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2\22\2007
AAE450 Senior Spacecraft Design
Project Aquarius
Kowalkowski - 1
Mike KowalkowskiWeek 6: February 22nd 2007
Project Aquarius
Power Engineering Group
MRCF, LP, NPS Vehicle Focal
HAB, MLV, MR Power Contact
2\22\2007
AAE450 Senior Spacecraft Design
Project Aquarius
Kowalkowski - 2
EP / NPS Brayton Reactor Sizing• Conceptual Design
– Common 2 MWe, 10 year reactor for NPS & EP
– Surface reactor buried• Boron-aluminum bay & LiH / W
cap provide “safe” radiation dose at 6 m 4
– Closed Brayton Cycle (24%) conversion efficiency
• P / M / V – EP System– Power: 2 MWe capacity– Mass: 27.6 mta
– Radiation Area: 2270 m^2b
– Volume: 12600 m^3 (Rogge)• a includes a 20% budget1
• b includes a 10% budget1
Comp. Turb..
Shield
MarsGroundReactor
T.A.
PowerConditioner
MainRad.
2\22\2007
AAE450 Senior Spacecraft Design
Project Aquarius
Kowalkowski - 3
MRCF / LP Sizing• MRCF (Mars Rocket
Construction Facility):– Oversized mobile tent– Mass: 0.38 mt– Stowed Volume: 21.5 m^3– Power: 0.0 kWe
• Aluminum poles & nylon mass included
• Mobile system so rocket can be constructed on the launch pad.
• LP (Launch Pad):– Launch gantry only
• MLV Mass Lifted: 500 mt
• Power: 85 kWe– 5 minute lift time
• Highly dependent on finalized mass of MLV
– 1.0 km from HAB requires significant cabling mass at higher (1.0 MWe) power 6
• On the order of 1 mt• Ryan Scott developing code
MRCF Over LP25 m
50 m
2\22\2007
AAE450 Senior Spacecraft Design
Project Aquarius
Kowalkowski - 4
Backup Slides
Week 4 Readiness Level
2\22\2007
AAE450 Senior Spacecraft Design
Project Aquarius
Kowalkowski - 5
EP / NPS Reactor Sizing Logic (1)• Reactor mass
– Scaled from nuclear power fuel number with 3x shield provision
• 65 MWd/kg– Courtesy: Courtney Rogge 8
• 24% CBC cycle efficiency 9
• Additional masses baselined against documentation 1,2,3,9
– Surface reactors have higher power conditioning requirements, accounting for higher overall masses, but the fundamental reactor is the same
• Thermal radiator concept– Radiators are also aluminum
skin of the EP system and are deployable on the surface.
• Surface power conditioning and distribution– Masses and volumes not
entered into the reactor bed.• Shield analysis
– With a safety zone of 6 meters, the HAB will be placed 100 meters to 400 meters from the nuclear power source without significant risk
2\22\2007
AAE450 Senior Spacecraft Design
Project Aquarius
Kowalkowski - 6
EP / NPS Reactor Sizing Logic (2)
• Reactor Mass– 21.8% Total System
• Shield Mass– 20.5% Total System
• Turbo alternators– 16.6% Total System
• Thermal Radiators– 15.6% Total System
• Power Conditioning (Surface)– 13.5% Total System
• Heat Exchanger / Controller– 11.97% Total System
2\22\2007
AAE450 Senior Spacecraft Design
Project Aquarius
Kowalkowski - 7
EP / NPS Reactor Sizing Logic (2)• As has been previously recognized, shielding mass and
reactor mass have been difficult to size, primarily because of security classifications of referenced codes. After ~10 hours / day for four days of autonomous research and consultation with the nuclear engineering department, these numbers are shown to be embraced and accepted by current research.
• A purer, mathematically based code is being developed from the Sandia National Laboratory RSMASS-D reactor and shield sizing study 5, Auburn University’s Lunar electricity wiring study 6, and NASA’s Lunar power management and distribution guidelines 7. Although these mathematical models will add further integrity to the final mass and volume numbers, the overall system masses should not reduce or increase significantly from the numbers presented today. This mathematical model will serve as a check to the NPS literature sizing model presented today and should be complete by next week.
2\22\2007
AAE450 Senior Spacecraft Design
Project Aquarius
Kowalkowski - 8
System Mass Trends
2\22\2007
AAE450 Senior Spacecraft Design
Project Aquarius
Kowalkowski - 9
Specific System Power
2\22\2007
AAE450 Senior Spacecraft Design
Project Aquarius
Kowalkowski - 10
Calculations Sheet EP/NPS
• Reference full spreadsheet online under references.1,2,3,8
• Kowalkowski.xls … 8 pages
Power (kWe) Reactor Mass (kg) Shield Mass (kg) Turboalternators (kg) Power Conditioning (kg) Radiators (kg) Heat Exchanger (kg)20 364 315 210 240 276 240
54.4 800 800 500 800 500 010000 8540 8180 9650 1000 6600 920030000 26800 4250 15870 3000 42840 9300
Percentages 21.81% 20.54% 16.61% 13.48% 15.59% 11.97%
Power (kWe) Mass (kg) Radiator Area (m^2) Specific Mass (kg/kWe) Specific Radiator Area (m^2/kWe)20 1687 42 84.35 2.1
54.4 3400 400 62.5 7.352941176239.6 6301.48 402.528 26.3 1.68360.9 8336.79 544.959 23.1 1.51478.6 10577.06 770.546 22.1 1.61553.5 12177 940.95 22 1.7825.2 22610.48 1947.472 27.4 2.3610000 43170 4800 4.317 0.4830000 102060 12000 3.402 0.4
System Mass Assumed efficiency @ 24% 11.50270842 kg/kWe2000 23005.42 kg
120% 27606.50 kgInferred Mass (kg) Calculated Mass (kg) Discrepancy
Reactor Mass 6327.41 2673.99 Calculated only fuel + 3x fuel shieldShield Mass 5670.99 24% efficiencyTurboalternators 4585.01Power Conditioners 3720.94 Total Volume (Rogge)Radiators 4304.07 12587 m^3Heat Exchanger 3303.65Radiator Area (m^2) 2062.25110% Radiator Area (m^2) 2268.47Shield Mass comprised of Tungstun / Lithium Hydride alternating layers of shielding & B
Numbers & Breakdown Percentages From Albert Juhasz & Lee Mason, NASA GRC
2\22\2007
AAE450 Senior Spacecraft Design
Project Aquarius
Kowalkowski - 11
Calculations Sheet MRCF/LP
• Reference full spreadsheet online under references.• Kowalkowski.xls … 8 pages
Mass Nylon DensityAluminum Mass 105.4986 kg 12 kg/m^3Aluminum Volume 0.039074 m^3Nylon Mass 240 kg 4 mm thickNylon Volume 20 m^3 New York State Department of Transportation
Total Mass 380.0485 kg https://www.nysdot.gov/portal/page/portal/divisions/engineering/technical-services/technical-services-repository/alme/pages/310-1.html
Total Volume 21.04103 m^310% Mass budget
5% Volume budget
Nylon Aluminum DensitySide 1 25 2700 kg/m^3Side 2 25Side 3 50 length 25 m
inner radius 0.0495 marea 1 625 outer radius 0.05 marea 2 625 poles 10area 3 1250area 4 1250 total volume 0.039074area 5 1250 total mass 105.4986
total surface area 5000 m^2total volume 20 m^3total mass 240 kg
Mass MLV 500 mtEnergy to Lift MLV 25% 23276584 JConversion factor 3600000 J/kWhEnergy to Lift MLV 25% 6.465718 kWhPower to Lift in 5 minutes 77.58861 kWe
2\22\2007
AAE450 Senior Spacecraft Design
Project Aquarius
Kowalkowski - 12
Power Systems Trade Study• Thermoelectric vs. Sterling vs. Brayton 10
– Assume high temperature (2000K) Brayton Cycle 1
• Most efficient power cycle above 100kWe, blade and coating technology available
– Current power requirements on the surface• 1MWe ISPP / LP• 150 kWe HAB• With a 90% conditioning and distribution coefficient, 1.25
MWe– This could allow for a reduction of size in reactor, but I have been
told that ISPP fuel requirements may increase, increasing the total amount of fuel needed to near 1.5 MWe levels (Kassab)
– This is dependent on MLV mass
2\22\2007
AAE450 Senior Spacecraft Design
Project Aquarius
Kowalkowski - 13
Cited References• 1 Mason, Lee. A Comparison of Fission Power Systems Options for Lunar & Mars Surface
Applications. AIP - Space Technology and Applications International Forum, 2006. Available online.
• 2 Juhasz, Albert, et. al. Lunar Surface Gas Turbine Power Systems with Fission Reactor Heat Source. 3rd International Energy Conversion Engineering Conference, 2005. Available online.
• 3 Juhasz, Albert, et. al. Multimegawatt Gas Turbine Power Systems for Lunar Colonies. 4th International Energy Conversion Engineering Conference, 2006. Available online.
• 4 Wright, Steven A and David Poston. Low Mass Radiation Shielding for Martian Surface Power Reactors. AIP - Space Technology and Applications International Forum, 2002. Available online.
• 5 Marshall, Albert C. RSMASS-D: An Improved Method for Estimating Reactor Mass and Shield Mass for Space Reactor Applications. Sandia National Laboratories, 1997. Available Online.
• 6 Gordon, Lloyd B. Electrical Transmission on Lunar Surface: Part 1 – DC Transmission. Auburn University, Auburn, Alabama. March 2001. Available Online.
• 7 Metclaff, Kenneth J. Lunar PMAD Technology Assessment. NASA Lewis Research Center. Feb 1992. Available Online.
• 8 Courtney Rogge. Conversations with a Nuclear Engineer. 19 February 2007. Basic Reactor Fuel Mass and Volume Sizing.
• 9 Baggenstoss, W.G. and T.L. Ashe. “Mission Design Drivers for Closed Brayton Cycle Space Power Conversion Configuration.” Journal of Engineering for Gas Turbines and Power. October 1992, Vol. 114, pgs. 721-726.
• 10 Mason, Lee. A Comparison of Brayton and Sterling Space Nuclear Power Systems for Power Levels from 1 Kilowatt to 10 Megawatts. AIP - Space Technology and Applications International Forum, 2001. Available online.
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