane 2.79 3.45 Yes
Note: Points of Contact for requirements provided on following appendix slide
REQUIREMENT BREAKDOWN
3/27/2018 103
V&S Group Use Resource Daily Need (Mg) Yearly Need (Mg)
City
Tube Pressurization Oxygen 0.097 35.6Tube Pressurization Nitrogen 0.227 83.0Drinking, Aeroponics, Bathing, and all other water city water needs
Water 160 58400
Food Production Aeroponics Carbon Dioxide 5.82 2120
Propulsion
Space TransportMethane 0.453 165Oxygen 1.72 629
Space Transport Argon 0.063 23.17Communications Methalox 0.002 0.804
CommunicationsMethane 0.003 0.951LOX 0.010 3.62
Communications Argon 7.68e-5 0.028
Science SupportDeimos
Methane 1.43e-4 0.052Oxygen 5.43e-4 0.1983
PhobosMethane 9.32e-5 0.034Oxygen 3.54e-4 0.129
ManufacturingPolyethylene, PVC production Methane 1.91 698
Resource Copper Production Carbon Monoxide 8.03 2930
RISK IDENTIFICAATION
• Compressor System
3/27/2018 104
Compressor Failure
Power transmission failure Mechanical failure
Lubricant failure, FOD
contamination, unregulated
thermal environment,
crack propagation
Faulty cabling, electrical shorting,
arcing
OR
APPENDIX – MAPS CODE
03/26/2018 105
APPENDIX – MAPS CODE
03/26/2018 106
APPENDIX – MAPS CODE RESULTS
3/27/2018 107
APPENDIX – MAPS CODE RESULTS
03/26/2018 108
CRUSHING FACILITY INTEGRATION
Adit KhajuriaCAD
Resource ExtractionMarch 27, 2018
3/27/2018 109
PROBLEM• Problem:
• Illustration of the integrated Crushing Facility• Updated drag-line excavator• Full crushing facility visual
• Integration with Ground transport
3/27/2018 110
SOLUTION
111
• Rests on lip of crater and uses boom and bucket to collect minerals from craters
• Gathers regolith and sends to haul truck• Haul truck transports regolith to crushing
facility• Crushing facility crushes regolith and
sends it up along conveyor belt• Electromagnet picks up meteorites• Crushed regolith is put into railcars for
transport to city
BACKUP - DRAGLINE EXCAVATOR
• Bucket volume of 5 m3
• Bucket is dragged along crater by cables, which are hoisted by the boom
• Boom extends 100m
BACKUP - DRAGLINE EXCAVATOR
1.7m 1.7m
1.7m
• Excavator moves on “stands”• Grips on bottom help with traction and
maneuverability along lip of crater
BACKUP - DRAGLINE EXCAVATOR
COMPLETE MINING SYSTEM OVERVIEW
Will ChlopanPower and ThermalResource Extraction
3/26/2018
1153/27/2018
THE PROBLEM
• How do we bring metal rich Martian rock to the city?
• System Requirements• No on site crew required• Can load 100 m3 of rock into railcars• Maintenance can be performed in 2 days or less• No risk to city with daily operations• Many resource requirements
• How does the mine connect to the city?
1163/27/2018
MINING OVERVIEW
117
System Specifications Per Mine
Power 3.0 MW
Mass 93 Mg
Volume 110 m3
3/27/2018
CAD by Adit Khajuria, and Anand Iyer
20 magnetic vehicles search for asteroids with rare materials
HAUL TRUCK
1183/27/2018
• 80 s cycle for dragline excavator • 2.260 m3 per cycle
• 20 s cycle for intermediate excavator• 0.300 m3 per cycle
Analysis by Islam Nazmy
DRAGLINE EXCAVATOR
3/27/2018 119
Bucket Size (m3
) Boom Length (m) Track Width (m) Cycle Period (s)
Dimension 2.260 100 2 80s
• Removes rock from impact craters• 1 per mine
CAD by Adit Khajuria
INTERMEDIATE EXCAVATOR
Bucket Size (m3
) Boom Length (m) Track Width (m) Cycle Period (s)
Dimension 0.300 3.0 0.5 20
3/27/2018 120
CAD by Anand Iyer
• Dragline excavator can not safely load haul trucks
• Intermediate excavator moves rock from pile made by dragline excavator into haul trucks
HAUL TRUCK
3/27/2018 121
Bed Width (m) Bed Height (m) Bed Length (m) Bed Volume (m3
)
Dimension 2 1.8 4 6
CAD by Adit Khajuria, and Anand Iyer
• Moves rock from excavators to crusher
• 3 per mine• Drives on haul road to recharge
batteries to and from excavator site• 9.635 kWh lead acid battery
- + -
- + -
- + -
CAD by Adit Khajuria
CRUSHER
1223/27/2018
• Processes 6 m3 from 1 haul truck in 1 min 28 s• Loads 100 m3 railcar in 3 hrs 11 min• Requires 450 kW to operate• 1 per mine• Loads rock into railcar
Analysis by Will Adams
RARE RESOURCE CART
3/27/2018 123
CAD by Adit Khajuria, and Anand Iyer
Vehicle RequirementsMass (Mg) 400E4Battery Capacity (MWhr)
14.24
Volume (m3
) 1000
• Searches for meteorites on the surface of Mars
• 20 vehicles operating simultaneously
• 5.607E5 Mg of meteorites per year
• Sweeps 1.023E3 km2 per day (total)
Analysis by Islam Nazmy
OVERVIEW OF RESOURCE EXTRACTION LOCATIONS
Megan HarwellScience
Resource ExtractionMarch 27, 2018
1243/27/2018
PROBLEMHow do the chosen resource extraction fulfill the needs of the city?• Fundamental needs:
• At minimum, must yield enough to sustain population• Minimize distances as much as possible• Must have extractable source and large pool of resources
• Assumptions:• Surface abundance is projected through regolith layers• All minerals are extractable in their current form
3/6/2018 125
Mineral Required by Needed(Mg/yr) Required to produce
SiO2City, transport, Food, SC
38.85 Glass production,
Al2O3City, s transport, ground, SC, food
350.18 Aluminum sheets, components used in manufacturing
FeO City, Manufacturing, ground transport, food
12694.40 Steal production, nutrition
Th City 2313.52 Reactor fuel
NO3, NO4food 31.62 Food production, growing plants
Mo Food, manufacturing 0.66 Steal production, alloy production, human nutrition
RESOURCE EXTRACTION SITES
Mineral Required by Needed(Mg/yr) Yield (Mg/yr) Source
SiO2City, transport, Food, SC
38.85 183200 Each extraction site
Al2O3City, s transport, ground, SC, food
350.18 29140 Each extraction site
FeO City, Manufacturing, ground transport, food
12694.40 73730 Each, abundance at Gale, Reull
Th City 2313.52 844400 Each, abundance at Shalbatana
NO3, NO4food 31.62 126.7 Gale Crater
Mo Food, manufacturing 0.66 4.087 Iron meteorites, trace at Gale
Thorium: 0.71 weight percent
Copper Oxide: 15 weight percent
Nitrates: 0.11 weight percent
MiridianiPlanum
Reull Vallis
Gale Crater
ShalbatanaValliis
APPENDIX: WHY THESE LOCATIONS
3/27/2018 127
Gale Crater: The specific layers under Gale are not reproduced in any crater closer to home base, nor are the lake sediments, according to this USGS map 3292 via JMARS.
The ephemeral lake theory includes that Gale may have been filled when the water table was higher than the depth of the crater, which would imply that its relationship with the northern plains ocean is an important factor in the minerology of the gale sediments.
Kinkora crater, at 112.88 E, -24.91 N was checked, but did not show the same geology as Gale. Yes, there was water alteration, but different drainage.
Gale Crater
3/27/2018 128
Shalbatana Vallis: Th eonly region shown to have
spectral signatures of copper so far. If the valley was formed from water running from Orson Welles Crater into the northern panes, then we should try to find a crater unit on a similar bedrock, also affected by water alteration.
Search for a valley with a similar geologic setup has been inconclusive. The guess was drainage from impact crater with lake sediments at bottom into lower altitude area, from the Hesparien to Naochian crust.
SOURCES[1] Yen, A., et al. 2005. “An integrated view of the chemistry and mineralogy of martian soils.” Nature. 435. pp. 49-54.[2] Klingelhofer, G. et al. 2004. "Jarosite and Hematite at Meridiani Planum from Opportunity’s Mossbauer Spectrometer". Science. Vol. 306. pp. 1740-1745.[3] Rieder, R., et al. 2004. "Chemistry of Rocks and Soils at Meridiani Planum from the Alpha Particle X-ray Spectrometer". Science. Vol. 306. pp. 1746-1749[4] Popa, C., et al. "Evidences for Copper bearing minerals in Shalbatana Valley, Mars," 45th Lunar and Planetary Science Conference. 2014. Abstract #2340. [5] http://onlinelibrary.wiley.com/doi/10.1029/2005JE002501/full[6] Thompson, A., “Buried Glaciers Found on Mars,” Space.comAvailable: https://www.space.com/6137-buried-glaciers-mars.htm.[7] Wetherill, G.W., “Isotopic Composition and concentration of Molybdenum in iron meterorites,” Journal of Geophysical Research, vol. 69, 20, 1964, pp. 4403-4408[8]”Poulet, F., Bibring, J.P., Mustard, J.F., Gendrin, A., Mangold, N., Langevin, Y., Arvidson, R.E., Gondet, B., The OMEGA Team. “Phyllosilicates on Mars and implications for early martian climate,” Nature, vol. 438, 2006, pp. 623-627.[9]Poulet, F., Mangold, N., Loizeau, D., Bibring, J.P., Langevin, Y, Michalski, J., Gondet, B., “Abundances of minerals in the phyllosilicate-rich units on Mars,” Astronomy & Astrophysics, Vol. 487, 2008, L41-L44[10]Carter, J., Poulet, F., Bibring, J.-P., Mangold, N., and Murchie, S., “Hydrous minerals on Mars as seen by the CRISM and OMEGA imaging spectrometers: Updated global view,” Journal of Geophysical Research: Planets, vol. 118, Apr. 2013, pp. 831–858.
3/27/2018 129
OVERVIEW OF THE CYCLER’S DESIGN
John ClevelandMission Design
Space Transportation3/27/18
3/27/18 130
THE PROBLEM: CREATING A SAFE AND EFFECTIVE CYCLER DESIGN
Cycler Design Requirements:1. Crew/passenger living area must rotate* to provide
artificial gravity2. Docking ports must not rotate* to improve docking
accuracy and safety3. Communications equipment must not rotate* to
ensure pointing accuracy4. Central column must be crew-accessible for
maintenance and storage5. Connected, pressurized sections must rotate* at the
same rate to increase lifetime of atmospheric seals*Note: Rotation with respect to an inertial reference frame
3/27/2018 131
THE SOLUTION: DOCKING AND UTILITY MODULES
• Cycler ring and central column are contiguous and always rotating
• Two non-rotating utility modules are positioned at each end of the central column
• Communications equipment and docking ports are mounted on utility modules
Images by Anand Iyer3/27/2018 132
APPENDIX: DOCKING PROCEDUREInitial state: Taxi inbound, docking port empty and non-rotating1. Taxi approaches and docks2. Utility module and taxi spin up to match cycler rotation
using reaction control thrusters3. Utility module seals with the cycler4. Passengers and crew disembark the taxi and enter the
cycler 5. Taxi depressurizes and utility module disengages seals
with the main body6. Utility module spins back down with taxi using reaction
control thrustersFinal state: Taxi docked, taxi and utility module non-rotatingCommunications during the procedure are handled by the other non-rotating utility module
3/27/2018 133
APPENDIX: OTHER DESIGNS CONSIDERED
Entire cycler rotatingFailed requirements 2 and 3
Main ring rotating, central column non-rotatingFailed requirement 5
Main ring rotating, central column non-rotating and depressurized
Failed requirement 4Ring and central column rotating, communications equipment mounted on non-rotating slip ring
Failed requirement 2
3/27/2018 134
COMMON LAUNCH VEHICLE
Andrew BlaskovichMission Design
Space Transportation3/27/2018
3/27/2018 135
PROBLEMSet of launch vehicles previously designed:• Optimized for individual performance
• 3 separate vehicles
• No common parts
Realistically these can be combined into one vehicle by altering the propellant load• This would be less efficient, but reduces manufacturing
and operational complexity
3/27/2018 136
Left to Right: Mnet launcher, Relay launcher, MEHDL Launcher (CAD
by Andrew Blaskovich)
SOLUTION
Use a common launch vehicle architecture• Designed based on the capability of putting 3 MEHDL satellites into
areostationary orbit• Vary the propellant loading for the specific mission
3/27/2018 137
71%
100%
100%
64.2%
100%
Common Upper Stage
Common Lower Stage
Common Fairing
Legend
Mnet Launcher
MEHDL-H Launcher
MEHDL-A Launcher
Common Launch Vehicle Architecture (CAD by Andrew Blaskovich)
TANK SIZING
• Tanks were assumed to be either spherical or capsule shaped
3/27/2018 138
Radius (m) Height (m)Lower Stage
Methane 3.30 -LOX 3.34 4.16
Upper Stage
Methane 1.73 -LOX 1.95 -
Tank Sizes
MethaneLOX
Cross Section View
LAUNCH VEHICLE CAPABILITIES
• The full stack can lift at least 6 Mg to low Mars Orbit at an inclination of 36.8°
• The upper stage alone can lift 0.7 Mg to low Mars orbit at an inclination of 36.8°
3/27/2018 139
Common Fairing Design. The length L can be chosen for the desired
payload
POWER FOR THE VEHICLE ASSEMBLY BUILDING
Faiz FerozPower & Thermal
Space TransportationMarch 27, 2018
3/27/2018 140
PROBLEMBig Picture: The Vehicle Assembly Building (VAB) is where all our launch systems are to be built and readied for launch
Problem: quantifying the power requirement and how to provide said power requirement for assembly tools and life support
Knowns:
• The VAB is located 10 km from the city
• The surface area exposed to Mars’ surface environment is 8400 m2
• The structure of the VAB is concrete with a 0.5 m thickness (Jacob Roe)
• A recycling system is not necessary as food and water are transported to the VAB, and waste is sent out
• Propellants need to be stored and regulated in the building
3/27/2018 141
Image by Anand I. and Sean T.
SOLUTION
Temperatures:• Ambient temperature: 218 K• Desired temperature: 293 KFor these temperature regulation at these values, the VAB requires 756 kW
Other power considerations:• Oxygen and Pressurization• Crane and Tools• Crawler Vehicle• Propellant Storage• Lighting
3/27/2018 142
Credit System Power [kW]
Me Temperature 756
TopherPowered Tools/Crane 5080
Propellant Storage 219
Tyler D. Crawler 1530
Matty P. Lighting 36.3
Andrew Ph. Oxygen/Pressurization 8.67
TOTAL: 7630
With the proximity of the VAB and the magnitude for the power requirement being 7.63 MW, the VAB will draw power from the city grid like the other resource sites with Jonathon Bensman’s power line design
APPENDIX
�̇�𝑞 =Δ𝑇𝑇𝑅𝑅 ∗ 𝐴𝐴
Δ𝑇𝑇 = |218 K – 293 K|
3/27/2018 143
Mars Atmosphere
VAB Room
Concrete Wall0.5 m
APPENDIX
A = 8400 m2
𝑅𝑅 =𝐿𝐿
𝑘𝑘𝑐𝑐𝑐𝑐𝑐𝑐𝑐𝑐𝑐𝑐𝑐𝑐𝑐𝑐𝑐𝑐 ∗ 𝐴𝐴
Thickness: L = 0.5 m
kconcrete = 0.6
𝑃𝑃 = ̇𝑞𝑞 ∗ 𝐴𝐴
3/27/2018 144
APPENDIXOverall Final Power Design for Space Transportation Vehicles
3/27/2018 145
QuantityMass
[Mg]
Power
[kW]
Volume
[m3]
7 8.4 700 1.25e-2
QuantityMass
[Mg]
Power
[kW]
Volume
[m3]
20 0.6 5 0.25
Credit SystemPower
[kW]
Me Temperature 756
TopherPowered Tools/Crane 5080
Propellant Storage 219
Tyler D. Crawler 1530
Matty P. Lighting 36.3
Andrew
Ph.Oxygen/Pressurization 8.67
TOTAL: 7630
Cycler: 7 Safe and Affordable Fission Engines (SAFE-400) each producing 100 kW of power meet 700 kW for a system requiring 515 kW
Taxi Vehicles: Twenty 12 V lead acid batteries each rated at 125 Ah to meet more than our taxi requirement of 4 kW
VAB: Power is drawn directly from the city to meet the 7.63 MW power
requirement
SOURCES
Z. S. Spakovszky, “16.4 Thermal Resistance Circuits,” Thermodynamics and Propulsion. [Online]. Available: http://web.mit.edu/16.unified/www/FALL/thermodynamics/notes/node118.html.
3/27/2018 146
DESIGN SUMMARY: CYCLER COMMUNICATIONS
Noah GordonCommunications & Control
Space Transportation3/27/2018
3/27/2018 147
THE PROBLEMProblem: • How do we communicate with the cycler while it is in transit?Requirements: • Maintain continuous two-way HD video communications with the cycler at all
times• The city shall be a joy to live in
148
CAD of cycler by Anand Iyer
3/27/2018
Assumptions:• We are able to perform routine maintenance on
the cycler• Limited data rate during solar conjunction of all
cyclers is acceptable• Solar conjunction occurs when a signal passes
within three degrees of the Sun [1]Ground Rules:• We place burdens of manufacturing on Earth
wherever possible• We prioritize high data rates for quality of life
THE SOLUTION• The cycler is part of the Mars-Earth High Data Link (MEHDL) system• The cycler is equipped with 25-m-diameter antennae, allowing Martian satellites to
have smaller antennae diameters and power requirements• We choose to route all communications between Mars and Earth through the
cycler’s large antennae to drastically reduce the strain on Martian manufacturing• We base link budget analysis on a standard data rate of 42 Mbps (Sam Albert)• When solar conjunction renders both cyclers unusable as relays (for 8.85 days
every 15 years per Eliot Toumey), curtail rate to 10 Mbps and use relay satellite• Relay satellite is in heliocentric orbit of Mars’ size, out of phase by eight degrees
149
Satellite Power (kW) Antennae Diameters (m)
Solar Panel Area (m2)
Dry Mass (Mg)
Cycler 8 2x25 - -Mars Terminal 7 0.5, (2x0.5), 5 123.2 1.78
Relay 6.5 3, 7 108.4 1.54Earth Terminal 5.3 0.5, 10 99.5 1.02
Summary of relevant numbers for MEHDLCollaborated with Alex Blankenberger on link budget analysis3/27/2018
APPENDIX: PREVIOUS ITERATION WITHOUT COMMS THROUGH CYCLER
3/27/2018 150
Previous Iteration
Satellite Power (kW) Antennae Diameters (m)
Solar Panel Area (m2)
Dry Mass (Mg)
Cycler 3.5 2x25 - -
Mars Terminal 14.5 0.5, (2x0.5), 3, 10 236.8 3.07
Relay 16.3 2, 3, 10 247.5 3.01
Earth Terminal 11 0.5, 10 187.7 2.61
Note reduction in antenna size on Mars Terminal and Relay, elimination of an antenna on Mars Terminal and Relay, and the roughly halving of power and mass requirements on satellites.
APPENDIX: RELAY SATELLITE ORBIT
3/27/2018 151
APPENDIX: RELAY SATELLITE
3/27/2018 152
Cad by Sam Zemlicka-Retzlaff
APPENDIX: LINK BUDGET ANALYSISEARTH TERMINAL<-> CYCLER
153
Link Budget Analysis spreadsheet from SMAD [2]
3/27/2018
APPENDIX: LINK BUDGET ANALYSISMARS TERMINAL<-> CYCLER
1543/27/2018
APPENDIX: LINK BUDGET ANALYSISRELAY <-> EARTH TERMINAL
155
(Using reduced data rate for relay satellite links)
3/27/2018
APPENDIX: LINK BUDGET ANALYSIS RELAY<->MARS TERMINAL
1563/27/2018
APPENDIX - REFERENCES1 GANGALE, T., “MarsSat: Assured
Communication with Mars,” Annals of the New York Academy of Sciences, vol. 1065, Dec. 2005, pp. 296–310.
2 Wertz, J. R., Everett, D. F., and Puschell, J. J., eds., Space Mission Engineering: The New SMAD, Hawthorne, CA: Microcosm Press, 2011.
1573/27/2018
MARS SCIENCE ROVER
Jonathan BensmanPower and Thermal Management
Science Support03/27/2018
158
PROBLEM: FINDING POWER REQUIREMENTS FOR THE SCIENCE ROVER
Requirements (Set by Science team) :• Max speed of 30 km/hr• Operates for 8 hours a day• 20° max slopeAssumptions:• Will take 12 hours to recharge batteryNeed to determine:• Mass of power system
• Power required by rover
• Volume of power system
159
From Logan Kirsch
SOLUTION: USING SOLAR PANELS TO PROVIDED NEEDED POWER
160
Battery and solar panel size and weight found using Stephen Kubicki’s code and resources
System Power Required [kW]
Motors 30.7
Drill 17.3
Camera [1] 0.003
Communication Antennas
0.1
Spectrometer 0.02
Total 48.12
Max power required for each system on the science rover:
A 50 kWh battery and solar panels that provide 1.5 kW of power are used to power the rovers.
There will be 70 active science rovers at a time, below is the replenishment rates for the power system of these rovers:
Resource Rates [Mg/yr]
Silicon 0.119
Steel 0.463
Water and Sulfuric
Acid
0.206
Lead 0.825Power for communication is set by the communication group.
APPENDIX I. ROVER DRILL [2]
161
From Logan Kirsch
The torque required for the drill was estimated to be similar to Earth’s soil, which is about 230.5 N-m. A rotations per minute (RPM) rate was set to 75.
𝑃𝑃𝑑𝑑𝑐𝑐𝑑𝑑𝑑𝑑𝑑𝑑 = 𝑇𝑇𝑅𝑅𝑃𝑃𝑇𝑇
𝑃𝑃𝑑𝑑𝑐𝑐𝑑𝑑𝑑𝑑𝑑𝑑 = 17.3 𝑘𝑘𝑘𝑘
APPENDIX II: ROVER MOTORS [3]Max power is the sum of the power required to accelerate to 35 km/hr, the power required to sustain the rover at 35 km/hr, and the power required for the rover to climb a 20° slope at a constant speed.
162
𝑃𝑃𝑎𝑎𝑐𝑐𝑐𝑐 = 𝑚𝑚𝑚𝑚𝑚𝑚
𝑃𝑃𝑠𝑠𝑠𝑠𝑠𝑠𝑐𝑐𝑎𝑎𝑑𝑑𝑐𝑐 =𝜇𝜇𝐹𝐹𝑁𝑁𝑑𝑑𝑡𝑡
𝑃𝑃𝑠𝑠𝑑𝑑𝑐𝑐𝑠𝑠𝑐𝑐 = 𝑤𝑤𝑤𝑤𝑤𝑤𝑤𝑤𝑤𝑤(𝜃𝜃)
𝑃𝑃𝑎𝑎𝑐𝑐𝑐𝑐 = 10 𝑘𝑘𝑘𝑘
𝑃𝑃𝑠𝑠𝑠𝑠𝑠𝑠𝑐𝑐𝑎𝑎𝑑𝑑𝑐𝑐 = 5.2 𝑘𝑘𝑘𝑘
𝑃𝑃𝑠𝑠𝑑𝑑𝑐𝑐𝑠𝑠𝑐𝑐 = 15.5 𝑘𝑘𝑘𝑘
For the calculations, the acceleration was set to 1 km/hr2, the friction coefficient was assumed to be sand at 0.56, and the normal force and weight of the rover was found using the Martian gravity of 3.711 m/s2.
APPENDIX II: CONT.
163
This chart shows the relation between the velocity of the rover and the angle of the slope. There is an asymptote at 0,0 on this chart.
From Jonathan Bensman
APPENDIX III. REFERENCES
164
1. [N/A], “GoPro Rechargeable Battery”, Amazon, https://www.amazon.com/GoPro-Rechargeable-Battery-Official-Accessory/dp/B00I01JQJM
2. [NA], “Hydraulic Earth Drills”, Little Beaver, http://www.littlebeaver.com/products/hydraulic-earth-drills/
3. “Power Needed to Climb Constant Slope at Constant Speed,” 2011. [Online]. Available: https://www.physicsforums.com/threads/power-needed-to-climb-constant-slope-at-constant-speed.558552/ .
MARS ASTRONOMICAL OBSERVATORY
Alaina GliddenDiscipline: Science
System: Science SupportMarch 26, 2018
3/26/18 165
THE PROBLEM
3/27/2018 166
Considerations-Exploit the lack of ozone layer on Mars: ground –based X-ray and UV telescopes-UV telescopes in theory are the same as visible and IR telescopes: make one 40 m optical telescopeRequirements-X-ray: Made of tubes of parabolic and hyperbolic glass coated with Iridium.-Optical: Made of segmented hexagonal mirrors coated with Iridium.-Glass material must have a low coefficient of thermal expansion such as ZerodurTM (0 ±0.100 𝑠𝑠𝑠𝑠𝑝𝑝
𝐾𝐾) [3].
Assumptions-X-ray: Reduce the fraction of mirror surface covered by a 100 µm dust particle by an order of magnitude. (Appendix A)-Optical: 0.04 arcsecond spatial resolution to image the objects out redshift (z) of ~10.
Top: x-ray telescope, bottom: optical telescope (CAD by Logan Kirsch).
THE SOLUTION
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Telescope Mass Power (Ap.B)
Diameter Length/Depth
Operating Range
X-ray 10.42 Mg
12.3 kW
3.8 m 5.2 m 100-10,000 eV [1]
Optical(121 Hexagonal mirrors)
161.44 Mg
1210 kW
40 m 34.5 m 0.51-9.54 eV
Optical and Dome
5821 Mg
2770 kW
90 m 65 m N/A
Structure for Optical Telescope (CAD by Logan Kirsch)
-The x-ray telescope will sit inside of the dome structure while not in use.-Structure will have doors on either side and rail so the telescope can be moved outside.-Both will be cleaned daily while one hexagonal mirror will be removed to be polished.-53 workers total [Michael Rose]
Comprehensive MPV in Appendix B
APPENDIX A: FRACTION OF MIRROR SURFACE CALCULATION
Fraction of the telescope mirror surface covered by a particle of radius “a” is given by equation (1) [2].
𝐹𝐹𝑐𝑐 = 𝜋𝜋𝑎𝑎2
2𝜋𝜋𝜋𝜋𝜋𝜋(1)
R = radius of the mirror tubeL = length of the tubeFor a 100 µm dust particle (threshold diameter of a dust particle suspended in a Martian wind storm [5]), 𝐹𝐹𝑐𝑐 of the Chandra X-Ray Observatory telescope is approximately 1 × 10−8. Decreasing this fraction to 1 × 10−9 and maintaining the 𝑅𝑅/𝐿𝐿 ratio of the Chandra X-Ray Observatory, the outer radius and length of our telescope are 1.9 m and 2.6 m respectively.
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APPENDIX B: MPV SUMMARY
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Componenet Mass (Mg) Power (kW) Volume (m3) Lifetime (yr)X-ray Telescope
10.42 12.3 4.12 30 (Zerodur)
X-ray Mount 31.3 7.4 4 30X-ray Total 41.72 19.7 8.12 N/AOptical Telescope
161.44 730 (day)1,210 (obs.)
63.81 30 (Zerodur)
Optical Mount 3,080 1,660 (day)1,620 (obs.)
385 30
Optical Structure
5,821 930 (day)410 (obs.)
316,600 100
Optical Total 9,062.44 2,770 (max) 317,048.81 N/AObservation Operation Total
9,104.16 2,789.7 317,056.93 N/A
See Appendix C for more comprehensive Power breakdown.
APPENDIX C: TELESCOPE POWER
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Optical
Telescope
X-Ray
Telescope
Dome maximum demand [kW] 2770 N/A
Dome normal demand during the day [kW] 930 N/A
Dome normal demand during observation [kW] 410 N/A
Telescope normal demand during the day [kW] 730 7.4
Telescope normal demand during observation [kW] 1210 12.3
Normal demand during the day for dome and telescope [kW] 1660 N/A
Normal demand during observation for dome and telescope [kW]1620 N/A
Work Done by Annie Ping
APPENDIX D: OPTICAL TELESCOPE STRUCTURE
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Dimensions
Work done by Trevor Waldman
APPENDIX D: STRESS AND DISPLACEMENT
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Mises Stress Displacement
APPENDIX C: WHAT COULD WE STUDY?-Supernova Remnants: Shell of shocked material, temperature, composition [4] (Fig. 1 Crab Nebula X-Ray core, Chandra)
-Active Stellar Caronae: Magnetic loops, Solar flares, Finding Non-Eclipsing Systems (Fig. 2 Sun Magnetic Field Lines and Solar Prominances, ISAS)
-Young and Binary Stars: O type stars, Stellar Wind, Stellar Formation. (Fig. 3 v1647 Orionis X-Ray ejection plumes, Chandra)
-Galaxies: Galactic Nuclei, Galaxy Clusters, Dark Matter (Fig. 4 Perseus Cluster Shows insights into Dark Matter, Chandra)
-Black Holes: High Energy Neutrinos, Cosmic Rays (Fig. 5 Sagittarius A Supermassive Black Hole at the center of the Milkyway Galaxy, Chandra)
-Planets and Small Bodies: Reflections of Planetary/Cometary Atmosphere, Aurora from Magnetic Fields (Fig. 5 Jupiter Polar Auroras, Chandra)
Photos from [7] and [8]3/27/2018 173
c. v1647 orionis
a. Crab Nebula b. Sun
d. Perseus Cluster
f. Jupitere. Sagittarius A
REFERENCES
3/27/2018 174
[1] Array, S., “Chandra Specifications,” pp. 2–3.[2] Aschenbach, B., “X-ray telescopes,” Reports on Progress in Physics, vol. 48, 1985, pp. 579–629.[3] Schott, “Thermal expansion of ZERODUR,” 2006.[4] Charles, P. A., and Seward, F. D., Exploring The X-ray Universe, New York, NY: Cambridge University
Press, 1995.[5] Cheng, J., The Principles of Astronomical Telescope Design, vol. 360. 2009.[6] McPherson, A. “E-ELT Opportunities.”[7] Melosh, H. J., Planetary Surface Processes, Cambridge: Cambridge Univ. Press, 2011.[8] Williams, D. R., “Mars Fact Sheet,: NASA Available:
https://nssdc.gsfc.nasa.gov/planetary/factsheet/marsfact.html[9] Chandra :: Photo Album Available: http://Chandra.Harvard.edu/photo/[10] Agency, J. A, E., “ISAS: Solar Corona – Seeking the Source of its Activity and Heating/The Forefront
of Space Science.” Japanese Available: http://www.isas.ac.jp/e/forefront/2005/shimizu.index.shtml
ROVER TIRE SLIP
Logan KirschCAD
Science Support3/27/2018
3/27/2018 175
PROBLEM• Context:
• Rovers needed for far-reaching science missions
• Rover design includes a rocker-bogie suspension and Nitinoltires
• Requirements:• Wheels must not slip when rover
is scaling inclines• Rover needs to maintain speeds
of 20 km/hr to gather samples at sufficient speeds (Science)
• Assumptions:• The coefficient of kinetic friction
for the science rovers is equal to that of the NASA Curiosity rover
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Science Rover CAD model
SOLUTION
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• Tire Slip• Use friction angle found by
the Curiosity rover of 30°[1]
• Compare tangential and friction force acting on the rover while on an incline
• Rocker-Bogie• Current systems only
move around 0.21 km/hr• By implementing an
improved control system, the rover can safely travel at speeds over 20 km/hr. [2]
• Conclusion:• Tires will not slip• Rocker-bogie will be able
to handle necessary speeds
Free Body Diagram of Rover on Slope
APPENDIX: TIRE SLIP CALCULATIONS
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Minimum friction angle: = 30° [1]Maximum gradient: = 12° (Based on science missions to impact craters)Gravitational Acceleration: g = 3.711 m/s2
Rover Mass: m = 954 kg (Rover mass calculations)
Coefficient of kinetic friction:
Tangential friction force:
φθ
( )tanψ φ=(30 )tanψ = °
0.577ψ =
* ( )frictionF mg cosψ θ=20.577*954 *3.71 / * (12)frictionF kg m s cos=
2000frictionF N=
APPENDIX: TIRE SLIP CALCULATIONS (CONT.)
Necessary Friction Force:
Necessary force must be less than actual friction force to avoid slip:
The tires will not slip
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* ( )necessaryF mg sin θ=2954 *3.711 / * (12)necessaryF kg m s sin=
736necessaryF N=
Neccesary FrictionF F<736 2,000N N<<
APPENDIX: ROVER MASS CALCULATION
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Component Mass SourceFrame 50 kg CAD ModelWheels 35 kg CAD ModelAxles 15 kg CAD ModelBattery 600 kg JD BensmanSolar Panels 101 kg JD BensmanDrill 50 kg [1]Samples 100 kg ScienceSpectrometer 3 kg ScienceTotal 954 kg
APPENDIX: ROVER SLOPE FBD
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NormalF
WeightF
*sin( )mg θ
θ
FrictionF
APPENDIX: LARGE OPTICAL TELESCOPE CAD
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• Similar design to that of the extremely large telescope
• Adaptive optics mirror array• Used in combination with the
large x-ray telescope
Telescope Mirror Array and Light CollectorDoors close when telescope is not in use to
protect the mirror array.
APPENDIX: BASKETBALL HOOP CAD
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• Hoop designed for standard height
• Shooting at same sized target so equally hard
• Ball will follow shallower arc because of lower gravity acceleration, making shooting harder
• People can jump higher meaning more will be able to dunk
APPENDIX: VOLLEYBALL NET CAD
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Made to standard men’s indoor volleyball dimensions
APPENDIX: MINE SITE SCENE
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Resource extraction scene created using CAD from Sean Thompson and Anand Iyer
REFERENCES
• [1] R. Sullivan, R. Anderson, J. Biesiadecki, T. Bond and H. Stewart, "Cohesions, friction angles, and other physical properties of Martian regolith from Mars Exploration Rover wheel trenches and wheel scuffs," AGU 100, 2011.
• [2] M. David and L. Tze-Liang, "High-Speed Traversal of Rough Terrain Using a Rocker-Bogie Mobility System," ASCE Library, 2002.
• [3] Williams, D., “Mars Rover "Spirit" Images,” NASA Available: https://nssdc.gsfc.nasa.gov/planetary/mars/mars_exploration_rovers/
mera_images.html.
3/27/2018 186
DEEP ICE CORE DRILLING
Annie PingPropulsion
Science SupportMarch 27, 2018
03/27/2018 187
THE PROBLEM• Problem: Mining ice cores to study the life on Mars
• Requirements:• Have to mine 3 km deep (Science System)• Location: North and South pole of Mars (Science System)
• Assumptions:• Distance from city (linear route – shortest route) [Pau Pineda Bosque]
• North Pole – 7400 km• South Pole – 3000 km
• People travel in personnel maintenance vehicles rails from ground transport – 12.9 m/s
• Need to Determine:• Amount of resources • Feasibility
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MISSION OVERVIEW
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North Pole South Pole
Steel [Mg] 1.30 x 106 2.56 x 105
Aluminum [Mg] 17.4 7.07
Concrete [Mg] 8.68 x 106 3.52 x 106
Polyethylene [Mg] 59.1 24.0
North Pole South PoleTravel Duration (Round Trip) 7.98 days 3.24 days
Work Time - 2.26 days
Estimated Required Drilling Time 220 days 220 days
Table 1: Times for each mission
Table 2: Resources required for the rails to reach the poles
• Recommended time outside due to radiation – 5.5 days(Kyle Tincup)
• Would need 100 teams of 12 people
• Assuming working 24 hours per day
• Assuming no radiation shielding
• Total = 1,200 people• Dome shelters (Trevor
Waldman)• 14.4 Mg of Al each• Holds 3 people• Need 4 • Total = 57.6 Mg of Al
Conclusions:• Would not recommend
ice core drilling• Lots of resources
required for one time mission
RESOURCE COMPARISON
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North Pole South PoleEntire Ground
Transport
Steel [Mg] 1.30 x 106 2.56 x 105 2.36 x 106
Aluminum [Mg] 17.4 7.07 31.7
Concrete [Mg] 8.68 x 106 3.52 x 106 1.58 x 107
Polyethylene [Mg] 59.1 24.0 107
U.S. DEEP ICE SHEET CORING DRILL
• Able to drill 122 mm diameter ice cores to depths of 4 km
• Cable-suspended EM drill system • Capable of cutting the ice core into 3 meter sections• Equipment
• Mass = 61.7 Mg• Power = 135 kW
• Total Ice Core • 35 m3 (0.14 m3 each section)• 32.15 Mg (32 kg each section)
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U.S. DEEP ICE SHEET CORING DRILL
192
Generator
WinchMast
Electromechanical Cable
Drill
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LONGEST ICE CORE SPECS
• Antarctica• 3405 meter long core• Drilled over the course of 6 field seasons
• ~40 days were available each season for drilling• 24-hours per day drilling operations• 6-days per week schedule by a crew of ~9 drillers• Team of 12 people
• Scientists, drillers, mechanic, cook, medic
• Scaled numbers for number of workers and time of mission
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STORING THE ICE CORE
• An ice core will remain frozen up to 0 degrees C• Gases in the air bubbles within the ice will start
to diffuse when the cores get warmer than -18 degrees C
• Air bubbles are the primary interest in ice cores• Measuring ancient samples of atmospheric gases
like CO2 and methane• Martian Temperature
• -125 degrees C in the winter near the poles• 20 degrees C in the summer near the equator
19403/27/2018
ICE CORE MASS AND VOLUME
• Used volume of cylinder formula• V = pi * r2 * h• where
• r is radius of ice core (0.061 m)• h is height of ice core (3 km)
• Used density of ice to calculate mass • 0.9167 g/cm3
• Multiply density by volume
19503/27/2018
REFERENCES• Neff, P., “Ice core drilling,” AntarcticGlaciers Available:
http://www.antarcticglaciers.org/glaciers-and-climate/ice-cores/ice-core-drilling/• “About Ice Cores,” National Science Foundation Ice Core Facility Available:
https://icecores.org/icecores/drilling.shtml• Sharp, T., “What is the Temperature of Mars?,” Space.com, Purch Available:
https://www.space.com/16907-what-is-the-temperature-of-mars.html
19603/27/2018
MEHDL OVERVIEW
Alex BlankenbergerCommunications Infrastructure
Communications & Control03/27/2018
3/27/2018 197
PROBLEMProblemWhat does the interplanetary communication network look like?RequirementMaintain uninterrupted connection between Earth, Mars, and Cycler.ConsiderationsHow many satellites?What orbits?How big are they?GoalProvide a high-bandwidth data link for the Martian settlers to communicate with Earth.
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CAD Model Credit: Sam Zemlicka-Retzlaff
SOLUTION
3/27/2018 199
Satellites Dry Mass [kg] Orbit Antennae Diameters [m]
3 x Earth Terminal 1,020 kg Geostationary Downlink: 0.5 m
Long Distance: 10 m1 x Mars Terminal Primary
1,780 kg Areostationary Downlink: 0.5 m
Crosslink: 2 x 0.5 m
Long Distance: 5 m2 x Mars Terminal Secondary
1,780 kg Areostationary Crosslink: 0.5 m
Long Distance: 5 m1 x Backup Relay 1,540 kg Heliocentric, out of
phase with Mars by 8ºTo Mars Terminal: 5 m
To Earth Terminal: 7 m2 x Cycler A lot bigger. Powered Trajectory Long Distance: 2 x 25 mNormal operation (42 Mbps):
Earth Ground ↔ Earth Terminal ↔ Cycler ↔ Mars Terminal ↔ Mars GroundIn conjunction (10 Mbps):
Earth Ground ↔ Earth Terminal ↔ Backup Relay ↔ Mars Terminal ↔ Mars Ground
APPENDIX A
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Mars Terminal/Earth Terminal ↔ Cycler LBAFSS Forward Link Cases* Small User Units Initial NotesUplink Frequency 60.00 GHz [1]Gateway Terminal Type Tracking
Diameter 10.00 m [1]Beamwidth 0.035 degAntenna Efficiency 55.0% % Assumed typical valueGain 73.37 dBiTransmit Power 1800.0 W [1]Backoff and Line Loss -1.5 dB [1]EIRP, Gateway 104.42 dBWEIRP per user 104.42 dBW
Propagation Range 402,500,000.0 kmWorst Case: Cycler to Mars Terminal or Relay
Space Loss -300.11 dBAtmospheric Losses 0.0 dB [1]Net Path Loss -300.11 dB
Satellite Antenna, TypeDiameter 25.0 mAntenna Efficiency 55.0% % Assumed typical valueGain 81.33 dBiLine Loss on Satellite -1.5 dB [1]Received Carrier Power Per User, C -115.86 dBWSystem Noise Temperature 27.4 dB-K Typical value selected for this scenarioG/T 53.93 dB/KReceiver C/No 85.34 dB-HzData rate per user 76.23 dB-HzAvailable Eb/No, Uplink 9.10 dB
Link Budget Analysis (LBA) done in collaboration with Noah Gordon
APPENDIX A CONT.
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Mars Terminal/Earth Terminal ↔ Cycler LBA
Modem Implementation Loss -1.20 dB Representative for this scenarioRequired Eb/No 4.76 dBLink Margin Up 3.1 dBChannel Bandwidth 36 MHzNumber of Channels 1Number of Users/Channel 1Single User Data Rate 42 MbpsCode Rate, ρ 2/3 Single User Bandwidth 42.210 MHzBandwidth Used/Channel 42.21 MHzTotal Capacity 42 Mbps
Link Budget Analysis (LBA) done in collaboration with Noah Gordon
APPENDIX B
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Mars Terminal ↔ Relay LBA
FSS Forward Link Cases* Small User Units Initial NotesUplink Frequency 60.00 GHz [1]Gateway Terminal Type Tracking
Diameter 5.00 m [1]Beamwidth 0.07 degAntenna Efficiency 55.0% % Assumed typical valueGain 67.35 dBiTransmit Power 1200.0 W [1]Backoff and Line Loss -1.5 dB [1]EIRP, Gateway 96.64 dBWEIRP per user 96.64 dBW
Propagation Range 32,000,000.0 km Relay to Mars Terminal distanceSpace Loss -278.12 dBAtmospheric Losses 0.0 dB [1]Net Path Loss -278.12 dB
Satellite Antenna, TypeDiameter 3.0 mAntenna Efficiency 55.0% % Assumed typical valueGain 62.91 dBiLine Loss on Satellite -1.5 dB [1]Received Carrier Power Per User, C -120.07 dBWSystem Noise Temperature 27.4 dB-K Typical value selected for this scenarioG/T 35.51 dB/KReceiver C/No 81.13 dB-HzData rate per user 72.04 dB-Hz
Link Budget Analysis (LBA) done in collaboration with Noah Gordon
APPENDIX B CONT.
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Mars Terminal ↔ Relay LBA
Modem Implementation Loss -1.20 dB Representative for this scenarioRequired Eb/No 4.76 dBLink Margin Up 3.1 dBChannel Bandwidth 36 MHzNumber of Channels 1Number of Users/Channel 1Single User Data Rate 10 MbpsCode Rate, ρ 2/3 Single User Bandwidth 10.050 MHzBandwidth Used/Channel 10.05 MHzTotal Capacity 10 Mbps
Link Budget Analysis (LBA) done in collaboration with Noah Gordon
APPENDIX C
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Relay ↔ Earth Terminal LBAFSS Forward Link Cases* Small User Units Initial NotesUplink Frequency 60.00 GHz [1]Gateway Terminal Type Tracking
Diameter 7.00 m [1]Beamwidth 0.05 degAntenna Efficiency 55.0% % Assumed typical valueGain 70.27 dBiTransmit Power 5300.0 W [1]Backoff and Line Loss -1.5 dB [1]EIRP, Gateway 106.01 dBWEIRP per user 106.01 dBW
Propagation Range 402,500,000.0 km Worst Case: Mars Terminal/Relay to EarthSpace Loss -300.11 dBAtmospheric Losses 0.0 dB [1]Net Path Loss -300.11 dB
Satellite Antenna, TypeDiameter 10.0 mAntenna Efficiency 55.0% % Assumed typical valueGain 73.37 dBiLine Loss on Satellite -1.5 dB [1]Received Carrier Power Per User, C -122.23 dBWSystem Noise Temperature 27.4 dB-K Typical value selected for this scenarioG/T 45.97 dB/KReceiver C/No 78.97 dB-HzData rate per user 70.00 dB-HzAvailable Eb/No, Uplink 8.97 dB
Link Budget Analysis (LBA) done in collaboration with Noah Gordon
APPENDIX C CONT.
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Relay ↔ Earth Terminal LBA
Modem Implementation Loss -1.20 dB Representative for this scenarioRequired Eb/No 4.76 dBLink Margin Up 3.0 dBChannel Bandwidth 36 MHzNumber of Channels 1Number of Users/Channel 1Single User Data Rate 10 MbpsCode Rate, ρ 2/3 Single User Bandwidth 10.050 MHzBandwidth Used/Channel 10.05 MHzTotal Capacity 10 Mbps
Link Budget Analysis (LBA) done in collaboration with Noah Gordon
REFERENCES
1Wertz, J. R., Everett, D. F., and Puschell, J. J., Space Mission Engineering : The New SMAD, Microcosm Press, 2011.
3/27/2018 206
COMMUNICATIONS INFRASTRUCTURE:THE FINAL DESIGN
Ryan DuongDiscipline: Mission Design
Vehicle & Systems Group: Communications Infrastructure3/27/18
207
208
MNet MEHDL GroundStation
CommunicationsInfrastructure
TotalMass (Mg) 1.67 10.3 1.73 18.9
Power (kW) 4.65 100 2.22 107
Volume (m3) 4.55 27.5 1.22 33.3
“What does the Martian communication network look like?”via Project Future Mars’ mission statement
System Summary:The Martian Communications Network (MNet)- 4 Draim Satellites [1]
The Mars-Earth High Data Link- 3 Areostationary Satellites- 3 Geostationary Satellites- 1 Relay Satellite [2]- Cycler (from Space Transport)
Problem: We were tasked with designing a comprehensive communications infrastructure on Mars that will provide constant global coverage and HD interplanetary communications and data transfer.
Solution: We performed several trade studies and analyses this semester regarding constellation designs, mission budgets (power, thermal, link, ΔV), and designed an eight satellite space segment.
“What does the Martian communication network look like?”via Project Future Mars’ mission statement
209
MNet
MEHDL-M
MEHDL-S
Cycler
MEHDL-E
New Planet, who dis?
Yo Rosco, waddup cuz?
Primary
CAD via Sam Zemlicka-Retzlaff & Anand IyerOrbits via FreeFlyer & STK
APPENDIX – REQUIREMENTS
To establish a comprehensive communications infrastructure, the system shall be comprised of two unique systems.
The Martian Communication Network shall:• Maintain constant global coverage to Martian ground-based
operations.• Operate throughout a 15 year mission lifespan. [3]• Be easy to manufacture on Mars. • Launch from Mars.
The Mars-Earth High Data Link shall:• Maintain interplanetary two-way continuous HD video communication.• Provide constant communications with the Martian Cyclers.• Accommodate all types of data for the city residents.• Maintain uninterrupted coverage during the Solar Conjunction. [4]• Operate throughout a 15 year mission lifespan.• Be easy to manufacture on Mars.
210
APPENDIX – CAD
211
MNet MEHDL-M MEHDL-E MEHDL-SCAD from Sam Zemlicka-Retzlaff
REFERENCES[1] Draim, J. E., “A common period four-satellite continuous global coverage
constellation,” Journal of Guidance, Control, and Dynamics, vol. 10, 1986, pp. 492–499.
[2] Gangale, T., “MarsSat: Assured Communication with Mars,” Annals of the New York Academy of Sciences, 10.1196/annals.1370.007
1Mehrotra, R., “Regulation of Global Broadband Satellite Communications” Available:<http://www.itu.int/ITU-D/treg/broadband/ITU-BB-Reports_RegulationBroadbandSatellite.pdf>.
2Morabito, D., and Hastrup, R., “Communications with Mars During Periods of Solar ...”Available: <https://www.bing.com/cr?IG=07641EBAB4924EB1AF812C15E6B297B0&CID=1776978211C96A2B08209C1810666BCB&rd=1&h=r85t7GNQwGCN8J1ojqiGMxDGv5GbAgseKK9Vl47DdQ&v=1&r=https%3a%2f%2fipnpr.jpl.nasa.gov%2fprogress_report%2f42-147%2f147C.pdf&p=DevEx,5066.1>.
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A CLOSER LOOK AT PROPELLANT BOILOFF
Name: Connor LynchDiscipline Group: Propulsion
Vehicle & Systems Group: Communications InfrastructureDate: March 27, 2018
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THE PROBLEM
• Cryogenic propellants reach their boiling point from external heat sources.
• Internal pressure increases → release vapor to prevent too much pressure buildup
3/27/2018 214
Q
Q
Boiloff ArgonImage of Tank by Samuel Zemlicka-Retzlaff
𝐵𝐵𝐵𝐵𝑅𝑅 =𝑄𝑄 ∗ 3600 ∗ 24∆𝐻𝐻 ∗ 𝑚𝑚𝑠𝑠 ∗ 𝜌𝜌𝑠𝑠
∗ 100
= Boiloff rate (%/day)
Average: 38%/life
[1]
PREVENTATIVE MEASURES
• Well-insulated tank• Use vaporized gas as propellant rather than
release it [2]• Include additional propellant for the mission.• Apply developing “zero-boil off” methods to
satellite interior [3]
3/27/2018 215
Mass (Mg) Volume (m3)
Argon of Whole Comm. System (per
15 years)0.420 0.301
REFERENCES
[1] Dobrota, D., Lalic, B., Komar, I., “Problem of Boil-off in LNG Supply Chain,” Transactions on Maritime Science, 2013, Vol. 2, pp. 91-100.
[2] Welle, R. P., “Propellant Storage Considerations for Electric Propulsion,” Proceedings of the 22nd
International Electric Propulsion Conference, 1991.
[3] Plachta, D. W., Christie, R. J., Carlberg, E., Feller, J. R., “Cryogenic Propellant Boil-Off Reduction System,” AIP Conference Proceedings 985, 2008.
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