Transcript Document
1
Long-Duration Interplanetary
Spacecraft:
A Design Study
Ryan Haughey
Undergraduate
Dept. of Aerospace Engineering
Texas A&M University
2
Project Overview
Design project for aerospace engineering students in final year of
undergraduate program
Subgroups developed initial goals, which were later integrated into
a final spacecraft
Presented to board of industry and academic reviewers in Dec.
2012
3
Mission Statement
“To expand the domain of humanity beyond the earth for the
betterment, preservation, and advancement of all humankind by
creating a self-sustaining, mobile habitat that ensures the physical and
psychological well-being of its inhabitants.”
>24 Month Trip Time
12 Crew Members
Capable of Interplanetary Space Travel
4
What’s the Purpose?
Scientific
Advance the state of the art in diverse technological areas
Innovations for space usually have important terrestrial
applications
Economic
Mining of asteroids could yield many valuable materials
High demand for space tourism, research opportunities
Exploratory
Spark a new age of enthusiasm for the sciences
Inspire next generation of scientists and explorers
5
Ultimate goal
Attain economic viability and sustainability of the interplanetary
habitat through a range of revenue-generating activities, primarily
mining of asteroids
6
Design Drivers
Detailed Design
Competitive Advantages
Presentation Outline
7
Design Drivers
Detailed Design
Competitive Advantages
Presentation Outline
8
Design Goals
Elements of a viable system
Livability – Crew must be able to function, survive
Practicality – Magic solution will not appear, must deal with
proven feasibility of technology
Modularity – Assembly must be simple, repairs must be efficient,
expansion must be an option
9
Challenges of a Interplanetary
Space
Physiological
Physiological
Weightlessness
Livability
Radiation
Cost barriers to entry
Design Driver: Physiological Factors in Prolonged
Spaceflight
No human being has ever traveled into interplanetary
space
In 5 decades of manned spaceflight, our understanding of
physiological change during long duration missions
remains limited
Physiological impacts are significant and varied
During the course of a mission: 0-g effects (bone loss,
muscle loss, immune system impairment, etc.),
radiation exposure and immunological depression
Return to Earth: cardiovascular de-conditioning and
orthostatic intolerance
Both in-flight and post-flight physiological issues must be
countered
Design Driver: Countering 0-g Effects
There is no completely satisfactory approach to
countering 0-g effects aside from sustained artificial
gravity.
We do not know how much “g” is required to maintain
human health indefinitely (besides zero g = bad, and
one g = good)
We will not know the answer to this for a long time, since
long term experiments are required.
Therefore, in this design study, we require:
1 g artificial gravity.
Acceptable levels of Coriolis effects
Exposure to 1g almost all the time
Countermeasures – Artificial Gravity
1
To avoid motion sickness,
we must rotate below 4
rpm (while keeping the
rotation radius as small
as possible)
Onset of
motion
sickness
Comfort
zone
4 rpm
Artificial gravity
becomes more “normal”
with increasing radius
Physiological Factors Size and Rotation Rate
1 g artificial gravity and acceptable levels of
Coriolois forces motivate:
Rotation rate = 3.5 rpm
Rotation radius = 70m
(Thus max dimension can’t be less than 140m)
Exposure to 1g almost all the time means entire
s/c must rotate (a separate wheel with an
attached zero-g component is not practical)
Design Driver: Interplanetary Space Environment
High levels of radiation present in interplanetary space
Material must limit radiation exposure to levels on par
with ISS astronauts
Micrometeorite protection must also be included
Livable temperature must be maintained
Design Driver: Mass
Support needed to keep structure together
Launch costs are around $2,000 per pound of material
Standard trusses would add unnecessary mass;
alternative solution needed
The crew has to breathe!
2
Atmospheric composition
pO2
22.7 +/- 9 kPa
(170 +/- 10 mm Hg)
p(inert gas; most likely N2)
26.7 kPa
pCO2
< 0.4 kPa
pH2O
1.00 +/- 0.33 kPa
(7.5 +/- 2.5 mm Hg)
Total pressure = ½ atm
What Shape?
½ Atm pressurization & centrifugal loading Solids of
revolution are the most efficient pressure vessels
1
Sphere
Long cylinder
Large ratio of
pressurized
volume to useful
floor space
(projected area)
Axis of minimum inertia =
rotation axis
Energy dissipation results
in disruptive nutation
Active attitude control of this
= one more thing to go wrong
Torus
Minimum ratio of
pressurized volume to
useful floor space
Rotation axis = axis of
maximum inertia
Attitude is passively
stable
How Much Space Do People and Plants Need?
Space use
Surface area
required,
m2/person
No. of
levels
Projected
area, m2
Estimated
height, m
Volume,
m3/perso
n
Residential
49
4
12
3
147
Offices
1
3
0.33
4
4.0
Assembly rooms &
radiation storm shelter
1.5
1
1.5
10
15
Recreation and
entertainment
1
1
1
3
3
Storage
5
4
1
3.2
16
Mech. subsystem
Communication distr.
switching equipment
0.5
1
0.5
4
0.2
Waste and water treatment
and recycling
4
1
4
4
16
Electrical supply and
distribution
0.1
1
0.1
4
0.4
Miscellaneous
2.9
3
1
3.8
11.2
Subtotals
65.0
-
21.43
-
212.8
Agricultural space
(a) Plant growing areas
44
3
14.7
15
660
(b) Food processing
collection, storage, etc.
4
3
1.3
15
60
(c) Agricultural drying area
8
3
2.7
15
120
Totals
121.0
-
40.13
-
1052.8
Note: This is Table 3.2 of cited reference 2, but with several categories of space removed owing to the
limitations of a 12-person vessel. The spaces removed are: Shops, schools and hospitals, public open space
(500 m3) service industry space, transportation and animal areas.
Total Projected
area per
person
= 40 m2
Total Volume
per person
= 1050 m3
Is a Complete Torus Too Roomy?
1
z, zb
R
2r
y, yb
x, xb
With R=70m, r=5m and three “floors”:
Projected area ~ 10X2RX3 ~ 12,600 m2
Enough for 315 people! But we only need to
sustain 12 …..
Solution: Use only what you need!
• Modular pod configuration
• Attach modules as needed to support volume requirements
• Addressing new challenges
• Vibration damping using tensioned cables and compression
columns
• Natural frequencies causing motion sickness are avoided
• Capitalizing new advantages
• Engines may be placed along outer radius of structure
without interfering with livable area
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Mission Requirements
Minimize delta-v required for transportation
2-3 year mission duration
Solution
Constant thrust departure from LEO to Lagrange points
“Grand Tour” of interplanetary space in Earth – Sun system
Drift along energy boundary of Earth-Sun system with little to no
delta-v
Orbit cycle used by many asteroids, could allow for rendezvous
and mining
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Initial Deployment: Spiral out to E-M L1
1
Start in 300 km circular
orbit about Earth
Thrust always aligned
with the velocity vector
Full thrust up until 11
days and coasting to
L1 thereafter
Spiral out to a coasting
trajectory to the E-M L1
“throat”.
Meld into the Lyapunov
orbit of L1 Station and
refuel
385 103 km
Propellant mass: 21 MT
Trip duration: 5.6 months
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From E-M L1 to S-E L2: Start of the First Grand Tour
After refueling, leave L1
on the outward invariant
manifold.
Swing by the Moon and
exit the E-M L2 throat in
time to meld with a
heteroclinic orbit leading to
the Sun-Earth L2
Take one turn around the
Lyapunov orbit and enter the
external domain of the SunEarth system
L1 Lyapunov
Orbit
Moon
E-L1 to S-L2: V=12m/s, 50 days
Orbit of the
Moon
122,720 km
L1
Sun
Earth-Moon Frame
Sun-Earth Frame
L2
L2
1
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Asteroid Mining Tours: Exterior Realm
1
1.
Drop off cargo at L1 Station. Leave L1 Lyapunov orbit.
Follow heteroclinic orbit to L2 (pink line, left to right)
(drop off cargo at Earth-Moon system)
2.
Meld into L2 Lyapunov orbit, follow for ¾ of a period,
then follow the unstabile manifold (green line, heading
down)
L1
L2
3.0 million km
Sun-Earth Frame
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Through S-E L2 to the Grand Tour of the Exterior Realm
1
3. Follow the
homoclinic,
exterior domain
orbit (green path
issuing from L2
and going
clockwise)
Apophis
4. Mine Amors and
Apollos on the way
(3 years)
Then: see next
slide
Sun
3-2 resonance
1 AU
26
Heteroclinic Transfer Between Exterior and Interior Realms
1
5.
Follow homoclinic exterior domain orbit to L2 on the stable
manifold (green line, pointing down, left). Refurbish and
repair at L2 Station
6.
Meld into L2 Lyapunov orbit, follow for ½ of a period, then
follow the heteroclinic orbit to L1 (pink line, right to left).
L1
L2
3.0 million km
7.
Deliver cargo to Earth-Moon system. Meld into L1 Lyapunov
orbit, Exchange crew and refuel at L1 Station.
8.
Follow Lyapunov orbit for one period, then follow the
homoclinic interior domain orbit (blue line heading to the left).
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Through S-E L1 to the Grand Tour of the Interior Realm
1
Forbidden
zone
Apophis
9. Follow the
homoclinic, interior
domain orbit (red
path issuing from L1
and going counter
clockwise)
10. Mine Atens and
Apollos on the way
(two years)
Sun
3-2 resonance
11. Then follow the
stable manifold to L1
(blue line in previous
slide, heading to the
right).
12. Refuel and
exchange crew at L1
station.
Go to step 1 and
repeat.
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Design Drivers
Detailed Design
Competitive Advantages
Presentation Outline
29
System
Teams
Management
PM: Ryan Haughey
Assistant PM: Blaise Cole
Budget & Scheduling
Life
Support
Stress &
Thermal
System
Architecture
Power
Propulsion
30
System Overview – Architecture
Michael Pierce, Paola Alicea, Terry Huang, Luis Carrilo,
Christopher Roach, Mario Botros
Goal:
Synergize design concepts to meet functional requirements
Challenges:
Physiological: radiation, bone loss, air
Psychological: confinement, productivity
System stability
Management
Budget & Scheduling
Life
Support
Stress &
Thermal
System
Architecture
Power
Propulsion
Moment of Inertia Overview
z
15MT
x,y,z axes = Principal
axes of inertia
18MT
Ixx = 203,300 MT-m2
Iyy = 463,600 MT-m2
Izz = 641,300 MT-m2
23MT
Total Mass = 350MT
y
x
46MT
4MT
(total)
Izz is largest moment
of inertia; rigid body
nutation of the spin
axis due to energy
dissipation coupling
is suppressed
Architecture Overview
33
Inflatable Living Pod
Modeled on NASA Transhab study (Inflatable pod)
Nearly 2 dozen layers in 1-ft thick skin provide thermal, ballistic, and
radiation protection
Radiation Protection: conservatively 30 rem/yr (ISS is 50 rem/yr)
Ballistic Protection: Micrometeorite and Orbital Debris Shield
Each pod provides living space for four crew members
6m
32.5 m
8.4 m
10 m
13 m
Auxiliary pods
Identical to living pods
Low-gravity environment: sufficient to allow for proper survival by plants
One pod optimized for food growth, other for oxygen generation
35
Engine & Power Pods
Provides housing for power plant and engine
Power plant selected as nuclear reactor (further discussion later)
Shielding for nuclear reactor assists structure in deep space
radiation and micrometeorite protection
36
Water Ballast
Stores system water
Displace water along structure length to adjust
moments of inertia
Thermal management of water could be accomplished
using heat pipes from power source
High levels of redundancy needed to protect against
micrometeorite impacts on water column
37
Docking Module
Standardized module allows for docking of rendezvous craft
ISS PIRS module may serve as good model
Combination docking port and airlock
Image credit: NASA
38
Floor Space Summaries
Living Pod Summary
Agriculture Pod Summary
Floor Area per Pod (m2)
79.48
Floor Area per Pod (m2)
142.98
Number of Pods
4
Number of Pods
2
Number of Crew
12
Number of Crew
12
Floor Area per Person (m2)
26.49
Floor Area per Person (m2)
23.83
Stanford Study per Person
Requirement2 (m2)
19.83
Stanford Study per Person
Requirement2 (m2)
18.70
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System Summary – Architecture
Goal:
Synergize design concepts to meet functional requirements
Findings:
Modular, inflatable habitation pods
Water ballast
Locate power, engine away from
the axis of rotation
Management
Budget & Scheduling
Life
Support
Stress &
Thermal
System
Architecture
Power
Propulsion
40
System Overview – Life Support
Megan Heard, Sarah Atkinson, Mary Williamnson, Jacob Hollister,
Jorge Santana, Olga Rodionova, Erin Mastenbrook
Goal:
Create an environment conducive to healthy human functions
with minimal re-supply for duration of mission
Challenges:
Crew nutrition & health
Water recycling & distribution
Waste Management
Oxygen regeneration
Management
Budget & Scheduling
Life
Support
Stress &
Thermal
System
Architecture
Power
Propulsion
41
Crew Nutrition
Modeled on diet of residents of Greek island of Ikaria, noted for
exceptional health and longevity
For missions past 21 months, more practical to self-sustain food
Some portions of diet require bringing food along (meats, oils)
Proposed solutions:
Aeroponically grow food in low-gravity agriculture pods
Maintain cold storage for stowed perishable food
Image credit: Tower Garden
42
Nutrition Logistics
Aeroponics Farming: Tower Gardens
Stored Farming (12 people, 2 years)
Height (m)
1.83
Total Stored Mass (kg)
8165
Base (m2)
0.58
Total Stored Volume (m3)
13
Number of Towers
12
Plants per Tower
28
Max Plant Output
336
Stored food consists of all which can
not be grown in tower gardens.
Includes: meats, grains, sugars, salts,
& milk
Aeroponics Farming: Shelf
Total Area (m2)
6.69
Tower gardens used to grow range of
fruits, vegetables, and herbs.
Shelf used to grow potatoes
Combination of produce and stored
food allow for full sustainment of crew
for around 3 years
43
Water Treatment
Must handle waste-water and gray-water
Prevent disease development
Effective water recycling becomes advantageous after 0.5 months
Proposed solution
Utilize ECLSS system currently in place on ISS (~95% efficient)
Mass (kg)
Volume (m3)
Power (kW)
Water for Humans:
5100
5.1
N/A
Water for Algae:
7920
7.92
N/A
Water for Agriculture:
1514
1.514
N/A
ECLSS Water Recycling
System
(2 units):
Total:
1782
6.51
4.42
Water Summary
14801.87
18.81
4.42
44
Waste Management
Isolation of outpost requires full effective recycling
Human waste can serve as effective crop fertilizers, reducing need
for artificial fertilization (added mass)
Proposed solutions
Closed-loop system with high-efficiency composters & ECLSS
water filtration system
Tie-in to agriculture system for fertilization
45
Waste Summary
Solid Waste Mitigation Summary
Solid Waste Production (kg/person/day)3
Number of Crew
Daily Waste Production (kg/day)
Waste Processor Performance
(kg/unit/day)4
Liquid Waste Migitation Summary
0.2
Liquid Waste Production
(l/person/day)5
2
12
2.4
Gray Water Production
(l/person/day)6
19
Number of Crew
12
0.43
Daily Waste Production (l/day)
252
4.3
Water Processor Performance
(l/unit/day)7
140
1.9
Number of Processors
2
Waste Capacity (l/day)
280
Number of Processors
10
Waste Capacity (kg/day)
Excess Waste Handling (kg/day)
Excess Waste Handling (l/day)
28
46
Oxygen Regeneration
Standard CO2 scrubbing and Oxygen Generation Systems consume
water in production of oxygen
After 21 months, a closed-loop system becomes more efficient
Proposed solution
Convert CO2 into O2 using green algae (Spirulina) tanks
Mechanically filter other impurities
Back-up system (in case of disease or catastrophic failure) would
be standard OGS/C02 scrubber similar to ISS
Image Credit: California State University – Long Beach
47
System Summary – Life Support
Goal:
Create an environment conducive to healthy human functions
with minimal re-supply for duration of mission
Findings:
High-nutrition, efficient diet
Recycle, grow as much as possible
Multipurpose systems
Management
Budget & Scheduling
Life
Support
Waste used as fertilizer
Stress &
Thermal
System
Architecture
Power
Propulsion
48
System Overview – Stress & Thermal
Alex Herring, Brendon Baker, Scott Motl, Keegan Colbert,
James Wallace, Travis Ravenscroft
Goal:
Develop a stable structure capable of withstanding loading
profile
Challenges:
Management
Rotational Loading & Rigidity
Truss design
Budget & Scheduling
Vibration Mitigation
Cable design and placement
Life
Support
Thermal Environment Management
Stress &
Thermal
System
Architecture
Power
Propulsion
49
Minimum Breaking Load (N)
Structural Layout: Tensioned Cable
300000
250000
200000
150000
100000
50000
0
0
0.005
0.01
0.015
Cable Diameter (m)
Cables connect pods in rotation plane to central column
Transfers centrifugal loads from rotation plane
Significantly reduces need for trusses, total structure mass
Manages vibration propagation
Total compressive force: 782 kN
Vibration mitigation drives cable size
0.02
50
Why such a complicated design?
Another structural configuration: “Bola”
Habitation areas connected by cable in rotation
Suited to small structures, with few crew members
Scale, mass of current structure would cause serious vibration
problems
Tensioned cable with column gives structural rigidity in all 6 rigid
body DOFs
Additional benefits
Thrust located off the spin axis
More maneuverable, allows for easier docking
Much more expandable
Pods can be more easily located at intermediate points in structure
51
Structural Rigidity
Trusses needed to maintain craft’s shape, operate in
case of no centrifugal loading (much lower loads)
Dimensions of structure require advanced materials
to minimize weight
Proposed solutions:
Composite (carbon-fibre) truss structure
Outer connecting tubes enclose truss, prevents
outgassing & radiation degradation of composite
52
Vibration Mitigation
Torus has been segmented, resulting in vibration instability
Cable dimension driven by vibration mitigation, not centrifugal
loading
Failing to address vibrations could result in structure shaking itself
apart
Augment tension cables to mitigate vibration in other planes
Avoid natural frequencies which induce motion sickness (0.05 – 0.8
Hz), 8 Hz (need more detailed model to address)
Cable Sizing Summary
X-translation mode minimum size (cm)
2
Y-translation mode minimum size (cm)
0.8
X-rotation mode minimum size (cm)
0.8
53
Thermal Management
Nuclear reactor will produce large amounts of waste heat
Near constant exposure to solar radiation once in deep space
Simple white exterior to living pods renders a temperature on order
of -60oF
Proposed solution
Black/white surface coating combination (43% white, 57% black)
passively raises temperature to comfortable levels
Radiator of around 200 m2 sized using Idaho National Labs
CERMET study (design basis for nuclear reactor)10
Heat pipes convey additional heat throughout structure to utilize
as needed
54
System Summary – Stress & Thermal
Goal:
Develop a stable structure capable of withstanding loading
profile
Findings:
Management
Tensioned-cable structure reduces
truss mass, vibration
Budget & Scheduling
Passive cooling can accomplish
thermal control, with minor support
Life
Support
Stress &
Thermal
System
Architecture
Power
Propulsion
55
System Overview – Propulsion
Kyle Monsma, Benjamin Morales, Carl Runco, Paul Schattenberg,
Mark Baker, Steven Swearingen
Goal:
Provide sufficient thrust to transport space craft into
interplanetary travel
Challenges:
Management
Mission duration
Long-duration thrust development
Budget & Scheduling
Attitude control
Life
Support
Stress &
Thermal
System
Architecture
Power
Propulsion
56
Engine Selection
Continuous thrust system is most practical
Electrodeless Lorentz Force (ELF) thrusters are emerging as
(relatively) high thrust, high Isp engine at a low weight & size
Engine Comparison
ELF8
VASIMR9
Engine Mass (MT)
3.8
7.6
Thrust (N)
66.5
47.5
Fuel Mass (% total)
8.74
7.84
Burn Time (days)
279
389
57
ELF Operation & Fuel
Image credit: University of Washington,
Dept. of Aerospace Engineering
Xe
5.894
3.057
1,839
Kr
3.749
2.413
2,891
Xeon provides maximum
efficiency
Xeon has greater compatibility
with existing spacecraft
technologies
58
Spin-up & Attitude Control
Need to attain 3.5 RPM for 1g conditions in given craft
Engines are mounted on edge of rotation plane, allowing gimballing
to combine spin and forward propulsion
Proposed solution:
During transit to Lagrange point, angle both engines to produce
rotation
CMGs could also be used to provide heading maintenance
59
Spin-Up Detail
Properties Summary
Total Mass (MT)
350
Principle Moment of Inertia (kg
m2)
6.63 E8
Required Angular Velocity (rpm)
3.5
Moment Arm (m)
70
Angle & Burn Time vs. Thrust
50
45
40
35
30
25
20
15
10
5
0
Angle (Degrees)
Burn Time (Days)
0
10
20
30
Thrust (N)
40
50
60
60
System Summary – Propulsion
Goal:
Provide sufficient thrust to transport space craft into
interplanetary travel
Findings:
Management
Low thrust, high-Isp engine (ELF)
Xeon fuel
Budget & Scheduling
Deflect engines to obtain spin
Life
Support
Stress &
Thermal
System
Architecture
Power
Propulsion
61
System Overview – Power
Collin Marshall, Andrew Tucker, Carl Mullins, Jack Reagan, Colby
Smith, Andrew Nguyen
Goal:
Provide reliable electrical power to meet spacecraft systems
requirements
Challenges:
Management
High power requirements by engines
Mass, size constraints
Budget & Scheduling
Radiation management
System redundancy
Life
Support
Stress &
Thermal
System
Architecture
Power
Propulsion
62
Powerplant
Estimated power requirements around 2
MWe
Solar array would be prohibitively large and
expensive
INL CERMET study demonstrated conceptual
feasibility of space nuclear reactors of this
rating10
Emergency power must be available for
sustaining limited life support functions in
event of outage
Power distributed using similar system to ISS
Image credit (modified):
Boeing Defense, Space &
Security
63
Reactor Core
2 separate reactors placed on opposite arms of ship
Each reactor supports minimum power requirements
Location near engine reduces transmission cable mass
Passively stable with active control rods
Allows for variable power output
Conserves fuel and reduces overall mass
64
Shielding & Power Generation
Be-W-LiH Layered Shielding covers broad spectrum protection
Required thickness: 0.28m; mass of 1,450 kg per reactor
Shadow shielding – Only shield craft needing protection
To center of craft
Power generated with standard Brayton cycle
High efficiency due to near 0K heat sink
Helium is working fluid
No regeneration
Each reactor-turbine combination produces
1.5 MWe
Heat pipes circulate waste heat around structure
Note: Cut-away view,
shield is
hemispherical
65
Power Conversion
Power Conversion Specifications10
Turbine Inlet Temperature (K)
1500
Pressure Ratio
15
Specific Mass (kg/kWe)
7.67
Total Mass (kg)
23,000
Efficiency
52%
Total thermal output (kWt)
5770
Total electrical output (kWe)
3000
Total waste heat (kWt)
2770
66
Emergency Power
Solar panels capable of providing minimum life-support functionality
paired with each pod
Back-up OGS system & heating will require 20 kW
Solar Panel Array Specifications
Panel Efficiency11
0.29
Panel Area per Pod (m2)
16.7
Panel Mass per Pod (kg)
176
67
System Summary – Power
Goal:
Provide reliable electrical power to meet spacecraft systems
requirements
Findings:
Management
Dynamic cycle power generation
Nuclear reaction heat production
Budget & Scheduling
Solar panels provide back up power
Life
Support
Stress &
Thermal
System
Architecture
Power
Propulsion
68
System Overview – Budget & Scheduling
Blaise Cole, Kevin Davenport, Lisa Warren
Goal:
Track the mass, power, and monetary requirements for the
system, and prepare a feasible deployment plan
Challenges:
Management
Developing funding structure
Creating deployment schedule
Budget & Scheduling
Life
Support
Stress &
Thermal
System
Architecture
Power
Propulsion
69
Systems Overview
System
Mass (MT)
System
Power (MW)
Architecture
235.4
Architecture
0.35
Structure
7.0
Propulsion
1.9
Propulsion
40.8
Life Support
0.3
Power
28.3
Power Required
2.56
Life Support
34.9
Total
346.4
Power Produced 3.02
70
Funding
Program would have extremely high costs for full integration
Significant levels of government support would be unlikely,
undesirable due to loss of control
Very risky nature of project would make significant levels of debt
unattainable, equity can lose direction
Proposed solution:
Use bootstrapping plan: start developing core components of craft
with terrestrial applications; provides revenue stream while
supporting further R&D of technology
Develop LEO research, tourism platform for further partnerships &
revenue streams
71
Deployment
Significant number of launches would be required to deploy full craft
Assembling at Lagrange point would be extremely difficult and
impractical
Proposed solution:
Assemble the structure in LEO, use as platform for research and
tourism
After built, transfer to Lagrange point (while unmanned)
Crew rendezvous with craft at Lagrange point, mission starts at
this point
72
Design Drivers
Detailed Design
Summary
Presentation Outline
73
Design Goals
Livability
Artificial gravity, radiation shielding, diet ensure long-term health
Internal architecture provides psychological comfort
Practicality
All technology grounded in present or near-future developments
Modularity
Assembly, repairs simple due to common pod
Can incrementally grow station by adding modular pods
Potentially attain full torus
74
Potential Applications
Asteroid mining (would need further development of additional
spacecraft for use in mining)
Space tourism (deep space or near-earth)
Debris removal and recycling
Scientific research platform
Permanent space station at Lagrange point
75
Acknowledgements
Dr. David Hyland
Department of Aerospace Engineering, Dwight Look College of
Engineering, Texas A&M University
The Fall 2012 AERO 426 team leaders and team members
76
Sources
1
Hyland, David, “Class Lectures,” AERO 426, Texas A&M University, Fall 2012.
2 R.D.
Johnson, C Holbrow, editors, Space Settlements: A Design Study, NASA, SP-413, Scientific and Technical.
3
“Feces,” Encyclopedia Brittanica Online Edition, 2013.
4
Oshima, T., Moriya, T., Kanazawa, S., Yamashita, M., “Proposal of Hyperthermophilic Aerobic Composting Bacteria and Their Enzymes in
Space Agriculture,” Biological Sciences in Space, Vol. 21 No.4, 2007.
5 “Urinalysis,”
Mercer University School of Medicine. 1994-2012 [http://library.med.utah.edu/WebPath/webpath.html#MENU].
6
Johnson, David, “Graywater Treatment and Graywater Soil Absorption System Designs for Camps and Other Facilities,” Alaska Department
of Environmental Conservation, May 2005.
7
Beasley, Dolores, “NASA Advances Water Recycling for Space Travel and Earth Use,” NASA News, Nov. 2004
8 Slough,
J., Kirtley, D., Weber, T., “Pulsed Plasmoid Propulsion: The ELF Thruster,” 31st International Electric Propulsion Conference. Sept.
2009.
9 Ad
10
Astra Rocket Company, Company Website, 2009-2013, [http://www.adastrarocket.com/aarc/VX200].
Webb, J. A., Gross, B. J., “A Conceptual Multi-Megawatt System Based on a Tungsten CERMET Reactor,” Nuclear and Emerging
Technologies for Space 2011, Idaho National Laboratory, Feb. 2011.
11 Gaddy,
Edward M., "Cost performance of multi-junction, gallium arsenide, and silicon solar cells on spacecraft," Photovoltaic Specialists
Conference, 1996., Conference Record of the Twenty Fifth IEEE, IEEE, 1996.
77
Thank you very much for your time!
Questions?