Cost - Benefit analysis of the aerocapture mission set

39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Volumn , Issue , 2003, Pages

  Hall, Jeffery L ^a   Noca, Muriel A ^a   Bailey, Robert W ^a  

^a CALIFORNIA INSTITUTE OF TECHNOLOGY   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AEROCAPTURE MISSION; BENEFIT ANALYSIS; BETTER PERFORMANCE; CHEMICAL PROPULSION; ELLIPTICAL ORBITS; ORBIT INSERTION; SOLAR ELECTRIC PROPULSION; VAN ALLEN RADIATION BELTS;

AEROASSIST; AEROSPACE APPLICATIONS; COST BENEFIT ANALYSIS; COSTS; INTERPLANETARY FLIGHT; IONIZING RADIATION; PROPULSION; SPACECRAFT;

AEROBRAKING;

EID: 84897747256     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

References (22)

1. M. I. Cruz, "The Aerocapture Vehicle Mission Design Concept, " AIAA Paper 79-0893 presented at the Conference on Advanced Technology for Future Space Systems, Hampton, VA, May 8-10, 1979.
2. Gerald D. Walberg, "A Survey of Aeroassisted Orbit Transfer", Journal of Spacecraft and Rockets, Vol. 22, No. 1, 1985.
3. W. H. Willcockson, "Mars Aerocapture Using Continuous Roll Techniques", AAS Paper 91-422, Proceedings of the AAS/AIAA Astrodynamics Conference, Durango, CO, Aug. 19-22, 1991.
4. P.F. Wecinski, W. Henline, H. Tran, F. Milos, P. Papadopolous, Y.-K. Chen, and E. Venkatapathy, "Trajectory, Aerothermal Conditions and Thermal Protection System Mass for The Mars 2001 Aerocapture Mission", AIAA Paper 97-0472, presented at the 35th Aerospace Sciences Meeting, Reno, NV, January 6-10, 1997.
5. Jeffery L. Hall, "An Overview of the Aerocapture Flight Test Experiment (AFTE)", AIAA Paper 2002-4621, AIAA Atmospheric Flight Mechanics Conference and Exhibit, Monterey, CA., Aug. 5-8, 2002.
6. Stephane Rousseau, Etienne Perot, Claude Graves, James P. Masciarelli, and Eric Queen, "Aerocapture Guidance Algorithm Comparison Campaign", AIAA Paper 2002-4822, presented at the AIAA/AAS Astrodynamics Specialist Conference and Exhibit, Monterey CA, August 5-8, 2002.
7. M. K. Lockwood, "Titan Aerocapture Systems Analysis", AIAA Paper 2003-4799, presented at the 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Huntsville, AB, July 20-23, 2003.
8. Bonnie James and Michelle Munk, "Aerocapture Technology Development Within the NASA In-Space Propulsion Program", AIAA Paper 2003-4654, 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Huntsville, AB, July 20-23, 2003.
9. National Academy of Science, Solar System Exploration "Decadal" Survey, July 2002. http://www7.nationalacademies.org/ssb/SSE_Survey_R eport_Part_1.pdf and http://www7.nationalacademies.org/ssb/SSE_Survey_R eport_Part_2.pdf 10http://elvperf.ksc.nasa.gov/elvMap/staticPages/launch _vehicle_info1.html
10. M. D. Rayman, "Results from the Deep Space 1 Technology Validation Mission, " IAA-99-IAA.11.2.01, 50th International Astronautical Congress, October 4-8, 1999, Amsterdam, The Netherlands.
11. J. E. Polk, et al., "In-Flight Performance of the NSTAR Ion Thruster Technology on the Deep Space One Mission, " AIAA-99-2274, presented at the 35th AIAA/ASME/SAE/ASII Joint Propulsion Conference, June 21-23, 1999.
12. J. A. Christensen, et al., "The NSTAR Ion Propulsion System for DS1, " AIAA-99-2972, presented at the 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Los Angeles, CA, June 1999.
13. M. J. Patterson, et al., "Next-Generation 5/10 kW Ion Propulsion Development Status, " IEPC-01-089, 27th International Electric Propulsion Conference, Pasadena, CA, October 15-19, 2001.
14. M. J. Patterson, et al., "NEXT: NASA's Evolutionary Xenon Thruster, " AIAA-2002-3832, presented at the 38th AIAA/ASME/SAE/ASII Joint Propulsion Conference, July 7-10, 2002, Indianapolis, IN.
15. S. Oleson, et al., "Mission Advantages of NEXT: NASA's Evolutionary Xenon Thruster, " AIAA-2002-3969, presented at the 38th AIAA/ASME/SAE/ASII Joint Propulsion Conference, July 7-10, 2002, Indianapolis, IN.
16. The assumed value of 370s is somewhat higher than currently identified systems but is intended to represent a "best-case" long-term performance goal.
17. Projected specific impulse of the NeXT ion engine under development by Glenn Research Center. (c.f. Refs. 14, 15, and 16.)
18. NASA, "New Frontiers AO, ELV Launch Services Information Summary 02/25/03", page 4, 2003, http://centauri.larc.nasa.gov/newfrontiers/AONew_ Frontiers-ELV_Info_S_1.pdf
19. JPL, February 2003. Unpublished estimate that a Cassini bipropellent system rebuild (500 kg dry mass) would cost $40M. The cost model gives 2 +1.7 x 5000.5 = $40M.
20. John R. Brophy, private communication, February 2003. He estimated that a 25 kw, 800 kg dry mass SEP system based on advanced NSTAR technology from DS-1 would cost $63M. The cost model gives 40+0.8 x 8000.5 = $63M.
21. Robert A. Mase, private communication. Mars Odyssey data indicates that aerobraking for the 600 kg spacecraft had a cost of $9.3M including planning, development, operations and science team during the 3 month aerobraking period. The cost model gives 5 + 0.2 x 6000.5 = $9.9M.
22. Jeffery L. Hall, unpublished data from the design described in Ref. 5. The estimated cost of the AFTE aerocapture system was $12.8M including the design, analysis, simulation, aeroshell fabrication, system integration, and testing. Since the AFTE aeroshell was approximately 50 kg, the model gives 7 + 0.8 x 500.5 = $12.7M.