International Journal of Aerospace Engineering
Volume 2009 (2009), Article ID 326102, 21 pages
doi:10.1155/2009/326102
Research Article

High-Fidelity Aerothermal Engineering Analysis for Planetary Probes Using DOTNET Framework and OLAP Cubes Database

Prabhakar Subrahmanyam

Department of Mechanical and Aerospace Engineering, Center of Excellence for Space Transportation & Exploration, San Jose State University, One Washington Square, San Jose, CA 95192, USA

Received 15 January 2009; Accepted 15 April 2009

Academic Editor: Tom Shih

Copyright © 2009 Prabhakar Subrahmanyam. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Linked References

  1. C. Davies, “Planetary Mission Entry Vehicles,” Quick Reference Guide, Ver. 2.1, NASA-ARC, 2002.
  2. Program Development Corp., “GridPro/az3000 User's Guide and Reference Manual,” 300 Hamilton Avenue, Suite 409, White Plains, NY 10601, 1996.
  3. P. Papadopoulos and P. Subrahmanyam, “Trajectory based automatic grid generation tool for atmospheric entry CFD modeling,” in Proceedings of the 9th International Conference on Numerical Grid Generation in Computational Field Simulations, pp. 190–201, San Jose, Calif, USA, June 2005.
  4. C. G. Justus and D. L. Johnson, “Mars Global Reference Atmospheric Model 2001 Version (MARS- GRAM 2001) Users Guide,” NASA/TM-2001-210961, April 2001.
  5. P. Subrahmanyam, “Multidimensional aerothermodynamic analysis for planetary probes using OLAP cubes,” in Proceedings of AIAA Atmospheric Flight Mechanics Conference, Keystone, Colo, USA, August 2006, AIAA-2006-6274.
  6. J. E. Pavlosky and St. L. G. Leger, “Apollo experience report—thermal protection subsystem,” Tech. Rep. NASA TN D-7564, NASA, Washington, DC, USA, January 1974.
  7. P. Papadopoulos and P. Subrahmanyam, “Web-based computational investigation of aerothermodynamics of atmospheric entry vehicles,” Journal of Spacecraft and Rockets, vol. 43, no. 6, pp. 1184–1190, 2006. View at Publisher · View at Google Scholar
  8. “TecPlot® Version 9 User's Manual,” Amtec Engineering, Inc., P. O. Box 3633, Bellevue, WA 98009-3633.
  9. Google Earth, http://earth.google.com/.
  10. J. Fay and F. Riddell, “Theory of stagnation point heat transfer in dissociated air,” Journal of Aeronautical Sciences, vol. 25, no. 2, 1958.
  11. E. R. Hillje, “Entry aerodynamics at lunar conditions obtained from the flight of Apollo 4 (AS 501),” Tech. Rep. NASA TN D-5399, NASA, Washington, DC, USA, October 1969.
  12. G. L. Brauer, D. E. Cornick, and R. Stevenson, “Capabilities and applications of the program to optimize simulated trajectories (POST),” Tech. Rep. NASA CR-2770, NASA, Washington, DC, USA, February 1977.
  13. C. R. Hargraves and S. W. Paris, “Direct trajectory optimization using nonlinear programming and collocation,” Journal of Guidance, Control, and Dynamics, vol. 10, no. 4, pp. 338–342, 1987.
  14. D. A. Spencer, R. C. Blanchard, R. D. Braun, P. H. Kallemeyn, and S. W. Thurman, “Mars Pathfinder entry, descent, and landing reconstruction,” Journal of Spacecraft and Rockets, vol. 36, no. 3, pp. 357–366, 1999.
  15. K. Sutton and R. A. Graves, “A general stagnation point convective heating equation for arbitrary gas mixtures,” Tech. Rep. NASA TR-376, NASA, Washington, DC, USA, 1971.
  16. M. E. Tauber and K. Sutton, “Stagnation-point radiative heating relations for earth and mars entries,” Journal of Spacecraft and Rockets, vol. 28, no. 1, pp. 40–42, 1991.
  17. M. E. Tauber, “A review of high-speed, convective heat transfer computation methods,” Tech. Rep. NASA TP-2914, NASA, Washington, DC, USA, July 1989.
  18. D. L. Cauchon, “Radiative heating results from the FIRE II flight experiment at a reentry velocity of 11.4 kilometers per second,” Tech. Rep. NASA TM X-1402, NASA, Washington, DC, USA, July 1967.
  19. E. V. Zoby and E. M. Sullivan, “Effects of corner radius on stagnation-point velocity gradients on blunt axisymmetric bodies,” Tech. Rep. NASA TM X-1067, NASA, Washington, DC, USA, 1965.
  20. R. K. Crouch and G. D. Walberg, “An investigation of ablation behavior of Avcoat 5026/29M over a Wide Range of Thermal Environments,” Tech. Rep. NASA TM X-1778, NASA, Washington, DC, USA, 1969.
  21. J. C. Ellison, “Experimental stagnation-point velocity gradients and heat-transfer coefficients for a family of blunt bodies at Mach 8 and angles of attack,” Tech. Rep. NASA TN D-5121, NASA, Washington, DC, USA, April 1969.
  22. NASA Ames Thermal protective Materials and System Branch, TPSX, Ver 4.1, August 2005, http://tpsx.arc.nasa.gov/.
  23. S. D. Williams and M. C. Donald, “Thermal protection materials: thermophysical property data,” Tech. Rep. NASA RP-1289, NASA, Washington, DC, USA, 1992.
  24. Anon, “User's manual, aerotherm charring material thermal response and ablation program,” Acurex UM-87-13/ATD, Aerotherm Division, Acurex Corporation, Mountain View, Calif, USA, November 1987.
  25. P. Subrahmanyam, “Development of an interactive hypersonic flow solver framework for aerothermodynamic analysis,” Engineering Applications of Computational Fluid Mechanics Journal, vol. 2, no. 4, pp. 436–455, 2008.
  26. S. Srinivasan, J. C. Tannehill, and K. J. Weilmuenster, “Simplified curve fits for the thermodynamic properties of equilibrium air,” Tech. Rep. NASA RP-1181, NASA, Washington, DC, USA, 1987.
  27. J. C. Tannehill, D. A. Anderson, and R. H. Pletcher, Computational Fluid Mechanics and Heat Transfer, Taylor & Francis, Philadelphia, Pa, USA, 2nd edition, 1997.
  28. S. C. Chapra and R. P. Canale, Numerical Methods for Engineers, McGraw-Hill, New York, NY, USA, 2nd edition, 1988.