Reentry Design Solution for a Hypersonic Small Capsule

Abstract:

Restriction and selection criteria of inertial guidance sensors and system for a small recoverable capsule from onboard a hypersonic, atmospheric reentering rocket vehicle have attracted a specific research on the reentry design and challenges, with emphasize on the overall cost reduction and an optimal balance between the performances and costs under the given exploitation constraints. A simplified method for attitude control is derived that shows an easy accommodation in the capsule, given its high mass constraints, and convenient applicability for the class of small payloads under investigation. The palled experiments and investigating methodology is shown, as the result of the ORVEAL contract research team of ADDA-Association Dedicated to Development in Astronautics research organization, under the sponsorship of Romanian UEFISCDI authority for scientific research.

• Periodical: Applied Mechanics and Materials (Volume 332)
• Pages: 33-43
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.332.33
• Online since: July 2013
• Authors: Radu Dan Rugescu
• Keywords: Astrionics, Atmospheric Reentry, Flight Control, Space Guidance, Space Navigation

References

[1] Gazley, C., Atmospheric-entry, in W. von Braun, H. H. Koelle (ed.), "Handbook of Astronautical Engineering", McGraw Hill, New York, 1961.

[2] Gazley, C. Jr., Atmospheric-entry, Paper P-2052, The Rand Corporation Engineering Division, Santa Monica, CA, http://www.rand.org/content/dam/rand/pubs/papers/2008/P2052.pdf, 1960.

[3] Robert Clifton Duncan, Dynamics of atmospheric entry, Original from the University of California, McGraw-Hill, 306 pages, 1962.

[4] Martin, John J., Atmospheric Entry - An Introduction to Its Science and Engineering. Old Tappan, N. J., Prentice-Hall, 1966.

[5] Willes, R. E., An Application of the Method of Matched Asymptotic Expansions to Ordinary and Optimal Problems in Hypervelocity Flight Dynamics, PhD Thesis, MIT TE-14, 1966.

[6] Loh, W.H.T., Re-entry and Planetary Entry Physics and Technology, Applied Physics and Engineering, Vol. 2, 1968, Springer Verlag, pp.19-178.

DOI: 10.1007/978-3-642-48927-3_2

[7] Ledu, J., Pollak, C., Flight Testing Results on a Hypersonic Re-Entry Nose Cone, J. Spacecraft, 6, 9(1969), pp.1044-1047.

DOI: 10.2514/3.29753

[8] Regan, Frank J., Re-Entry Vehicle Dynamics (AIAA Education Series), New York, American Institute of Aeronautics and Astronautics, Inc., ISBN 0-915928-78-7, 1984.

[9] A. E. Roy, Orbital Motion. Adam Hilger, Bristol, 3rd edition, 1988.

[10] Hankey, Wilbur L., Re-entry aerodynamics, AIAA Education Series, American Institute of Aeronautics and Astronautics, Washington, D.C., 1988.

[11] Anderson, Jr., John D., Hypersonic and High Temperature Gas Dynamics, New York, McGraw-Hill, Inc., ISBN 0-07-001671-2, 1989.

[12] Cheng, H. K., Hypersonic Gas Dynamics of Slender Bodies, in Modern Developments in Gas Dynamics 1995, Springer Verlag, pp.131-182.

DOI: 10.1007/978-1-4615-8624-1_4

[13] Frank J. Regan, Satya M. Anandakrishnan, Dynamics of atmospheric re-entry, American Institute of Aeronautics and Astronautics, Inc., 599 p., 1993.

[14] Shawn Beaudette, "Satellite Mission Analysis", Carleton University Spacecraft Design Project, 2004.

[15] Lebleu, D., and Anne-Marie Schipper, Huygens and Netlander, a system overview, 2004, http://www.mrc.uidaho.edu/entryws/presentations/Papers/Lebleu.pdf.

[16] J. E. Marsden, S. D. Ross, K. Grubits, O. Junge, Wang-sang Koon, F. Lekien, M. Lo, S. Ober-blöbaum, K. Padberg, R. Preis, and B. Thiere, "New Methods in Celestial Mechanics and Mission Design", Bulletin (New Series) of the American Mathematical Society, Vol. 43 (2005).

DOI: 10.1090/s0273-0979-05-01085-2

[17] Rivell, Thomas, Notes on Earth Atmospheric Entry for Mars Sample Return Missions, NASA/TP-2006-213486, http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20060053240_2006255396.pdf.

DOI: 10.1108/09504120610647500

[18] R. D. Rugescu, and Cr. E. Constantinescu, "Accuracy Requirements for On-Board Drag Measurement Systems", Sc. Bulletin U.P.B., series D, Mech. Eng., 62, 2(2000), pp.63-72.

[19] Cr. E. Constantinescu, R. D. Rugescu, S. Ciochină, and R. C. Cacoveanu, "First flight experiment with the NERVA-1 inertial platform", Proceedings of 2010 International Conference on Mechanical Engineering, Robotics and Aerospace ICMERA-2010, ISBN 978-1-4244-8867-4, IEEE Catalog Number CFP1057L-PRT, December 2-4, Bucharest, Romania, 2010, pp.312-316.

DOI: 10.4028/www.scientific.net/amm.325-326.990

[20] Kazeminejad, Bobby, Analysis and Optimization of the Recovered ESA Huygens Mission, Diplom-Ingenieur in Physics Thesis, Graz University of Technology, Institute for Theoretical Physics, http://www.mrc.uidaho.edu/~atkinson/Huygens/Documents/MS_Kazeminejad.pdf, Austria, 2002.

[21] Cameron, J. D. M., Explicit guidance equations for maneuvering re-entry vehicles, 1977 IEEE Conference on Decision and Control including the 16th Symposium on Adaptive Processes and A Special Symposium on Fuzzy Set Theory and Applications, Vol. 16, pp.670-678, 1977.

DOI: 10.1109/cdc.1977.271656

[22] Harris, Ronald, and Setterlund, Roy, Advanced Maneuvering Re-entry Vehicle Guidance, Proceedings of the 49th Annual Meeting of The Institute of Navigation, Cambridge, MA, June 1993, pp.537-542.

[23] Frank Jouhaud. Fuzzy logic control - application to the guidance of a reentry space capsule. Number IAF-97-A.7.10. 48th International Astronautical Congress, Turin (Italy), October 1997.

[24] Voinot, O., D. Alazard, P. Apkarian, S. Mauffrey, and B. Clément, Launcher attitude control: Discrete-time robust design and gain-scheduling. IFAC Control Engineering Practice, 11:1243–1252, 2003.

DOI: 10.1016/s0967-0661(02)00234-4

[25] Zheng, Liwei, and Jing, Wuxing, Application of predictive guidance to reentry vehicle, 1st International Symposium on Systems and Control in Aerospace and Astronautics, 2006. ISSCAA 2006, pp.663-668.

DOI: 10.1109/isscaa.2006.1627421

[26] N. Fezans, D. Alazard, N. Imbert, and B. Carpentier. H∞ control design for multivariable mechanical systems - application to RLV reentry. In Guidance, Navigation and Control Conference and Exhibits, Hilton Head Island, SC, USA, 20 - 23 August 2007, AIAA.

DOI: 10.2514/6.2007-6349

[27] O'Donnell, Franklin, The Venus Mission – How Mariner 2 led the world to the planets, Jet Propulsion Laboratory, 1962, http://www.jpl.nasa.gov/mariner2/.

[28] Alekseenko, A. A., Dmitry A. Fedosov, Sergey F. Gimelshein, Deborah A. Levin, and Robert J. Collins, Transient Heat Transfer and Gas Flow in a MEMS-Based Thruster, Journal of Microelectromechanical Systems, Vol. 15, No. 1, February 2006, pp.181-194.

DOI: 10.1109/jmems.2005.859203

[29] C. K. Murch, J. E. Broadwell, A. H. Silver, and T. J. Marcisz, Low-Thrust Nozzle Performance, AIAA, Paper 68-17, 513, 1968.

[30] J. Morgan Parker, Michael J. Wilson, The Minimum Impulse Thruster

[31] Stratton, James, The use of the AEROJET MR-103H thruster on the New Horizons mission to Pluto, IAC-04-S.1.09, 55th International Astronautical Congress 2004 - Vancouver, Canada.

DOI: 10.2514/6.iac-04-s.1.09

[32] Rugescu, R. D., Gasdynamical thrust of reactive engines, U.P.B. Sc. Bull., series D, Mechanical Engineering, 62, 3(2000), pp.45-54.