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Propulsion Stage
EAV
Falcon XX
Parth Trivedi
Propulsion Stage
Disposable EAV
Launch
Parth Trivedi
Crew A Crew 1 Crew 1-2 Crew 1-3 Crew 1-4 Crew 1-5 Crew 1-6 Crew 1-7 DRA 5 *
Total cost (2004 millions) 155625 158544 206509 257002 303206.4 346006 385080.8 421338.4 75000
Days 547 5479 5479 5479 5479 5479 5479 5479 550
Days * People 4000 43800 81760 113880 140160 160600 175200 183960 3300
Millions/ Person Day 38.91 3.62 2.53 2.26 2.16 2.15 2.20 2.29 22.73
*DRA 5 cost is not officially posted, not confident in DRA 5 cost
Falcon 9 Heavy › To carry crew capsule and propellant
required to rendezvous with transit vehicle
Image Credit: http://www.spacex.com/assets/img/20110405-falcon-heavy.jpg
Payload
Mass [t]
Cost Per
Launch
Cost per kg of
payload
53.0 $125 Million $2358.49
Falcon XX › To carry Cargo Vehicles into LEO
› To carry crew vehicle components to be
assembled in LEO
Image Credit: http://www.spacex.com/assets/img/20110405-falcon-XX.jpg
Payload
Mass [t]
Cost Per
Launch
Cost per kg of
payload
150.0 $300 Million $2000
Circular Spiral Out › Constant thrust
Parameter Value
TOF [days] 350
Mo[t]* 113
Mp[t] 15
Mf[t] 98
*Mo – mass at LEO (350 km)
Various departure dates starting in 2022 › Multiple cargo missions per departure date
› 21 Total Cargo Missions
Parameter Value
TOF [days] 316
Mo[t]* 98
Mp[t] 12
Mf[t]t 87
*Mo – Earth Departure Mass t Mf – Mars Arrival Mass
Assemble Crew Transit Vehicle in LEO
Crew A: 2 Launches to assemble spacecraft
+ 1Crew Rendezvous
=3 total Launches
Crew 1-7: 1 Launches to assemble spacecraft
+ 1Crew Rendezvous
=2 total Launches
Crew Transit Vehicle +
EP Tug Mass
Mo[t]* 196.0
Image by Sam Rieger
Elliptical Spiral
Electric Propulsion
Parameter Value
TOF [days] 669
Mo[t]* 196
Mp[t] 37.3
Mf[t] 158.7
*Mo – mass at LEO (350 km)
Samantha Rieger
Parameter Value
Power 900 kM
Thrust 35 N
Thrust for
Decay orbit 1.78 N
Isp 4000 s
Crew rendezvous when
Earth Escape Tug (EET)
reaches periapsis of
highest energy ellipse
Launch vehicle capsule
will fall back to Earth to
be reused
Once Crew departs, EET
will perform aerobraking
maneuvers back into a
circular orbit
Image by Peter Barchert
Impulsive ΔV at
perigee of ellipse
will place crew in
transfer arc to
Mars
-2.5 -2 -1.5 -1 -0.5 0 0.5 1 1.5 2 2.5
x 108
-2.5
-2
-1.5
-1
-0.5
0
0.5
1
1.5
2
2.5x 10
8
x direction (km)
y d
irection (
km
)
Interplanetary leg
Earth orbit
Mars orbit
Transfer
Departure
Arrival
Image by Peter Barchert
Parameter Value
Impulsive ΔV 0.65 km/s
Plane Change ΔV 24.3 m/s
Correction Maneuvers ΔV
100 m/s
Total ΔV 0.77 km/s
Slow down in the atmosphere and go through a series of
maneuvers to end in a circular orbit
-2 -1 0 1 2
x 104
-2.5
-2
-1.5
-1
-0.5
0
0.5
1
1.5
2
2.5x 10
4 Hyperbolic Martian Approach
x-distance (km)
y-d
ista
nce (
km
)
Mars
Martian Atmosphere
Synchronous Orbit
Approach
Atmospheric Entry
Mars Sphere of Influence
-6 -4 -2 0 2 4 6
x 105
-6
-4
-2
0
2
4
6x 10
5 Hyperbolic Martian Approach
x-distance (km)
y-d
ista
nce (
km
)
Mars
Martian Atmosphere
Synchronous Orbit
Approach
Atmospheric Entry
Mars Sphere of Influence
Parameter Value
V∞/♂ 4.04 km/s
V at atmosphere 6.36 km/s
Flight Path Angle -9.6˚
V- [km/s] Vcircular [km/s] ΔV [km/s] Mp [t]
3.52 3.45 0.091 2.36e-3
16
V- [km/s] Vcircular [km/s] ΔV [km/s] Mp [t]
3.52 3.45 0.088 2.26e-3
Drawing by Monica Pires
Atmospheric
Entry
Atmospheric Exit
Raise
Maneuver
Locations
17
Elliptical Spiral
Electric Propulsion
Parameter Value
TOF [days] 89.48
Mo[t]* 29.5
Mp[t] 4.05
Mf[t] 25.45
*Mo – mass at LEO (350 km)
Samantha Rieger
Parameter Value
Power 850 kW
Thrust 25 N
Isp 4900 s
Inputs/Assumptions
› a = 2.8gMars
› m = 105 t
› Isp = 375 s
› Constant mass
› Drag of atmosphere
Results
› ΔV = 3.88 km/s
› TOF = 404.1 s
1 2 3 4 5 6
x 105
0
0.5
1
1.5
2x 10
5
Rosalie Geeck and Monica Pires
Trajectory of Launch from Mars
X-position (m)
Y-p
ositio
n (
m)
Final Altitude
Final Trajectory
0 100 200 300 400
-20
0
20
40
60
Rosalie Geeck and Monica Pires
Steering Angle, , vs Time
time (s)
Ste
ering A
ngle
,
(deg)
0 1000 2000 30000
200
400
600
Rosalie Geeck and Monica Pires
Y-Velocity vs X-Velocity
Velocity x-component (m/s)
Velo
city y
-com
ponent
(m/s
)
0 100 200 300 4000
1000
2000
3000
Rosalie Geeck and Monica Pires
Velocity Components vs Time
time (s)
Velo
city (
m/s
)
Velocity: x-direction
Velocity: y-direction
-2.5 -2 -1.5 -1 -0.5 0 0.5 1 1.5 2 2.5
x 108
-2
-1.5
-1
-0.5
0
0.5
1
1.5
2
x 108 Samantha Rieger
e axis (km)
p a
xis
(km
)
Earth
Mars
Transfer Orbit
Stay on Mars TOF Necessary transfer ΔV
Actual impulsive ΔV (reduces due to tug)
547 days 180 days 3.43 km/s 1.88 km/s
& Rosie Geeck
Circularizing Earth EP tug maneuvers (low
thrust or impulsive)
Find minimum ΔV to orient flight path
angle at Mars atmospheric entry
Finalize Crew and Cargo Missions
Finalize Earth Elliptical spiral for Crews
1-7
Mission Number of Missions Departure Date end spiral Mars Arival Date tof spiral tof transfer tof
com 1 7/1/2022 7/1/2022 10/3/2023 100.50 458.00 558.50
fuel 3 7/27/2023 7/19/2024 6/7/2025 357.30 323.30 680.60
A1 2 4/24/2021 5/30/2020 5/5/2023 339.40 400.90 740.30
1 1 7/21/2023 7/27/2024 7/31/2025 372.80 368.00 740.80
2 2 2/28/2025 9/3/2026 7/13/2027 340.30 313.10 653.40
3 2 10/30/2027 10/13/2028 8/2/2029 348.80 293.30 642.10
4 2 11/19/2029 12/4/2030 9/2/2031 379.60 272.40 652.00
5 2 4/6/2034 4/11/2035 12/23/2035 369.50 256.50 626.00
6 2 3/25/2034 4/25/2035 4/21/2036 395.40 362.40 757.80
7 2 6/26/2036 5/31/2037 3/23/2038 338.90 295.50 634.40
8 2 11/3/2038 7/28/2039 4/29/2040 267.80 275.60 543.40
21 350.98 316.10 667.08
Mo mf1 Mp1 Mp2 Mp Ma [t] Vinf filename
33432.80 29277.00 4155.80 2208.50 6364.30 27068.50 2.91 cargocom
113140.00 98366.30 14773.70 13366.30 28140.00 85000.00 3.70 cargof
126488.50 109910.70 16577.80 12910.70 29488.50 97000.00 3.61 cargoa1b
117894.50 102478.80 15415.70 12478.80 27894.50 90000.00 3.32 cargo1c
107923.40 93853.50 14069.90 11853.50 25923.40 82000.00 3.13 cargo2b
110522.70 96102.20 14420.50 11102.20 25522.70 85000.00 3.58 cargo3b
119958.90 104264.30 15694.60 11264.30 26958.90 93000.00 3.54 cargo4b
116882.60 101603.60 15279.00 10603.60 25882.60 91000.00 3.13 cargo5b
124791.40 108443.30 16348.10 12443.30 28791.40 96000.00 2.41 cargo6b
107499.00 93486.30 14012.70 11486.30 25499.00 82000.00 3.15 cargo7b
85627.00 74554.50 11072.50 10554.50 21627.00 64000.00 3.64 cargo8b
113072.80 98306.35 14766.45 11806.35 26572.80 86500.00 3.32
113.07 98.31 14.77 11.81 26.57 86.50
Mission Earth Departure Mars Arrival
Date V∞ [km/s] ΔV [km/s] Date V∞ [km/s] Vp [km/s]
A/1 12/06/2026 4.86 1.190 06/04/2027 5.83 7.625
2 01/14/2029 4.80 1.146 07/13/2029 5.34 7.257
3 03/06/2031 4.80 1.146 08/25/2031 4.52 6.677
4 05/05/2033 3.50 0.683 11/01/2033 3.46 6.011
5 07/09/2035 3.47 0.674 01/05/2036 2.73 5.622
6 09/11/2037 4.87 1.174 03/10/2038 3.31 5.925
7 10/20/2039 5.00 1.228 04/15/2040 4.93 6.961
VASIMR Engine
Engine Parameters
Power Requirement , [kw] 850
Isp , [s] 4900
Engine Mass , [t] 4.25
Reactor Mass , [t] 5.95
Cargo
Comm.
Cargo
(Fuel)
Cargo
A1
Cargo
1
Cargo
2
Cargo
3
Cargo
4
Cargo
5
Cargo
6
Cargo
7
Cargo
8
Payload
mass , [t] 12.57 70.50 82.50 75.50 67.50 70.50 78.50 76.50 81.50 49.50 72.00
Propellant
mass , [t] 6.36 28.14 29.49 27.89 25.92 25.52 26.96 25.88 28.79 25.50 21.63
Tank mass
, [t] 0.64 2.81 2.95 2.79 2.59 2.55 2.70 2.59 2.88 2.55 2.16
Reactor
mass , [t] 5.95 5.95 5.95 5.95 5.95 5.95 5.95 5.95 5.95 5.95 5.95
Engine
mass , [t] 4.25 4.25 4.25 4.25 4.25 4.25 4.25 4.25 4.25 4.25 4.25
Propulsion
total
system
mass , [t]
17.20 41.15 42.64 40.88 38.72 38.27 39.85 38.67 41.87 38.25 33.99
Total
vehicle
mass , [t]
(at
departure)
90.47 111.65 125.14 116.38 106.22 108.77 118.35 115.17 123.37 87.75 105.99
Electric Propulsion Tug
Power
Requirement ,
[kw]
900
Isp , [s] 4000
Thrust , [N] 32.1
Propellant Mass ,
[t]
64.6
Inert Mass , [t] 32.5
Total System
Mass , [t]
97.1
Chemical Propulsion (impulsive burn)
Propellant LOX/CH4 (4:1)
Delta V , [km/s] 0.77
Isp , [s] 400
Propellant Mass ,
[t]
27
Inert Mass 4.6
Total System
mass , [t]
31.6
Illustration by Shourya Jain
LH2 Required: 1.5 T
Propellant + tank Req:
95 T
Launch
at Mars
(2 stage)
Impulsive
burn at LMO
(2 stage)
Payload Mass
Capsule
Required Propellant +
Tank Mass at LMO
5 T
5 T
0 T
62 T
Burn Time (each
stage)
150 sec 500 secs
Propellant Mass 10 T 81.5 T
Inert Mass 2 T 13 T
Total Mass 17 T 156 T
Electric Propulsion Tug
Power
Requirement ,
[kw]
900
Isp , [s] 4000
Thrust , [N] 32.1
Propellant Mass ,
[t]
64.6
Inert Mass , [t] 32.5
Total System
Mass , [t]
97.1
Chemical Propulsion (impulsive burn)
Propellant LOX/CH4 (4:1)
Delta V , [km/s] 0.77
Isp , [s] 400
Propellant Mass ,
[t]
22.6
Inert Mass 3.68
Total System
mass , [t]
26.28
N2O4/Aerozine 50 bipropellant engine
› Total thrust: 261 kN
Four engines at 65 kn
› Specific Impulse 331 s
System
(Per Engine) Mass Volume (m3)
Fuel 341 kg 0.28
Oxidizer 764 kg 0.63
Pressurant 3.77 kg 0.04
Dry Engine 500 kg 0.05
Totals 6.43 t 4
I = 5.2 e6 N-s
tb= 10 hr = 36,000 s
F = 144 N
mp = 2.42 t
Fper = 18 N
mo = 1.71 kg
Dc = 1.1cm
Dc = 0.25 cm Catalyst Bed
Images by Thomas Mifsud
De = 1.14 cm
System Mass Volume (m3)
AGpropellant 302 kg 0.30
AGpressurant 1.77 kg 0.048
A/Cpropellant 53 kg 0.052
A/Cpressurant 0.31 kg 0.0084
Totals (est)* 4.96 t 4.89
AG Total @ 16 Thrusters (I = 5.2e6 N-s)
AC Total @ 30 Thrusters (I = 1.2e4 N-s) *Mass Totals = 46 Total Thrusters + Propellant + Total Pressurants
3CO2+6H2=>CH4+2CO+4H2O
2H2O=>2H2+O2
Mass Leverage =
Electrolysis can be used for Human
Factors
By Richard O’Connor
Ballute material is
Kapton
Filled with Helium Gas
to Mars surface
Pressure for landing
and 100 Pa for
Aerocapture
Tethers are PBO
Low Heating Rates with Ballutes
Non-Ablators Carbon phenolic
If a Ballute is usable than this Heat shield
will work
TPS
Mass 3.0 t
Use of Atmosphere to
change the Orbit
Initial Conditions
Velocity 10.94 km/s
Altitude 256000 km
After 20 days of
Aerobraking
Finals Conditions
Energy Dissipation 297 MJ
Heat Shield Mass 4.01 t
By Mounia Belmouss
Using the Atmospheric
Drag to do a ΔV for
entering into an Orbit
3500 4000 4500 5000 5500 6000 6500 7000 7500 800060
80
100
120
140
160
180
200
220
240Altitude vs. Velocity
Velocity [m/s]
Altitude [
Km
]
Total Mass 50 t
Velocity 7.625 km/s
Ballistic Coefficient (β) 1.5 kg/m2
Ballute Mass 3 t
TPS Mass 3 t
Max g’s 5g
Crew
Mass 46.4 t
Velocity 3.5 km/s
Ballistic Coefficient (β) 3.8 kg/m2
TPS Mass 3.0 t
Ballute Mass 2.93 t
3300 3350 3400 3450 3500 3550 3600 3650 3700
-500
-400
-300
-200
-100
0
100
x [km]
y [
km
] Working on pinpoint landing
Working on last 14km and
handing over to hovering
Cargo
Mass 68t – 91t
Velocity 6.0 km/s
TPS Mass 3.0 t
Ballute Mass 4.89 t
3300 3350 3400 3450 3500 3550 3600
-700
-600
-500
-400
-300
-200
-100
0
x [km]
y [
km
]
Some of the Cargo Missions will be Aerocaptured to LMO
Increased Mass gives a better ballute efficiency
Looking into Subsonic Parachutes
Astronauts would get a spike in g’s of about 4g
Multi-chute designs similar to Apollo being considered
Direct Re-entry into Earth
Use of Capsule with Subsonic Parachutes similar to Apollo/Orion
PICA-X ablator
6200 6300 6400 6500 6600 6700 6800
-1200
-1000
-800
-600
-400
-200
0
x [km]
y [
km
]
Conditions
Initial Velocity 12.6 km/s
Flight Path Angle -7.1o
Max gs 6.6 g
Heat Shield Mass 0.64 t
θ is longitude
R is radius from the
center of Mars
ω is the angular
velocity of Mars
D is Drag
Ψ is heading angle
relative to the North
Φ Flight Path Angle
η is the latitude
V is velocity
From Gates page 10, Gates got from Vinh
Rdot = V*sinΦ
Φdot = (1/V)*(g –(V^2)/R))*cos(Φ) +2*
ω*cos(η)*cos(Ψ)
+(R*w^2)/velocity*(cos(Φ)*cos(η)-
sin(Φ)*sin(η)*sin(psi))
Vdot = -D/M +(g)*sin(Φ)+ (ω ^2)
*R*cos(lat)*(sin(Φ)*cos(η)-
cos(Φ)*sin(η)*sin(Ψ))
θdot = V*cos(Φ)* cos(Ψ)/(R*cos(η))
ηdot = V*cos(Φ)*sin(Ψ)/R
Ψdot = -(V/R)*cos(Φ)*cos(psi)*tan(η)+2* ω
* (tan(Φ)*cos(Ψ)-sin(η))-
(r*w^2)/(V*cos(Φ))* sin(Φ)*cos(η)*cos(Ψ)
Cargo
Mission Vinf km/s
Vmar km/s
Mass t
flight Path degrres
Ballute r m
Ballute R m
Ballute Mass t TPS t
Aero Mass t Max g
Max qpres Pa
max q hball W/cm2
Vend Km/s
Altend km
1 3.36 5.953496 91 -9.8 23.4 93.6 4.89 3 7.89 2.06 109.22 1.58 104.6 14
2 3.26 5.897636 78 -9.6 23.4 93.6 4.89 3 7.89 2.38 104.71 1.5 95.27 14
3 3.31 5.925421 89 -9.6 23.4 93.6 4.89 3 7.89 2.1 105.574 1.57 103.2 14
4 3.53 6.051067 97 -9.8 23.4 93.6 4.89 3 7.89 2.24 128.37 1.7762 108.69 14
5 3.51 6.039422 96 -9.8 23.4 93.6 4.89 3 7.89 2.386 129.18 1.768 108 14
6 3.34 5.942232 90 -9.7 23.4 93.6 4.89 3 7.89 2.25 124.3 1.68 109.3 14
7 3.26 5.897636 78 -9.6 23.4 93.6 4.89 3 7.89 2.14 103.4 1.55 101 14
8 3.46 6.0105 68 -9.6 23.4 93.6 4.89 3 7.89 2.17 93.11 1.51 93.7 14
9 3.46 6.0105 68 -9.6 23.4 93.6 4.89 3 7.89 2.17 93.11 1.51 93.7 14
Mission Vp [km/s] Mass [t]
flight
Path [degree]
Ballute r [m]
Ballute R [m]
Ballute Mass [t]
Velocity
Detach [km/s] TPS [t]
Aero Mass [t] Max g
Max qpres [Pa]
max q
hball [W/cm2
A 7.625 58.48 -10.7 41.6 104 3.42 3660 3 6.42 5.1 85.1 1.6463
1 7.625 52.13 -10.7 39 93.6 2.73 3655 3 5.73 4.9 86.98 1.73
Aerocapture
Landing
Mission Vp [km/s] Mass [t] flight Path [degree]
Ballute r [m]
Ballute R [m]
Ballute Mass [m] TPS [t]
Aero Mass [t] Max g
Max qpres [Pa]
max q hball [W/cm2]
Vend [m/s]
Altend [km]
A 3.5069 55.06 -7 19.5 78 2.93 3 5.93 4.127 186.5 0.5998 95.95 14
1 3.5069 46.4 -7 19.5 78 2.93 3 5.93 4.12E+
00 157 0.5499 86.7 14
Landing
vtraj.m – uses Vinhs equations of Motion
to find rates of change.
trajectory_full_circlar_notflat.m –full
trajectory file
[1] Anderson, J.D. Hypersonic and High Temperature Gas Dynamics II Ed. AIAA, Inc. Reston, Virginia 2006.
[2] Braun, R. D. and Manning, R. M., “Mars Exploration Entry, Descent and Landing Challenges,” Journal of Spacecraft and Rockets, Vol. 44, No. 2, March—April, 2007., pp. 310—323.
[3] Gates, K. L., “Theory and Applications of Ballute Aerocapture andDual Use Ballute Systems for Exploration of the Solar System,” Ph.D. Thesis, School of Aeronautics and Astronautics, Purdue University, West Lafayette, IN, Aug. 2009.
[4]“Public Access to Mars Global Surveyor Radio Science Standard Atmospheric Temperature-Pressure Profiles” http://nova.stanford.edu/projects/mgs/tps-public.html. 11 January 2011
[5] Vinh, N. X., Busemann, A., and Culp, R. D., Hypersonic and Planetary Entry FlightMechanics, The University of Michigan Press, Ann Arbor, MI, 1980.
[6] Lockwood Mary Kae“Mars Exploration Entry, Descent and Landing Challenges,” Journal of Spacecraft and Rockets, Vol. 44, No. 2, March—April, 2007., pp. 310—323.
Crew A Phase Power System Power System Type In Use During Phase Mass [kg] Mass Rollup [kg]
Spiral Spin Up
Tug T Reactor Y 17001.85
41753.67 T Hab Solar N 5371.00
Rovers (4) Methane IC N 6000.00
Relays (100) Batteries N 13380.82
Transport of Crew to Trans Hab
EAV/MDV Batteries Y 242.15
24993.97 T Hab Solar Y 5371.00
Rovers (4) Methane IC N 6000.00
Relays (100) Batteries N 13380.82
Transit to Mars Orbit
EAV/MDV Batteries N 242.15
24993.97 T Hab Solar Y 5371.00
Rovers (4) Methane IC N 6000.00
Relays (100) Batteries N 13380.82
Mars Descent
EAV/MDV Batteries Y 242.15
19622.97 Rovers (4) Methane IC N 6000.00
Relays (100) Batteries N 13380.82
Crew A (Continued) Phase Power System Power System Type In Use During Phase Mass [kg] Mass Rollup [kg]
Surface Operations
Rovers (4) Methane IC Y 6000.00
26110.76
Relays (100) Batteries Y 13380.82
Surface Hab C Reactor Y 6390.93
ISRU
MAV Batteries N 96.86
EDV Batteries N 242.15
Mars Ascent
MAV Batteries Y 96.86
5710.01 EDV Batteries Y 242.15
T Hab Solar Y 5371.00
Transit to Earth Orbit EDV Batteries N 242.15
5613.15
T Hab Solar Y 5371.00
Earth Descent EDV Batteries Y 242.15
242.15
Crew 1-7 Phase Power System Power System Type In Use During Phase Mass [kg] Mass Rollup [kg]
Spiral Spin Up
Tug T Reactor Y 17001.85
28372.85 T Hab/S Hab Solar N 5371.00
Rovers (4) Methane IC N 6000.00
Transport of Crew to Trans Hab
EAV Batteries Y 242.15
11613.15 T Hab/S Hab Solar Y 5371.00
Rovers (4) Methane IC N 6000.00
Transit to Mars Orbit T Hab/S Hab Solar Y 5371.00
11371.00
Rovers (4) Methane IC N 6000.00
Mars Descent T Hab/S Hab Batteries N 96.86
6096.86
Rovers (4) Methane IC N 6000.00
Surface Operations
T Hab/S Hab C Reactor
Y 6390.93
12390.93 ISRU Y
Rovers (4) Methane IC Y
6000.00
Cargo A Phase Power System Power System Type In Use During Phase Mass [kg] Mass Rollup [kg]
Transit to Mars Orbit
EP Stage
C Reactor
Y
6390.93
15639.60
ISRU Y (Partial)
Surface Hab N
Rovers (4) Methane IC N 6000.00
Probes (10) Batteries N 3151.81
MDS Batteries N 96.86
Mars Descent and Autonomous Operations
ISRU C Reactor
Y 6390.93
15639.60
Surface Hab N
Rovers (4) Methane IC N 6000.00
Probes (10) Batteries Y 3151.81
MDS Batteries Y 96.86
Surface Operations Ref Crew A: Surface Operations
Cargo 1-7 Phase Power System Power System Type In Use During Phase Mass [kg] Mass Rollup [kg]
Transit to Mars Orbit
EP Stage C Reactor
Y 6390.93
12487.79 ISRU Y (Partial)
Rovers (4) Methane IC N 6000.00
MDS Batteries N 96.86
Surface Operations Ref Crew A: Surface Operations
Comm Sats Phase Power System Power System Type In Use During Phase Mass [kg] Mass Rollup [kg]
Deploy Earth Trailing Sat ET Sat Solar Y 171.77 171.77
Deploy Mars Sats M Sat Solar Y 41.39 41.39
System Power
Requirement
[kW]
Power System
Type
Power System
Mass
[kg]
Tug 4000 Reactor 17,002
Cargo/Mars Hab 1000 Reactor 6,390.9
EAV/MDV 5 Batteries 242.15
MAV 2 Batteries 96.86
EDV 5 Batteries 242.15
Rover 70 Methane IC 1,500
Probe 7 Batteries 315.18
Transfer Hab 100 Solar 5,371
Relay Station .05 Batteries 133.81
Mars Sat 1.38 Solar 171.77
Earth Sat 0.24 Solar 41.39
𝑚𝑏𝑎𝑡𝑡 = 0.0318 𝑘𝑊ℎ 2 + 8.3213 𝑘𝑊ℎ + 7.3874
The HPM is much more massive
than Space Rated Reactors
and was thrown out
0 2000 4000 6000 8000 10000 12000 14000 16000 180000
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2x 10
4 Reactor Mass v Output
kWe
kg
Emperical Data
Curve Fit
0 2000 4000 6000 8000 10000 12000 14000 16000 180000
1000
2000
3000
4000
5000
6000
7000
8000
9000
10000Shield Mass v Output
kWe
kg
Emperical Data
Line Fit
Radiation Shielding Shows a
Linear relation to Reactor
output
Some reactors looked at used Rankine Cycle Power Converters, a Conversion Factor was applied so that a best fit solution for a Brayton Cycle could be obtained
Radiators Scale Linearly while
other components of the Heat
Rejection System do not
0 2000 4000 6000 8000 10000 12000 14000 16000 180000
1
2
3
4
5
6x 10
4 Converter Mass v Output
kWe
kg
Emperical Data
Modified to Brayton Cycle
Line Fit
0 2000 4000 6000 8000 10000 12000 14000 16000 180000
1000
2000
3000
4000
5000
6000
Radiator Mass v Output - 3.87 kg/m2 1000K Tw
kWe
kg
Radiators
Heat Rejection System
Radiator Line Fit
HRS Line Fit
Heat Rejection System Sized
using out lighter Radiators and
higher working temp
Total Mass and the masses of
each component are shown
0 2000 4000 6000 8000 10000 12000 14000 16000 180000
200
400
600
800
1000
1200
1400
1600
1800
2000
Radiator Mass v Output - 1.44 kg/m2 1200K Tw
kWe
kg
Radiators
Heat Rejection System
0 2000 4000 6000 8000 10000 12000 14000 16000 180000
1
2
3
4
5
6
7x 10
4 Total Nuclear Power System Mass v Output
kWe
kg
Total System
Reactor Core
Radiation Shield
Power Conversion System
Heat Rejection System
%reactor sizing 3
clc, clear all, close all
%% All Emperical Values:
% SAFE-400, SP-100, 1993NASA, 1988Scaled SP-100, 1983ORNL, 2001Rocketdyne, HPM
kwt=[400 2400 24000 25000 28000 52000 70000]; %kW
kwe=kwt./4; %assuming 25% actual values are [100 100 5000 25000] or [25% 4% 20% 35%]
mr=[512 700 3810 4200 3500 4500 20000];%kg Reactor Mass - emperical
ms=[0 1037 3800 3930 4100 6930 0]; %kg Shield Mass - emperical
mc=[688 909 13820 57690 11400 23762 0]; %kg Converter Mass - emperical (heat trans+power conersion)
mhr=[0 1027 4180 4180 5500 4435 0]; %kg heat Rejection Mass - emperical
Ad=[0 0 636 0 660 899 0]; % m^2 radiator Area
Mspd=[0 0 6.57 0 8.33 3.87 0]; % kg/m^2 Radiator Specific Mass
t=[1200, 0, 975, 0, 1020, 1000, 0]; %K workign temp
qdot=[0 0 31.45 0 34.85 46.72 0]; % kW/m^2 Heat Flux
md=Ad.*Mspd; %kg Radiator Mass - Emperical
% coolant loops/heat transport system are in power conversion
% - shuffled mass around
%P/A loop: ORNL 11000-4000 kg, NASA 9760-3800 kg
% moved from Shield Mass to PCS Mass - numbers are based on Scaled SP
% for Radiator mass need to accomodate for changes in qdot based on working
%% Calulated Values
acc=100;
kWt=linspace(400,70000,acc);
kWe=kWt./4;
%Reactor Mass - kg
%--HPM is way high other (space rated) show a nice curve from SAFE to
%--Rocketdyne
mR=65.5.*kWe.^0.4465; % [kg]
% mR=65.5.*kWe.^0.4465 [kg]
%%
%Shield Mass
%--Apears to be pretty much linear
PS=polyfit(kwe(2:6),ms(2:6),1);
mS=PS(1).*kWe+PS(2);
%mS=0.4731*kWe+851.4043 [kg]
%%
%Power Conversion
%--convert to Appx Brayton cycle masses using 56140/31140 conversion factor
%--applied to PCS only (not heat transfer)
r_b=56140/31140;
mcb=mc+[0 409*(r_b-1) 7860*(r_b-1) 0 4500*(r_b-1) 12060*(r_b-1) 0];
PC=polyfit(kwe([1 2 3 5 6]), mcb([1 2 3 5 6]),1);
mCb=PC(1).*kWe+PC(2);
%mCb=2.5486*kWe+492.6896 [kg]
%Radiator Mass - kg
kWw=kWt-kWe; %kWth Wasted Power
eta_eps=0.76;%0.51009743;
SBc=0.0000000567/1000; %kW/(m^2 K^4) Stephan-Boltzman Const
T=t(6); %K working Temp
To=1200; %K our system's Tw
MspD=Mspd(6); %kg/m^2 specific mass
MspDo=1.4375; %kg/m^2 Our System's Specific Mass
%radiator Area
AD=kWw/(eta_eps*SBc*(T^4)); %m^2
ADo=kWw/(eta_eps*SBc*(To^4)); %m^2
%radiator mass
mD=MspD*AD;
mDo=MspDo*ADo;
over=110.*kWw.^0.2; %Heat Rejections System Overhead Mass
mHR=mD+over;
mHRo=mDo+over;
%mHRo=(1.4375/89.3356)*(3*kWe) + 110*(3*kWe)^0.2
%%
%Total Mass
mT=mR+mS+mCb+mHRo;
% mT=65.5.*kWe.^0.4465 + 0.4731*kWe+851.4043 + 2.5486*kWe+492.6896...
% + (1.4375/89.3356)*(3*kWe) + 110*(3*kWe)^0.2
%% Solar/Battery/Fuel Cell Sizing Frankencode %% AAE 450 %% Mike Parmentier, Mike Ashenbrener clc, close all, clear all
%% Solar Array Mass - kg Xd = 0.8; %Path efficiency, assumed solfluxmars = 593; %W/m^2, average solar flux at Mars powreqE = 100000; %W, power required solfluxearth = 1358; %W/m^2, average solar flux at Earth PsaE = powreqE/Xd; %W,Power generated by solar array IdE = 0.77; %Degradation factor PoE = 0.32 * solfluxmars;%solfluxearth; %W, Power output with efficieny PbegE = PoE*IdE; %W, beginning of life power lifeE = 20; %years, lifetime LdE = (1-0.03)^lifeE; %lifetime degradation PendE = PbegE*LdE; %W, end of life power AreaE = PsaE/PendE; %m^2, array area Msp=0.85; %kg/m^2 ME=Msp*AreaE; %kg MassE = 0.04*PoE; %kg, array mass %% Radiator Mass - kg kWw=70;%kWt-kWe; %kWth Wasted Power eta_sig=0.76;%0.51009743; SBc=0.0000000567/1000; %kW/(m^2 K^4) Stephan-Boltzman Const %T=t(6); %K working Temp To=500; %K our system's Tw %MspD=Mspd(6); %kg/m^2 specific mass MspDo=1.4375; %kg/m^2 Our System's Specific Mass
%radiator Area %AD=kWw/(eta_sig*SBc*(T^4)); %m^2 ADo=kWw/(eta_sig*SBc*(To^4)); %m^2 %radiator mass
%mD=MspD*AD; mDo=MspDo*ADo; over=110.*kWw.^0.2; %Heat Rejections System Overhead Mass %mHR=mD+over; mHRo=mDo+over; %mHRo=(1.4375/89.3356)*(3*kWe) + 110*(3*kWe)^0.2
%% Battery Mass MspB=48.43; %kg/kW from ISS at nominal operating conditions kWb=20; % kW used as backup only - can draw a larger power by
more quickly draining batteries mB=MspB*kWb %or use Mike's numbers MspB2=2.7/.24; %kg/(kW*hr) OpHrs=24; OpPwr=20; mB2=MspB2*OpHrs*OpPwr % - that's 4.8 hrs at full power - more than
enough %% Total Solar Array System Mass mTsol=mHRo+ME+mB %% Capsule Entry Batteries mBcap=MspB*5 %% MAV Batteries mBmav=MspB*2 %% Fuel Cells % for 100kW hab over 180 days rO2=4*0.45359237; %kg/hr from Shuttle 14 kW rH2=0.6*0.45359237; %kg/hr RO2=rO2*100/14; %kg/hr for 100kW RH2=rH2*100/14; %kg/hr mO2=RO2*24*180; %kg/180 days - est TOF mH2=RH2*24*180; %kg/180 days mfc=255*0.45359237*5; %kg dry mass (would be 7 assuming m_i
improvements) mTfc=mfc+mO2+mH2
Nuclear Sizing Formula mT=65.5.*kWe.^0.4465 + 0.4731*kWe+851.4043 + 2.5486*kWe+492.6896... + (1.4375/89.3356)*(3*kWe) + 110*(3*kWe)^0.2 Fuel Cell Sizing Formula - Fct(t)
mTfc=578.3303+(1.8144+0.2722)*hrs [kg] - Fct(pwr) mTfc = 255*.453*0.7*kWe/14+(1.8144+0.2722)(kWe/14)*24*180 =
1.928kWe+643.8651 kWe
Solar Sizing Formula
mPsol=0.85*(kWe/0.8)/(.77*.32*1.358*(1-0.03)^20)= 13.4*kWe [kg] mRsol= mBsol=(48.43/5)*kWe mTsol=13.4*3*(1.438/89.34)*(48.43/5)kWe+110*3^0.2 kWe = 137 kWe^0.2
+ 6.267 kWe
%Michael Ashenbrener
%AAE 450
%Battery Sizing
%Sizing Code
powreq = 460; %Watt, power required
h = 17212; %km, altitude
per = 24.66; %hr, period
r = 3396.2; %km, Mars radius
a = h + r; %km, distance from center of Mars
beta = acos(r/a); %rad, angle swept out by sat. in eclipse,assuming
alpha = asin(r*tan(beta)/a); %rad, angle swept out fact. in sun incidence
tfracsun = (pi + 2*alpha)/(2*pi); %percent of period in eclipse
tday = tfracsun * per * 60 * 60; %sec, time in sunlight
tshadow = (1 - tfracsun) * per * 60 * 60; %sec, time in eclipse
tshadowhr = tshadow/60/60; %sec, eclipse time
DOD = .45; %depth of discharge
Nobatt = 1; %number of batteries
n = 0.9; %transmission efficiency
E = 250; %W-hr/kg, power density
Cr = powreq.*tshadowhr./(DOD.*Nobatt.*n); %Capacity per battery
MassB = Cr./E; %Mass mass of one battery
MassBtot = MassB.*Nobatt; %Total mass of batteries
%Curve Fit Plot
x = linspace(1,50,1000);
y = 0.0318.*x.^2+8.3213.*x+7.3874;
plot(x,y)
xlabel('kW-h')
ylabel('kg')
title('Michael Ashenbrener: Battery Sizing Curve')
http://spaceflight.nasa.gov/shuttle/reference/shutr
ef/orbiter/eps/pwrplants.html
http://www.emcore.com/assets/photovoltaics/Pa
per_Navid_9-22-00.pdf
http://www.apollosaturn.com/asnr/p27-32.htm
Badescu, Viorel, “MARS Prospective Energy and
Material Resource Guide”, Ch 9, Springer, 2009.
Will use 2 or 3 of each sensor on every crew and cargo vehicle
Total Mass/mission = 42.02 kg
Total Power/mission = 263 W
Hardware Mass [g] Power [W]
Sun Sensor 10 5
Star Sensor 20,000 120
Magnetometer 500 5
Earth-Horizon Sensor 500 1.5
Specifications/thruster
› Mass : 1.71 kg
› Thrust: 18 N
8 thrusters will be used in total on all
missions
8 back up thrusters will also used on
each mission
JY Joints - (Modified canfield joints) Mass: 4kg
Power: TBD
Has four arms instead of three
More accurate pointing than clusters
Allows 2 pi steradian motion which allows
higher degrees of rotation than gimbaled
thruster clusters
Modeled after the CMGs on ISS
Linear scaling of mass and volume
Will be placed at the cm of each mass
ISS TH CW Cargo
(Largest)
Mass of
CMG
[kg]
390908 69.76
14.85 66.32
Volume
of CMG
[m3]
272.155 0.0311
0.0104 0.1744
4 thrusters on CW
4 thrusters on hab
By Jonathan Young
Spin-up takes place after escape from LEO
Analyzed 4 different methods of spin-up
Spin-up procedure chosen: › Lengthen to 174.4 m over 5 hours
› Tightening propellant = 110 kg
› Start spin-up from 0-1.7 rpm using 505 kg of propellant over 11 hours
› 2 thrusters total are used on CW and Hab for spin-up
› Shut off thrusters and winch in the tether to cause the system to spin up to
4 rpm over 5 hours.
› Spin up from 0-4 rpm takes place over 21 hours
› Burn time of 10 hours for each thruster
› Thrusters burn alternately
Winch system attached to CW with eject
mechanism
Tether
› Mass: 1.07t
By Kirk Maatman
174.4
One impulse burn to go from LEO to transfer
arc
A/C propellant budget for correction: › Requires about 6.3 t of propellant
› Using 8 AC-18 thrusters
› Alternately pulsing at 1 second intervals
› For about 57.1 hours
› To get a ∆V of 100m/s
Total Separation
› l = 391.3 m
Total propellant mass to re-dock
› mP = 55.5 t
Propellant reserved for de-spin of artificial gravity at Mars
› mP = 0.495 t
Conclusion:
› If the tether snaps, the propellant onboard to de-spin at Mars is
not sufficient to dock the hab and counterweight together.
› Tether break is a mission failure unless other measures are put into
place
Will be performed before LMO
De-spin will be achieved by firing the
thrusters in opposite direction of spin
Similar procedure for all Mars-bound human
missions
Prop mass needed for de spin = 496 kg
De-spin will take about 10 hours.
Waste materials ejected towards the end of
de-spin
› Crew A
winch in the TH towards the CW until they are x m apart.
Eject winch system as shown
Undock MDV
Move MDV in path shown and dock MDV to CW in prep for
landing
TH stays in orbit
By Rozaine
Wijekularatne
TH goes into LMO
By Rozaine
Wijekularatne
› Crew 1-7
No MDV
Winch CW and Hab together as close as possible and
eject winch system.
Rendezvous Hab with CW as shown for landing
By Rozaine
Wijekularatne
By Rozaine
Wijekularatne
Four thrusters on JY joints
One CMG
CMG at cm of cargo
Thrusters placed at 90 degree angles
CMG and 8 thrusters on TH used for
control of ERV
No propellant budget yet
EAV
Mass: 2.6 t
Volume: 12 m3
EDV
Mass: 2.6 t
Volume: 12 m3
Transit to Earth
Mass: 45.6 t
Volume: 145 m3
MAV
Mass: 2.6 t
Volume: 12 m3
TransHab in Orbit
Mass: 45.6 t
Volume: 145 m3
MDV
Mass: 4.6 t
Volume: 17 m3
Transit to Mars
Mass: 55.2 * t
Volume: 170* m3
Trans
HAB CW
*AG System Mass not included
Diagram by Stephanie Johnston
Cargo A
Mass: 47.7 t Volume: 207 m3
Trans HAB
Trans HAB
Does NOT include: General electronics & computers, and seats for crew capsules
* HF Considerations include: Food, water, breathable air, radiation shielding, greenhouse, appliances, equipment, maintenance, crew weights, daily consumables, thermal protection, recycling systems, etc.
Food Specs
Years #
People Mass
[t] Volume
[m3] % Self-
Sustaining
Actual Mass
Reduction Crew 1 -7 Launched
8 43.5 143.8 0% 0%
Crew 1 -7 Landed
8 34.0 0% 0%
Cargo 1 0.0 8 34.7 158.7 5-10% 0% Cargo 2 2.1 16 60.6 263.5 15-20% 10% Cargo 3 4.3 24 65.0 301.1 25-30% 20% Cargo 4 6.4 32 84.0 382.0 35-40% 25% Cargo 5 8.6 40 80.1 393.4 45-50% 40% Cargo 6 10.7 48 84.6 425.6 60-70% 50% Cargo 7 12.9 56 60.8 370.4 80-90% 75% Cargo 8 15.0 56 37.4 278.1 100% 90% Cargo 9 17.1 56 37.4 278.1 100% 90%
0.0
20.0
40.0
60.0
80.0
100.0
0.0 10.0 20.0
Ma
ss [
t]
Mission Years
Mass Requirements for
Cargo Missions 1-7
= Large Greenhouse
* Does NOT include: General electronics & computers
Radiation Shielded Room
Waste after 180 Days # of People and Days ==> 8 180 Mass Units Volume Units Mass [kg] Volume [m3] Waste Food 1.82 kg/p/d 0.008 m3/p/d 2620.8 11.52 WCS Supplies 0.05 kg/p/d 0.0013 m3/p/d 72 1.872 Collection bags 0.23 kg/p/d 0.0008 m3/p/d 331.2 1.152 Hygiene Consumables 0.075 kg/p/d 0.0015 m3/p/d 108 2.16 Disposable Wipes 0.025 kg/p/d 0.0005 m3/p/d 36 0.72 Trash Bags 0.05 kg/p/d 0.001 m3/p/d 72 1.44 Used Tape 0.041 kg/p/d 0.0002 m3/p/d 59.04 0.288 Medical Consumables 83.33333 kg 0.41667 m3 83.33 0.42 Water* 4.1 kg/p/d 5904 5.91 Air +Tanks (180 days) 232
TOTAL 9518.4 25.5 *Water 4.1 kg/p/d came from 15% waste water a day assuming crew uses 27.6 kg/p/d of water, this does not include a 40 day buffer where no water is recycled which is acting as a buffer for Crew A return mass/volume
Calculations and Table by Stephanie Johnston
Lights
Mass [kg] Volume [m^3] Power [W]
22 Units (1 Hab) 74.8 0.246539 660
Thermal Protection/System
Mass (kg) Volume (m^3) Power (W)
Heating 63.72 0.02 49,020 Cooling 280.8 0.1 258.58
Total +30% 447.876 0.156 64062.154
Calculations by Joubert Lucas; Table by Stephanie Johnston
Water Recovery System
› Transit Total Mass Consumed= 6403.2 kg
› Recovery Percentage=85%
› Total Mass of Life Support System=1906.4 kg
Air Revitalization Subsystem
› Transit Total Mass Consumed= 1440 kg
› Recovery Percentage=95%
› Total Mass of Life Support System=1013.8 kg
Waste Handling and Processing
› Total Mass=463 kg
Total Mass of ECLSS= 3.14t
Total Power of ECLSS= 6.4 kW
Total Volume of ECLSS= 13.64 From Ashley Davis’s Presentation (Section 1, Presentation 4)
Crew Transit Missions
Surface Area (m^2) Thickness (m) Arial Density
(g/cm^2) Weight (kg) (includes
30% Buffer) Volume (m^3) (based on 30%
buffered weight)
2.25 X 2 X 2m room 36.74 0.09 9.00 4298.71 4.48
Crew A Food 51.24 0.02 1.60 1065.89 1.11
Crew 1 Food 32.28 0.02 1.60 671.47 0.70
Cargo Missions (to protect food from radiation)
Surface Area (m^2) Thickness (m) Arial Density
(g/cm^2) Weight (kg) (includes
30% Buffer) Volume (m^3) (based on 30%
buffered weight)
Cargo A 76.76 0.02 1.60 1596.63 1.66
Cargo 1 90.31 0.02 1.60 1878.55 1.96
Cargo 2 129.65 0.02 1.60 2696.76 2.81
Cargo 3 158.28 0.02 1.60 3292.17 3.43
Cargo 4 172.52 0.02 1.60 3588.33 3.74
Cargo 5 179.42 0.02 1.60 3731.89 3.89
Cargo 6 157.37 0.02 1.60 3273.22 3.41
Cargo 7 109.77 0.02 1.60 2283.28 2.38
Cargo 8 (and after) 49.03 0.02 1.60 1019.83 1.06
*Assuming food (dehydrated, etc) is stored in cubed boxes **Used polyethylene, which has a density of 0.96 g/cm^3
Research by Joubert Lucas; Table by Stephanie Johnston
Reference Requirement
[kg/p/d]
Water (Rapp 2008) 27.6
Crew A Mission Transit Descent/Ascent Living on Mars Estimated Days 360 40 550
Mass Total H20 Consumption kg 79488 8832 121440
Percent H20 Recovered % 85 85
Mass H20 Needed to Bring with kg 11923.2 18216
Total Transit Mass of H20 to Mars kg 20755.2
Total Transit Volume of H20 to Mars m3 20.8 *Divide kg water by 998.2 for m^3
Total Cargo (Surface) Mass of H20 kg 18216.0
Total Cargo (Surface) Volume of H20 m3 18.2 *Assuming H20 is gathered In-Situ
Crew 1 Mission Transit to Mars Descent Living on Mars Estimated Days 180 20 550
Mass Total H20 Consumption kg 39744 4416 121440
Percent H20 Recovered % 85 85
Mass H20 Needed (Back-Up) kg 5961.6 18216
Total Transit Mass kg 10377.6
Total Transit Volume m3 10.4
Total Cargo (Surface) Mass kg 18216.0
Total Cargo (Surface) Volume m3 18.2 *Assuming H20 is gathered In-Situ
By Stephanie Johnston
Estimated Consumption
Reference Requirement (kg/day) Oxygen(Rapp 2008) 1
Crew Mission A: Crew Size 8
Crew A Mission Transit Recycled Days Not Recycled Living on Mars Estimated Days 360 40 550 MT kg 2880 320 4400 Rp % 95 95 MB kg 144 220 Total Transit Mass of 02 kg 464.0 Total Transit Volume of 02 m3 Density [kg/m^3] 1140.99 Total Cargo (Surface) Mass of 02 kg 220.0 Total Cargo (Surface) Volume of 02 m3 *Assuming O2 is gathered In-Situ
Crew Mission 1: Crew Size 8
Crew 1 Mission Transit Recycled Days Not Recycled Living on Mars Estimated Days 180 20 800 MT kg 1440 160 6400 Rp % 95 95 MB kg 72 320 Total Transit Mass of 02 kg 232.0 Total Transit Volume of 02 m3 Total Cargo (Surface) Mass of 02 kg 320.0 Total Cargo (Surface) Volume of 02 m3 *Assuming O2 is gathered In-Situ
By Stephanie Johnston
Tank O2: Crew A Days Crew Size Efficency Mb [kg] # of Tanks Radius [m] Length [m] Volume[m^3] Total Mass [kg] 360 8 85 432 9 0.6 2 28.5003 448.276 40 8 0 320 7 0.5 2.2 15.7605 331.5184 7 8 0 8.4 1 0.1 0.5 0.0199 8.5611
Crew 1 Days Crew Size Efficency Mb [kg] # of Tanks Radius [m] Length [m] Volume[m^3] Total Mass [kg] 180 8 85 216 4 0.6 2.2 13.5716 230.6739 20 8 0 160 3 0.6 2.2 10.1787 174.0702
Tank N2: Crew A Days Crew Size # of Tanks Radius [m] Length [m] Volume[m^3] Total Mass [kg] 360 8 2 0.5 2.5 4.9742 411.724 40 8 1 0.1 0.1 0.0073 19.4068 7 8 1 0.1 0.1 0.0073 19.4068
Crew 1 Days Crew Size Mb [kg] # of Tanks Radius [m] Length [m] Volume[m^3] Total Mass [kg] 180 8 18.72 1 0.5 2.5 2.4871 238.0567 20 8 2.08 1 0.1 0.1 0.0073 19.4068
Summary of Tank Mass/Volume:
Mass [kg]
Volume [m^3]
O2+ N2 for Crew A Transit 1210.93 49.24 O2+ N2 for Crew 1 Transit 662.21 26.24 O2+ N2 for Crew Capsule 27.97 0.0272
By Ashley Davis and Stephanie Johnston
Food Dry Food Consumed Earth food Emergency Food Greenhouse + Supplies Food Savings % Savings
Subtotal
Food Dry Food Consumed Earth food Emergency Food Greenhouse + Supplies Food Savings % Savings
Subtotal
First Cargo Second Cargo Third Cargo Fourth Cargo
8 800 16 800 24 800 32 800
Mass [kg]
Volume [m3]
Mass [kg]
Volume [m3]
Mass [kg]
Volume [m3]
Mass [kg]
Volume [m3]
14720.0 51.2 29440.0 102.4 44160.0 153.6 58880.0 204.8
15278.9 53.1 27199.8 94.6 35762.7 124.4 40967.6 142.5
1511.1 5.3 1679.0 5.8 3190.1 11.1 3358.0 11.7
11000.0 50.0 21000.0 80.0 11000.0 50.0 21000.0 80.0
10.0 0.0 4721.2 16.4 11447.2 39.7 22874.4 79.4
0.0 0.0 8.6 8.3 18.6 17.6 25.9 25.3
27790 108.4 49878.8 180.448 49952.8 185.488 65325.6 234.176
Fifth Cargo Sixth Cargo Seventh Cargo 8th, 9th, 10th…Etc 40 800 48 800 56 800 56 800
Mass [kg]
Volume [m3]
Mass [kg]
Volume [m3] Mass [kg]
Volume [m3] Mass [kg]
Volume [m3]
73600.0 256.0 88320.0 307.2 103040.0 358.4 103040.0 358.4 41975.0 146.0 32236.8 112.1 14103.6 49.1 0.0 0.0
5037.0 17.5 6380.2 22.2 8395.0 29.2 6720.0 23.4 11000.0 50.0 21000.0 80.0 11000.0 50.0 6000.0 30.0 36988.0 128.5 62183.0 216.1 95101.4 330.5 110880.0 385.4
38.9 37.6 51.1 50.2 74.0 72.0 89.7 87.8 58012 213.52 59617 214.32 33498.6 128.256 12720 53.36
Calculations by Lisa Kurtzhals and Spreadsheet by Stephanie Johnston
Nonstop Communication between Earth
and 8 Astronauts at all times
HDTV feed between each astronaut and
Earth
10 MBps of data from Earth to Mars
90 MBps of data from Mars to Earth
Min 7 ground stations on Earth
One Earth trailing satellite
Antennae on Crew Transfer Vehicle
Three Mars-orbiting satellites
One Mars ground station
Antennae on Rovers
Basic Transmission Antenna
Basic Reception Antenna
• One receiving dish and one
transmitting dish for each link
• Link Budget Analysis used to
size dish sizes and power
requirements to achieve
signal gain margin of >3 dB
• Parabolic dish design used for
all dishes
*CAD Drawings by Parthsarathi Trivedi
*Diagram by Parthsarathi Trivedi
35 deg.
θ
θ = 50o
φ = 155o
3 Satellites in Mars-Synchronous
Orbit
-17,031 km altitude
-25o inclination
MS3
MS2
MS1
φ
High-gain horn antenna: Single Antenna:
25 W Transmitting Power
0.84 kg Mass
0.011 m3 packing volume
Entire Network (200 Repeaters):
5 kW Transmission Power
168 kg Mass
2.21 m3 packing volume
Repeater Batteries:
9.39 kg per battery
1877 kg (200 batteries)
2.4 kWh (2 continuous days of
power)
Total System Mass:
11.07 kg per repeater unit
2048 kg total mass
Device Total Mass Total TransmissionPower
CTV Comm. 250 kg 180 W
TRAILSAT 500 kg 240 W
MS1 450 kg 1.38 kW
MS2 450 kg 1.38 kW
MS3 450 kg 1.38 kW
Surface Hab 4.2 kg 30 W
Rover-HD 4.2 kg 30 W
Rover-Audio 0.34 kg 55 W
Cave Network 2048 kg 5 kW
*Illustration by Parthsarathi Trivedi
CTV to Earth Link
Transmitting Dish Size 5.25 m
Receiving Dish Size 4 m
Propagation
Distance
1.745*109 m
Beamwidth 0.1 deg
Transmitting Power 180 W
Transmitting
Frequency
40 GHz
Bit Rate 754,974,720
bits/sec
Gain Margin 3.73 dB
TRAILSAT to Surface Link
Transmitting Dish Size 1.31 m
Receiving Dish Size 1.4 m
Propagation
Distance
175,627,910
km
Beamwidth 60 deg
Transmitting Power 60 W
Transmitting
Frequency
40 GHz
Bit Rate 754,974,720
bits/sec
Gain Margin 3.91 dB
TRAILSAT to Mars Link
Transmitting Dish Size 5.25 m
Receiving Dish Size 5.25 m
Propagation
Distance
1.75*109 km
Beamwidth 0.1 deg
Transmitting Power 180 W
Transmitting
Frequency
40 GHz
Bit Rate 335,544,320
bits/sec
Gain Margin 3.85 dB
MSO to Surface Link
Transmitting Dish Size 0.66 m
Receiving Dish Size 0.5 m
Propagation
Distance
18,000 km
Beamwidth 4 deg
Transmitting Power 1.2 kW
Transmitting
Frequency
8 GHz
Bit Rate 754,974,720
bits/sec
Gain Margin 3.05 dB
MSO to Earth Link
Transmitting Dish Size 5.25 m
Receiving Dish Size 4 m
Propagation
Distance
1.745*109 m
Beamwidth 0.1 deg
Transmitting Power 180 W
Transmitting
Frequency
40 GHz
Bit Rate 754,974,720
bits/sec
Gain Margin 3.73 dB
Rover to Rover Direct Communication
› Omnidirectional .86 m Antennae
› VHF Audio Transmission
› 160 MHz Signal Frequency
› 111 km Max. Range
› 55 W Transmission Power
Earth to Mars Link
Transmitting Dish Size 5.25 m
Receiving Dish Size 4 m
Propagation
Distance
1.75*109 km
Beamwidth 0.1 deg
Transmitting Power 180 W
Transmitting
Frequency
40 GHz
Bit Rate 335,544,320
bits/sec
Gain Margin 3.73 dB
Earth to TRAILSAT Link
Transmitting Dish Size 1.31 m
Receiving Dish Size 1.4 m
Propagation
Distance
175,627,910
km
Beamwidth 0.4 deg
Transmitting Power 180 W
Transmitting
Frequency
40 GHz
Bit Rate 335,544,320
bits/sec
Gain Margin 3.57 dB
Vehicle Breakdown
Configuration
Design
Crew A
Vehicle Breakdown
Configuration
Design
Crew 1-7
Vehicle Structural Mass [t]
Earth Ascent Vehicle / Mars
Descent Vehicle
5.7
Counter weight 21.97
Transit Hab 12.23
Cargo #1 8.21
Cargo #2 12.28
Cargo #3 8.21
Cargo #4 9.43
Mars Ascent Vehicle / Earth
Descent Vehicle
5 t
Total Dimensions
› 14 m Height + Capsule
› 10 m Diameter
Transit Hab › 6.5 m Height
Winch › 1 m Height
Counterweight › 6.5 m Height
Capsule › 6m Height
› 6m Diameter
Nellans
6 m
l-6m-l
6.5m
1m
6.5m
l--10m--l
14m
Nellans
Vehicle Structural mass [t]
Earth Ascent Vehicle 5.7
Tranist Hab 26.64
Counter Weight 21.97
Cargo Mission Structural Mass [t] Volume [m^3]
1 11.36 234.16
2 10.83 207.13
3 11.43 237.8
4 12.86 311.2
5 10.42 219.0
6 12.34 284.3
7 12.04 269.2
8 11.15 223.6
9 11.15 223.6
2 Transit Habs
2 Cargo Habs
2 Crews = 16 People
Inflatable Top
› 120 m^3 of space to
empty
Leg Mass
› 540 kg
Underbelly Mass
› 100 kg
Nellans
Mass of legs and bottom structure › Legs = 540 kg
› Bottom = 100 kg
Average additional space in each cargo mission is 315.72 m^3 over the 9 missions. Found by adding all the volumes and dividing by 9. › Means that there is 75 cubic meters of space
in the cargo missions that can be permanent space.
Total Rod Mass Total Truss Mass
Outer Panel Mass
Inner Panel Mass
Length [m]
Number of Rods
Cross Sectional Area [m²] Density [kg/m³] Single Truss [kg] 7.9515 Outer Surface Area [m²] 296.4
Inner Surface Area [m²] 212.1
2.25 48
0.0002271 4540
Number of Trusses 24 Al 6061-T6 Arial Density [kg/m²] 5.4 Total Mass [kg] 2889
3.827 24
Total Mass [kg] 190.8 Stuffing Arial Density [kg/m²] 8.5
4.439 16
Ti-662 Panel Thickness [m] 0.003
3.369 16
Ti-662 Density [kg/m³] 4540
0.985 16
Total Mass [kg] 8157
Total Mass [kg] 351.0
Total Structural Mass [t] 11.59
Zack Wallace Spreadsheet
4
Rovers A/C Engin
e Hover
Prop Hover
Inert Structur
e Food Greenhouse
+ Cleaning
Supplies Toilet WCS
Supplies Collection
Bags Hygiene
Consumables Clothe
s Disposable
Wipes Trash
Bags Extra
Hardware Radiation
Shielding
6 3 14.5 7.71 0.54 10.72 14.72 11.04 0.2 0.045 0.32 1.472 0.48 0.099 0.16 0.32 0.61369 5.37745
87.77128 45.30128
32 - 15 11.36 51.2 38.4 1.44 2.18 8.32 5.12 9.6 0.0336 3.2 6.4 3.74 5.60151
234.1656
Cargo Mission 1
Cargo Mission 2
2 Missions 3 Rovers A/C Engin
e Hover
Prop Hover
Inert Structur
e Food Greenhouse
+ Cleaning
Supplies Toilet WCS
Supplies Collection
Bags Hygiene
Consumables Clothe
s Disposable
Wipes Trash
Bags Extra
Hardware Radiation
Shielding
Mass (t) 4.5
3 14.5 6.45 0.448 10.19 13.25 5.52 0.2 0.045 0.32 1.472 0.48 0.0099 0.16 0.32 0.61369 3.978585 73.3653
3
Volume (m^3) 24
15 15 10.83 46.08 19.2 1.44 2.18 8.32 5.12 9.6 0.0336 3.2 6.4 3.74 4.14435 207.125
3
Kyle Hoos Spreadsheet
2 Missions 1
Rover A/C
E
n
g
i
n
e Hover Prop Hover
Inert Structure Food Greenhouse
+ Cleaning
Supplies Toilet WCS
Supplies Collection
Bags Hygiene
Consumables Clothe
s Disposable
Wipes Trash
Bags Extra
Hardware Radiation
Shielding
Mass (t) 1.5
3
1
4
.
5
7.892 0.5486 12.22 20.608 5.52 0.4 0.045 0.64 2.944 0.96 0.0198 0.32 0.64 1.227 5.29235
89.8616
Volume
(m^3) 8 -
1
5 12.86 71.68 19.2 2.88 2.18 16.64 10.24 19.2 0.0672 6.4 12.8 7.48 5.5649479
311.1718
Cargo Mission 4
2 Missions 3 Rovers A/C Engine Hover
Prop Hover Inert Structure Food Greenhouse
+ Cleaning
Supplies Toilet WCS
Supplies Collection
Bags Hygiene
Consumables Clothes Disposable
Wipes Trash
Bags Extra
Hardware Radiation
Shielding
Mass (t) 4.5
3 14.5 7.39 0.5136 10.79 17.66 5.52 0.3 0.045 0.48 2.208 0.72 0.01485 0.24 0.48 0.920535 4.8202375
84.13001
Volume
(m^3) 24
- 15 11.43 61.44 19.2 2.16 2.18 12.48 7.18 14.4 0.0504 4.8 9.6 5.61 5.02108
237.7879
Cargo Mission 3 Kyle Hoos Spreadsheet
Cargo Mission 5
Cargo Mission 6
2 Missions 1 Rover A/C Engine Hover
Prop Hover Inert Structure Food Greenhouse
+ Cleaning
Supplies Toilet WCS
Supplies Collection
Bags Hygiene
Consumables Clothes Disposable
Wipes Trash
Bags Extra
Hardware Radiation
Shielding
Mass (t) 4.5
3 14.5 7.9121 0.55 10.42 18.4 5.52 0.5 0.045 0.8 3.68 1.2 0.02475 0.4 0.8 1.534225 4.952675
90.09575
Volume
(m^3) 8
- 15 11.06 64 19.2 3.6 2.18 20.8 12.58 24 0.084 8 16 9.35 5.15903646
219.013
2 Missions 2
Rovers A/
C Engin
e Hover
Prop Hover
Inert Structur
e Food Greenhouse
+ Cleaning
Supplies Toilet WCS
Supplies Collection
Bags Hygiene
Consumables Clothe
s Disposable Wipes Trash
Bags Extra
Hardware Radiation
Shielding
Mass (t) 3
3 14.5 7.2663 0.5051 11.7 13.24
8 5.52 0.6 0.045 0.96 4.416 1.44 0.0297 0.48 0.96 1.22738 3.978585
82.7474
6
Volume
(m^3) 16
- 15 12.34 46.08 19.2 4.32 2.18 24.96 15.36 28.8 0.1008 9.6 19.2 11.44 4.144359375
284.340
7
Kyle Hoos Spreadsheet
Cargo Mission 7
2 Missions 2
Rovers A/
C Engine Hover
Prop Hover
Inert Structure Food Greenhouse
+ Cleaning
Supplies Toilet WCS
Supplies Collection
Bags Hygiene
Consumables Clothe
s Disposable
Wipes Trash
Bags Extra
Hardware Radiation
Shielding
Mass (t) 3
3 14.5
6.2859
0.5485 11.4 5.152 5.52 0.7 0.045 1.12 5.152 1.68 0.0345 0.56 1.12 2.147915 2.11965
71.69078
Volume
(m^3) 16
- 15 12.04 17.92 19.2 5.04 2.18 29.12 17.92 33.6 0.1176 11.2 22.4 13.09 2.20796875
269.2342
Cargo Mission 8
2 Missions A/C Engine Hover Prop Hover Inert Structure Food Greenhouse+ Cleaning Supplies WCS Supplies Collection Bags Hygiene Consumables Clothes Disposable Wipes Trash Bags Extra Hardware
Mass (t)
3 14.5 7.8898 0.5485 10.51
0 5.52 0.7 1.12 5.152 1.68 23.06666667 0.56 1.12 2.147915 89.83485617
Volume (m^3)
- 15 11.15
0 19.4 5.04 29.12 17.92 33.6 0.1176 11.2 22.4 13.09 223.60388
Cargo Mission 9
2 Missions A/C Engine Hover Prop Hover Inert Structure Food
Greenhouse+
Cleaning Supplies
WCS Supplies
Collection Bags
Hygiene Consumables Clothes
Disposable Wipes
Trash Bags
Extra Hardware
Mass (t)
3 14.5 7.8898 0.5485 10.51
0 5.52 0.7 1.12 5.152 1.68 23.0667 0.56 1.12 2.147915 89.83486
Volume (m^3)
- 15 11.15
0 19.4 5.04 29.12 17.92 33.6 0.1176 11.2 22.4 13.09 223.6039
Kyle Hoos Spreadsheet
Cargo A1 Cargo A2 Cargo A3 Cargo A4
HF/hardware 35
HF/Consume 0 0
Insitu Collect 2 0 0 Insitu Prop 1.5
0 0 0 EDV Cap 4.8
0 0 Comm 0
Rovers 6 0 0 0
43 6.3
mass =
7.5685 11.6359 7.5685 8.7922
mass_prop =
8.4788 8.4619 2.6234 9.1859
mass_inert =
0.5894 0.5883 0.1824 0.6386
>> MASS = mass + .54 + .1
MASS =
8.2085 12.2759 8.2085 9.4322
Taken From Kyle Hoos Code
5.848m
7.2
18
m
1.695
3.827m
Vstorage =
38.91905m^3
Vcommon =
116m^3
Melissa Young and Zack Wallace
V = 15m3
V = 15m3
V = 15m3
V = 15m3
Vstorage =
46.534086m^3
X2 floors =
93.068172 m^3
Melissa Young and Zack Wallace
Olympus Mons* › 226.3oE, 18.3oN
› Max elevation: 22 km
Arsia Mons › 238.9oE, 8.8oS
› Max elevation: 16 km
Pavonis Mons › 247.2oE, 1.2oN
› Max elevation: 14 km
Ascraeus Mons › 226.2oE, 18.3oN
› Max elevation: 18 km Mars Global Surveyor image
*
Dimensions for one Probe
› Mass: 0.4t
› Power: 13 KW*h
› Volume: 2.0m3
Sources
Two-stroke internal combustion engine
Solar Panels ( 0.698t)
Lithium Ion Battery (0.2t)
Hydraulic Pump
Heat Rejection System
Capabilities
› Up to ~3.0 m/s
› Navigate 60o incline
› Carrying 0.08t scientific instruments
Features
› Cameras: true color images, hand lens imager,
descent imager, navigation, hazard avoidance
› Rover Environmental Monitoring System
› Hydrogen, ice, water detector
› Radiation assessment
› Sample analysis
Illustration by Alaina Austin, Inspired by Boston Dynamics
Summary of different mechanisms
Final recommendation
› Mass
› Volume
› Power
Concept Elaboration by: Charles Miller
Airbags
Mass: .533t per hab
Volume: 302.64 m3 per hab
Not feasible
Hab is too heavy to implement airbag system
Hovering
› Fuel
Mass: 5.1t per hab
Volume: 4.15 m3 per hab
Need hovering landing gear (more mass)
Illustration by Alaina Austin
Mass: 0.804t
Volume: 0.273 m3
Proven, well understood
technology
Rough terrain may
make this infeasible
Will need either wings or
a propulsive force
Schematic and concept elaboration by Joubert Lucas
Use a winch to lower the Hab
Mass: 0.4t (winch without anchor)
Power: 2.5 – 3.4 KW
Limited mobility
Will only be successful if the correct site geometry found
Pros
› Re-usable
› Compatible with both cave geometries
Cons
› Hab requires large wheels or legs
› No clear method of guiding hab further into the lava tube
› Need to drill in order to anchor the winch
› Hab can be damaged during the lowering process due to
impact with cave walls
Schematic and concept elaboration by Parthsarathi Trivedi
Mass: 3.08 t
Power: 3 MW
Pros:
› Safe and slow descent
of hab into lava tube
Cons:
› Extremely high torque
about joints.
› Requires large hydraulic system.
› No lateral movement
into the cave Image and concept elaboration by Ajay Jakate
*Image not to scale
Schematic and Concept Elaboration by: Alaina Austin
200M1-A1-SA
2 front tracks
4 back tracks
Mass: 22.22t per hab
Volume: 4.54 m3 per hab
Limited mobility
Will only be successful if the
correct site geometry found
140
Mobile crane
Mass: 36.3t
Volume: 187.8 m3
Power: 167.8 kW
Pros
Can also be used for loading/unloading vehicles
Moving materials, and assembly/disassembly
Mass savings over a crawler type crane
Cons
Cons: may require some on site prep for stability.
Schematic and concept elaboration by Dan Jones
2 tracks Mass: 47.2t
Volume: 3.0 m3
Pros
› Can easily transport the hab to its final destination inside the lava tube
› Once set up, can be re-used for going in and out of the cave
› No power required for coming down due to friction force (length factor)
Cons
› Difficult to construct rail (pylons)
› Needs regular maintenance
Schematic by Parthsarathi Trivedi, Concept elaboration by: Rob Wallace
Spray hot water down hole to create 10 m wide level slope down lava tube.
Use winch to lower down
~547 days of crew time to set up
Water required › Bad case: 37500 m3
,37500t
› Better case: 10000 m3
or less 10,000 t or less
Require either shipping water or water acquisition operations
Image by Pat Rawlings
Image by Bill O’Neill
Hybrid of Boom Crane and Rail Line
30% Margin for deviation › Mass: 108.55t
› Volume: 248.04 m3 › Power: 167.8 kW
Pros: › One time mass delivery
› Crane can be useful tool for other operations
› Rail enables mobility over harsher terrain
› Used for geometry 1 or 2
› Re-usable (for both entry and exit from the cave)
› Requires minimal power
› Can easily guide the hab(s) into the lava tube
› Rails and supports easier to lay out on the flat floor of the lava tube
Figure by Parthsarathi Trivedi
Schematic by Parthsarathi Trivedi
Recommended