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Ryan Scott Week 7: March 1st, 2007

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.

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Ryan Scott Week 7: March 1st, 2007

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  1. Ryan ScottWeek 7: March 1st, 2007 Updated as of 3/02/07 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 Ryan

  2. MRCF ISPP HAB NPS PMAD Martian Surface Power Distribution • AC Results (Aluminum) • Power:1426 kWe • Mass:15840 kg • Volume5.87 m^3 • DC Results (Al, not used) • Power:1426 kWe • Mass:22520 kg • Volume8.36 m^3 • 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 Ryan *Follow-up Calculations Presented by Mike

  3. 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 SSME MLV Engine Selection • 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% *More Detailed Analysis to be Introduced by Cat Ryan

  4. Backup Slides 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* Ryan

  6. *Power Distribution Factor Was found by Consulting Mike Ryan

  7. *Power Distribution Factor Was found by Consulting Mike 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 Ryan

  9. HAB, Above Ground – Two Wire AC Ryan

  10. HAB – Two Wire AC Ryan

  11. ISPP, Above Ground – Two Wire AC Ryan

  12. ISPP – Two Wire AC Ryan

  13. MRCF, Above Ground – Two Wire AC Ryan

  14. MRCF – Two Wire AC Ryan

  15. MLV Engine Selection The next 2 slided show the calculations for choosing a MLV engine Ryan

  16. MLV Engine • Space Shuttle Main Engine • Engines Reviewed • SSME • HM60/Vulcain • LE-7 • RS-68 • RL-10 • CECE • RD0146 *Table recreated from www.pw.com Ryan

  17. MLV Calculations 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 Ryan

  19. 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 Satellite Update *Picture Made by Steve 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. 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 • 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 Ryan

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