1. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 1 Ryan Scott Week 7: March 1st, 2007 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 Updated as of 3/02/07

2. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 2 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:1426kWe –Mass: 15840kg –Volume5.87m^3 DC Results (Al, not used) –Power:1426kWe –Mass: 22520kg –Volume8.36m^3 *Follow-up Calculations Presented by Mike

3. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 3 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

4. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 4 Backup Slides

5. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 5 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*

6. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 6 *Power Distribution Factor Was found by Consulting Mike Aluminum WireAC Power Breakdown ACDC HABISPPMRCF Power1426 kWePower1001200126kWe Mass1584022520kgMass4.8640.00564.086kg Volume5.878.36m^3Volume0.53550.00180.4908m^3 DC Power Breakdown HABISPPMRCF Power100.001200.00126.00kWe Mass2664304.53172kg Volume0.990.141.17m^3 Length5006 m Area1974225602350m^2 Area conversion factor mm^2 -> m^2 0.000001

7. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 7 *Power Distribution Factor Was found by Consulting Mike Copper WireAC Power Breakdown ACDC HABISPPMRCF Power1426 kWePower1001200126kWe Mass1640036600kgMass10.050.01168.442kg Volume6.888.34m^3Volume0.42350.00140.3881m^3 DC Power Breakdown HABISPPMRCF Power1001200126kWe Mass1044010038773kg Volume1.170.110.99m^3 Length5006 m Area2350188001974m^2 Area conversion factor mm^2 -> m^2 0.000001

8. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 8 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

9. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 9 HAB, Above Ground – Two Wire AC

10. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 10 HAB – Two Wire AC

11. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 11 ISPP, Above Ground – Two Wire AC

12. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 12 ISPP – Two Wire AC

13. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 13 MRCF, Above Ground – Two Wire AC

14. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 14 MRCF – Two Wire AC

15. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 15 MLV Engine Selection The next 2 slided show the calculations for choosing a MLV engine

16. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 16 MLV Engine Engines Reviewed –SSME –HM60/Vulcain –LE-7 –RS-68 –RL-10 –CECE –RD0146 Space Shuttle Main Engine Maximum Thrust: (109% Power Level) At Sea Level: In Vacuum: 418,000 lb 512,300 lb Throttle Range:67% - 109%­ Pressures:Hydrogen Pump Discharge: Oxygen Pump Discharge: Chamber Pressure: 6,276 psia 7,268 psi 2,994 psia Specific Impulse: (In Vacuum) 452 sec­ Power: High Pressure Pumps Hydrogen: Oxygen: 71,140 hp 23,260 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 Hydrogen Liquid Oxygen *Table recreated from www.pw.com

17. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 17 MLV Calculations

18. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 18 Satellite Update The next slide shows the updated satellite information taken from the overview documents of the class website on 2/28/07

19. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 19 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

20. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 20 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.

21. AAE450 Senior Spacecraft Design 3/1/2007 Ryan 21 New References Continued 7 Space Shuttle Main Engine. Retrieved February 25, 2007, from http://www.boeing.com/defense-space/space/propul/SSME.html 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=75a0184c712de010VgnVCM100 000c45a529fRCRDhttp://www.pw.utc.com/vgn-ext- templating/v/index.jsp?vgnextrefresh=1&vgnextoid=75a0184c712de010VgnVCM100 000c45a529fRCRD 9 Arian 5 – Specifications. Retrieved February, 2007, from http://www.spaceandtech.com/spacedata/elvs/ariane5_specs.shtml 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 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.htmlhttp://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=eb6607b06f5eb010VgnVCM1000 000881000aRCRDhttp://www.pw.utc.com/vgn-ext- templating/v/index.jsp?vgnextrefresh=1&vgnextoid=eb6607b06f5eb010VgnVCM1000 000881000aRCRD 13 CECE. Retrieved February, 2007, from http://www.pw.utc.com/vgn-ext- templating/v/index.jsp?vgnextrefresh=1&vgnextoid=91380e78738ee010VgnVCM100 000c45a529fRCRDhttp://www.pw.utc.com/vgn-ext- templating/v/index.jsp?vgnextrefresh=1&vgnextoid=91380e78738ee010VgnVCM100 000c45a529fRCRD 14 RD-0146. Retrieved February, 2007, from http://www.pw.utc.com/vgn-ext- templating/v/index.jsp?vgnextrefresh=1&vgnextoid=e3b90030296eb010VgnVCM100 0000881000aRCRDhttp://www.pw.utc.com/vgn-ext- templating/v/index.jsp?vgnextrefresh=1&vgnextoid=e3b90030296eb010VgnVCM100 0000881000aRCRD