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Development and testing of subsonic tandem deceleration system

Published online by Cambridge University Press:  05 October 2016

M. Samani  and
M. Faraji Mahyari
M. Samani*
Affiliation:
Department of Engineering, College of Mechanical Engineering, Yadegar-e-Imam Khomeini (RAH), Shahre Rey Branch, Islamic Azad University, Tehran, Iran
M. Faraji Mahyari
Affiliation:
Department of Engineering, College of Mechanical Engineering, Yadegar-e-Imam Khomeini (RAH), Shahre Rey Branch, Islamic Azad University, Tehran, Iran
*
[email protected]
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Abstract

For many years, deceleration systems developed in an evolutionary fashion. This evolution needed flight test and experimental data. Concurrently, payload became much more expensive and needed to be safer. Today, there are a variety of methods employed to recover airborne bodies such as bio-capsules, reentry satellites, carrier missiles' boosters, reentry satellites, etc. Most of these methods make use of a parachute landing system in which recovery occurs in multiple phases. This paper studies the final phase of the subsonic recovery scenario for which a multi-phase deceleration system has been designed. To observe and evaluate system performance, a test projectile is designed that accelerates the payload to a certain velocity in order to test the recovery system. Finally, theoretical and test results are compared to indicate the appropriate design and reliable deceleration velocity in a space payload recovery.

Keywords

subsonic recoverysubsonic tandem deceleration systemtest scenario
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1234 , December 2016 , pp. 1833 - 1848
Copyright
Copyright © Royal Aeronautical Society 2016 

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References

REFERENCES

1. Witkowski, A. and Bruno, R. Mars exploration rover parachute decelerator system program overview, AIAA Paper, 2003, 2100, p. 2003.Google Scholar
2. Spencer, D.A. and Braun, R.D. Mars pathfinder atmospheric entry-trajectory design and dispersion analysis, J Spacecraft and Rockets, 1996, 33, (5), pp. 670–676.Google Scholar
3. Arenson, D. Rocket powered test vehicles, J Jet Propulsion, 1955, 25, (9), pp. 441–445.Google Scholar
4. Kenig, S. et al Rigging test bed development for validation of multi-stage decelerator extractions, 22nd AIAA Aerodynamic Decelerator Systems Technology Conference, 2013, Daytona Beach, Florida, US.Google Scholar
5. Pepper, W.B. Design and development of the 24-foot diameter hybrid Kevlar-29/nylon ribbon parachute, J Aircr, 1980, 17, (1), pp. 45–52.CrossRefGoogle Scholar
6. Kent, W. Space shuttle orbiter drag parachute design, Space, 2001, 1, p. 29287.Google Scholar
7. Heindel, K. and Wolf, D. Parachute tests for a missile descent system, 15th CEAS/AIAA Aerodynamic Decelerator Systems Technology Conference, 1999, Toulouse, France.Google Scholar
8. Guidotti, G. et al, Design, development, testing, and in-flight qualification of a parachute recovery system, J Spacecraft and Rockets, 2012, 49, (4), pp. 700–708.Google Scholar
9. Gallon, J.C. and Witkowski, A. Verification and validation testing of the parachute decelerator system prior to the first supersonic flight dynamics test for the low density supersonic decelerator program, 23rd AIAA Aerodynamic Decelerator Systems Technology Conference, 2015, Daytona Beach, Florida, US.Google Scholar
10. Lin, X. Rocket-boosted test for a ribbon parachute, 10th AIAA Aerodynamic Decelerator Systems Technology Conference, 10th, 1989, Cocoa Beach, Florida, US.Google Scholar
11. Machín, R.A., Iacomini, C.S., Cerimele, C.J. and Stein, J.M. Flight testing the parachute system for the space station crew return vehicle, J Aircr, 2001, 38, (5), pp. 786–799.Google Scholar
12. Braun, R.D. and Manning, R.M. Mars entry, descent and landing challenges. IEEE Aerospace Conference, March 2006, Big Sky, Montana.Google Scholar
13. Pepper, W.B., Preliminary report on development of an interim parachute recovery system for a re-entry vehicle. J Aircr, 1980, 17, (3), pp. 218–224.Google Scholar
14. Schatzle, P. and Curry, W. Flight simulation of a vehicle with a two-stage parachute system, J Aircr, 1980, 17, (8), pp. 545–546.Google Scholar
15. Thomas, R.L. Design and development of a small universal sounding rocket recovery system, CEAS/AIAA Aerodynamic Decelerator Systems Technology Conference, 1999, Toulouse, France.Google Scholar
16. Thomas, R.L., Thomas, D.G. and Morgan, B. Flight testing a parachute orientation system to air launch rockets into low earth orbit, 19th AIAA Aerodynamic Decelerator Systems Technology Conference, 2007, Williamsburg, Virginia, US.Google Scholar
17. Samani, M. and Pourtakdoust, S.H. Analysis of two-stage endo-atmospheric separation using statistical methods, J Theoretical and Applied Mechanics, 2014, 52, (4), pp. 1115–1124.Google Scholar
18. Roskam, J. Airplane Flight Dynamics and Automatic Flight Controls, 1979, Roskam Aviation and Engineering Corp., Ottawa, Kansas, US.Google Scholar
19. Blakelock, J.H., Automatic Control of Aircraft and Missiles, 1991, John Wiley & Sons, Canada.Google Scholar
20. Bruns, K.D., Moore, M.E., Stoy, S.L., Vukelich, S.R. and Blake, W.B. Missile Datcom. User's Manual-Rev 4/91. 1991, DTIC Document.Google Scholar
21. Knacke, T.W., Parachute recovery systems design manual. 1991, DTIC Document.Google Scholar
22. Mohaghegh, F. and Jahannama, M. Decisive roll of filling time on classification of parachute types, J Aircr, 2008, 45, (1), pp. 267–275.CrossRefGoogle Scholar
23. Potvin, J. Universality considerations for graphing parachute opening shock factor versus mass ratio, J Aircr, 2007, 44, (2), pp. 528–538.Google Scholar
24. Perschbacher, T. and Potvin, J. The improved ideal parachute model and its application to the study of the inflation dynamics of slider-reefed ram-air and round parachutes, 15th Aerodynamic Decelerator Systems Technology Conference, 1999, American Institute of Aeronautics and Astronautics.Google Scholar
25. Lee, C.K. Modeling of parachute opening—an experimental investigation, J Aircr, 1989, 26, (5), pp. 444–451.Google Scholar
26. Lingard, J. The Effects of Added Mass on Parachute Inflation Force Coefficients, AlAA 95-1 561, 1995.Google Scholar
27 Siewert, A., Seely, L., Smith, M., Silbert, M. and Widows, H. Design of the Black Brant V sounding rocket family of recovery systems, 13th Aerodynamic Decelerator Systems Technology Conference, Aerodynamic Decelerator Systems Technology Conferences, 15–18 May 1995, Florida, US.Google Scholar