ryan scott week 7: march 1st, 2007
DESCRIPTION
Ryan Scott Week 7: March 1st, 2007. Updated as of 3/02/07. Power Group Leader TC, TV, dE, aM, dM, aE, CS1-2, CSM *This Week* Power Distribution on Martian Surface MLV Engine Selection Updated Communication Satellite Data. *Slides reviewed and/or edited by Kirk. MRCF. ISPP. HAB. NPS. - PowerPoint PPT PresentationTRANSCRIPT
3/1/2007 Ryan
AAE450 Senior Spacecraft Design
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Ryan ScottWeek 7: March 1st, 2007
Power Group LeaderTC, TV, dE, aM, dM, aE, CS1-2, CSM
*This Week*
Power Distribution on Martian Surface
MLV Engine Selection
Updated Communication Satellite Data
*Slides reviewed and/or edited by Kirk
Updated as of 3/02/07
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AAE450 Senior Spacecraft Design
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Martian Surface Power Distribution• Design Criteria
– MRCF• 126 kWe, 500 m
– ISPP• 1200 kWe, 6 m
– HAB• 100 kWe, 500 m
• Type of Wire?– Aluminum
– Copper
• Above or Below Ground Wiring?– Heat dissipation of Martian surface
– Heat dissipation of Martian atmosphere • Will Wire Reach too High of a
Temperature?– High current suspended
– Lower current buried
HAB
NPS
ISPP
MRCF
PMAD
• AC Results (Aluminum)– Power: 1426 kWe
– Mass: 15840 kg
– Volume 5.87 m^3
• DC Results (Al, not used)– Power: 1426 kWe
– Mass: 22520 kg
– Volume 8.36 m^3
*Follow-up Calculations Presented by Mike
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AAE450 Senior Spacecraft Design
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MLV Engine Selection• Design Criteria
– Thrust to weight ratio minimum 1.4
– 1 Fault tolerant design• Can NOT cause a detrimental
moment during fault• Ability to throttle down if no
fault• Ability to throttle up in event
of fault– Liquid hydrogen– Liquid oxygen– Area constraints
*More Detailed Analysis to be Introduced by Cat
• 5 Space Shuttle Main Engines– T(mass) = 17.97 mt (300 kg for excess piping)– T(Volume) = 4.267 m x 60 m^2– T(thrust) = 5 x 2090 kN = 10450 kN– T/W = 1.8-2.8 (on mars, 5 engines)– T/W = 1.4-1.7 (on mars, 3 engines)– Throttle Range
• 67% - 109%
SSME
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AAE450 Senior Spacecraft Design
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Backup Slides
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AAE450 Senior Spacecraft Design
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Martian Power Distribution
Next 9 slides show the results of the design for the power distribution of the Martian power grid
*note detailed calculations shown in Matlab code*
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*Power Distribution Factor Was found by Consulting Mike
Aluminum Wire AC Power Breakdown
AC DC HAB ISPP MRCF
Power 1426 1426 kWe Power 100 1200 126 kWe
Mass 15840 22520 kg Mass 4.864 0.0056 4.086 kg
Volume 5.87 8.36 m^3 Volume 0.5355 0.0018 0.4908 m^3
DC Power Breakdown
HAB ISPP MRCF
Power 100.00 1200.00 126.00 kWe
Mass 2664 304.5 3172 kg
Volume 0.99 0.14 1.17 m^3
Length 500 6 500 m
Area 1974 22560 2350 m^2
Area conversion factor mm^2 -> m^2
0.000001
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*Power Distribution Factor Was found by Consulting Mike
Copper Wire AC Power Breakdown
AC DC HAB ISPP MRCF
Power 1426 1426 kWe Power 100 1200 126 kWe
Mass 16400 36600 kg Mass 10.05 0.0116 8.442 kg
Volume 6.88 8.34 m^3 Volume 0.4235 0.0014 0.3881 m^3
DC Power Breakdown
HAB ISPP MRCF
Power 100 1200 126 kWe
Mass 10440 1003 8773 kg
Volume 1.17 0.11 0.99 m^3
Length 500 6 500 m
Area 2350 18800 1974 m^2
Area conversion factor mm^2 -> m^2
0.000001
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AAE450 Senior Spacecraft Design
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Data Considered When Choosing Operating Voltage
• Total mass– DC– AC
• Total Volume• Wire Temperature• Wire Location
Results of Matlab Code Given on Next 6 slides
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AAE450 Senior Spacecraft Design
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HAB, Above Ground – Two Wire AC
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AAE450 Senior Spacecraft Design
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HAB – Two Wire AC
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AAE450 Senior Spacecraft Design
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ISPP, Above Ground – Two Wire AC
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ISPP – Two Wire AC
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MRCF, Above Ground – Two Wire AC
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MRCF – Two Wire AC
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MLV Engine Selection
The next 2 slided show the calculations for choosing a MLV
engine
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AAE450 Senior Spacecraft Design
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MLV Engine• Engines Reviewed
– SSME– HM60/Vulcain– LE-7– RS-68– RL-10– CECE– RD0146
• Space Shuttle Main EngineMaximum Thrust:
(109% Power Level)
At Sea Level:In Vacuum:
418,000 lb512,300 lb
Throttle Range: 67% - 109%
Pressures: Hydrogen Pump Discharge:Oxygen Pump Discharge:Chamber Pressure:
6,276 psia
7,268 psi2,994 psia
Specific Impulse: (In Vacuum)
452 sec
Power: High Pressure Pumps
Hydrogen:Oxygen:
71,140 hp23,260 hp
Area Ratio: 69:1
Weight: 7,774 lb
Mixture Ratio: 6.03:1
Dimensions: 168 in. long 90 in. wide
Propellants: Fuel:Oxidizer:
Liquid HydrogenLiquid Oxygen
*Table recreated from www.pw.com
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AAE450 Senior Spacecraft Design
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MLV Calculations
98.0
2133000
evm
eaee AppvmF )(
eaee AppvmF )(
eaee AppvmF )(
mAe 39.2
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Satellite Update
The next slide shows the updated satellite information taken from the overview documents of the class
website on 2/28/07
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AAE450 Senior Spacecraft Design
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Satellite Update• CS1 x 2
– 16.75 kWe– 185.4 kg (Battery, Solar Panel,
Wires, Power Conditioning)– 189.8 m^2 by 0.127 m
• CSM x 5 (Solar Panels Same for GPS and CSM)– 2 kWe– 38.73 kg (Battery, Solar Panel,
Wires, Power Conditioning)– 22.66 m^2 by 0.127 m
*Picture Made by Steve
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New References
• 1 Pouliquen, M., “HM60 Cryogenic Rocket Engine for Future European Launchers,” AIAA Paper 346-353, Oct. 1983.
• 2 Rachuk, V. and Titkov, N., “The First Russian LOX-LH2 Expander Cycle LRE: RD0146,” AIAA Paper 1-15, July. 2006.
• 3 Wood, B., “Propulsion for the 21st Century—RS-68,” AIAA Paper 1-14, July 2002.• 4 Okita, K. & Fukushima, Y., “Improved LE-7 Engine,” AIAA Paper 1-6, July 1995.• 5 Burks, A., “DEVELOPMENT OF LOX-HYDROGEN ENGINES FOR THE SATURN
APOLLO LAUNCH VEHICLES,” AIAA Paper 1-12, June 1968.• 6 Sackheim, R., “Overview of United States Space Propulsion Technology and
Associated Space Transportation Systems,” AIAA Paper 1310-1333, Decmeber 2006.
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New References Continued• 7 Space Shuttle Main Engine. Retrieved February 25, 2007, from
http://www.boeing.com/defense-space/space/propul/SSME.html• 8 SSME. Retrieved February 25, 2007, from
http://www.pw.utc.com/vgn-ext-templating/v/index.jsp?vgnextrefresh=1&vgnextoid=75a0184c712de010VgnVCM100000c45a529fRCRD
• 9 Arian 5 – Specifications. Retrieved February , 2007, from http://www.spaceandtech.com/spacedata/elvs/ariane5_specs.shtml
• 10 LE-7 Specifications. Retrieved February 25, 2007, from http://www.spaceandtech.com/spacedata/engines/le7_specs.shtml
• 11 RS-68 Engine. Retrieved February, 2007, from http://www.boeing.com/defense-space/space/propul/RS68.html
• 12 RL10. Retrieved February, 2007, from http://www.pw.utc.com/vgn-ext-templating/v/index.jsp?vgnextrefresh=1&vgnextoid=eb6607b06f5eb010VgnVCM1000000881000aRCRD
• 13 CECE. Retrieved February, 2007, from http://www.pw.utc.com/vgn-ext-templating/v/index.jsp?vgnextrefresh=1&vgnextoid=91380e78738ee010VgnVCM100000c45a529fRCRD
• 14 RD-0146. Retrieved February, 2007, from http://www.pw.utc.com/vgn-ext-templating/v/index.jsp?vgnextrefresh=1&vgnextoid=e3b90030296eb010VgnVCM1000000881000aRCRD