A reusable space vehicle design study exploring sharp leading edges

35th AIAA Thermophysics Conference

Volumn , Issue , 2001, Pages

  Reuther, James ^a   Kinney, David ^a   Smith, Stephen ^a   Kontinos, Dean ^a   Gage, Peter ^b   Saunders, David ^b  

^a NASA AMES RESEARCH CENTER   (United States)

^b FLORET Inc   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

SPACE STATIONS; VEHICLE PERFORMANCE;

CREW TRANSFER VEHICLES; DESIGN CAPABILITY; HEATING CONDITIONS; HIGH FIDELITY ANALYSIS; INTERNATIONAL SPACE STATIONS; MISSION CAPABILITY; SHARP LEADING EDGES; ULTRA-HIGH-TEMPERATURE CERAMICS;

CURRICULA;

EID: 85086491090     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: 10.2514/6.2001-2884     Document Type: Conference Paper

References (16)

1. Kolodziej, P., Bowles, J. and Roberts, C., "Optimizing Hypersonic Sharp Body Concepts from a Thermal Protection System Perspective," AIAA Paper 98-1610, 1998.
2. Stone, H.W., Piland, W.M., "21st Century Space Transportation System Design Approach: HL-20 Personnel Launch System," Journal of Spacecraft and Rockets, Vol. 30, No. 5, September-October 1993 pp. 512-528.
3. Smith, S.C., Reuther, J., Kinney, D., Saunders, "Low Speed Aerodynamics and Landing Characteristics of Sharp-Class Crew Transfer Vehicle Concepts," AIAA 2001-2888, 35th AIAA Thermophysics Conference, 11-14 June 2001, Anaheim, CA.
4. Saunders, D., Alien, G., Gage, P., Reuther, J., "Crew Transfer Vehicle Trajectory Optimization," AIAA 2001-2885, 35th AIAA Thermophysics Conference, 11-14 June 2001, Anaheim, C A.
5. Kinney, D., Bowles, J., Yang, L., Roberts, C., "Conceptual Design of a 'SHARP'-CTV," AIAA 2001-2887, 35th AIAA Thermophysics Conference, 11-14 June 2001, Anaheim, CA.
6. Kontinos, D.A., Gee, K., Prabhu, D.K., "Temperature Constraints at the Sharp Leading Edge of a Crew Transfer Vehicle," AIAA 2001-2885, 35th AIAA Thermophysics Conference, 11-14 June 2001, Anaheim, CA.
7. Gregory, T.J., Ardema, M.D. and Waters, M.H., "Hypersonic Transport Preliminary Performance Estimates for an All-Body Configuration," AIAA Paper 70-1224, 1970.
8. Allen, Jr., G.A., Gage, P.J. and Venkatapathy, E., "A Web-based Analysis System for Planetary Entry Vehicle Design," AIAA Paper 98-4826, 1998.
9. Gill, P.E., Murray, W., Saunders, M.A., Wright, M.H., "User's Guide for NPSOL (Version 4): A Fortran Package for Nonlinear Programming," 1986.
10. Wurster, K.E., Stone, H.W., "Aerodynamic Heating Environment Definition/Thermal Protection System Selection for the HL-20," Journal of Spacecraft and Rockets, Vol. 30, No. 5, September-October 1993 pp 549-557.
11. Kolodziej, P., "Aerothermal Performance Constraints for Hypervelocity Small Radius Unswept Leading Edges and Nosetips," NASA TM-112204, July 1997.
12. Jackson, E.B., Rivers, R.A., Bailey, M.L., "Effect of Lift-to-Drag Ratio in Pilot Rating of the HL-20 Landing Task," Journal of Spacecraft and Rockets, Vol. 30, No. 5, September-October 1993, pp. 543-548.
13. Ware, G.M., Cruz, C.I., "Aerodynamic Characteristics of the HL-20," Journal of Spacecraft and Rockets, Vol. 30, No. 5, September-October 1993, pp. 529-536.
14. Reuther, J., Jameson, A., Farmer, J., Martinelli, L. and Saunders, D., "Aerodynamic Shape Optimization of Complex Aircraft Configurations via an Adjoint Formulation," AIAA Paper 96-0094, 1996.
15. Hankey, W.L. and Schroeder, L.J., "Optimization of Lifting Re-entry Bodies," Proceedings 12th Annual Air Force Science and Engineering Symposium, 1965.
16. Naftel, J.C., Talay, T.A., "Ascent Abort Capability for the HL-20," Journal of Spacecraft and Rockets, Vol. 30, No. 5, September-October 1993, pp. 628-633.