Authors

Abstract

According to the importance of knowing aerodynamic parameters of parachutes used as recovery system of a sounding rocket, some launching tests were conducted to achieve the acceptable reliability. A testing rocket which simulated the recovery condition of the sounding rocket was used in these tests. Furthermore, the results of the tests used for validating a simulation code written for investigating the aforementioned two stage recovery system process. Some aerodynamic parameters of parachutes such as drag coefficient, opening force coefficient, and filling time, filling distance and drag area increase during inflation process were estimated from the tests in various conditions. The results show that for the first and second used drogue chutes with large canopy-loading, in contrast to the main parachute with small canopy-loading, the inflation parameters were not dependent on the height or air density. The drag area versus time shows linear variation for the first drogue chute, and shows second and third function for the other two parachutes. The situation of the second drogue chute in front of the main parachute affects the filling time of the main parachute. The distance between the parachutes, the ratio of their canopy areas and the air velocity are some parameters that affect the filling time. The results of this investigation could be worth for the design of a decelerator system, preciously.

Keywords

  1. Tutt, B. A. and Taylor, A. P., “The Use of LS-DYNA to Simulate the Inflation of a Parachute Canopy,” 18th AIAA Aerodynamic Deceleratory Systems Technology Conference and Seminar, 2005.
  2. Poynter, D. F., The Parachute Manual, Vol. II, California: Para Pub., 1991.
  3. Knacke, T. W, Parachute Recovery systems: Design Manual, California, Para Pub., 1992.
  4. Ewing, E. G., Bixby, H. W. and Knacke, T. W., Recovery Systems Design Guide, Technical Report, Irvin Industries Inc, California Division, 1978.
  5. Rychnovsky, R. E., “A Lifting Parachute for Very-Low-Altitude, Very-High-Speed Deliveries,” Journal of Aircraft, Vol. 14, No. 2, 1977, pp. 184-187.
  6. Masciarelli, J., Cruz, J. R., and Hengel, J. E., “Development of an Improved Performance Parachute System for Mars Missions,” 17th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar, Monterey, California, 2003.
  7. Thomas, R., 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 and Seminar, Williamsburg, VA, 2007.
  8. Stein, K. and et al., “Aerodynamic Interactions between Parachute Canopies,” Transactions of the ASME, 70, 2003.
  9. Rasi Marzabadi, F., Meshkani, R., Pouryavi, H. and Ebrahimi, M., “Aerodynamic Coefficient Corrections of Parachute Group of a Space Vehicle Based on Experimental Tests,” 1st National Hydraulic and Aerodynamic Conferences, HAC2012, Tehran, Aeronautical Organization, 2012 (In Persian).