Fig 1: Parachute recovery system hardware. Main parachute constructed of Spectra 1000 suspension lines, and 1/2 in kevlar tape radials with F-111 (low porosity) ripstop nylon for low weight and packing bulk.Drogue parachute constructed of 1/2 in kevlar tape suspension lines and radials with MIL-C-7020, Type I ripstop nylon (high porosity). Components consists of 14 ft cross parachute, cross parachute y-bridle (mounts radio beacon and strobe light), parachute canister, drogue parachute tow line, 6 ft ribless guide surface drogue parachute and its deployment bag.
Fig 2 : Inflated veiw of 14 ft cross parachute showing details of y-bridle, spectra lines, kevlar tapes and cross arm connectors.Photos by: Randy Thomas

Design and Development of aSmall Universal Sounding Rocket Recovery System

(AIAA Paper 99-1711)

Thomas, R.L., "Design and Development of a Small Universal Sounding Rocket Recovery System", 15th CEAS/AIAA Aerodynamic Decelerator Systems Technology Conference, Toulouse, France, pp. 66-76, June 8-11, 1999, (AIAA Paper 99-1711) Conference proceedings CP999.

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PAPER ABSTRACT:

This paper presents a preliminary 3-phase design, in which hardware was developed to fully test a flight worthy and operational sounding rocket parachute recovey system. This recover system consists of a 3 ft diameter guide surface drogue, and a 14 ft main cross parachute at a cross arm (W/L) ratio of 2.8:1 (063), packed into a 6 in diameter parachute canister. construction with nylon, kevlar and spe tra provide low weight and packing bulk. The complete recovery system weighs 4.5 lb and packs into a length of 8 in. System is designed for a 25 lb to 55 lb payloads with impact velocities of 22 to 29 ft/sec, and can be used up to 80 lb at 35 ft/sec. Design heritage from a large cross parachute recovery system by the author (AIAA 97-1531), led to development of this recovery sysem, which further addresses issues of performance and parameters contributing to wake recontact.

NOTE: (AIAA stands for American Institute of Aeronautics and Astronautics)

 

PAPER REFERENCES

1. Thomas, R., Kline, K., Rosenfield, G., and Das, D. "Hybrid Rocket Flight Testing to Develop the Hyperion Sounding Rocket Recovery Systems", 15th CEAS/AIAA ADS Technology Conference, June 9-11, 1999, Toulouse, France. (AIAA 99-1761)

2. Thomas, R., "Design, Fabrication, Packing and Testing of the ARIM-1 Sounding Rocket Recovery System", 14th AIAA ADS Technology Conference, June 3-5, 1997, pp. 451-473. (AIAA 97-1531-CP)

3. Thomas, R., Calculating Parachute Descent Rates: Technical Report No. 1, Paratech Parachutes, 139 Kelsan Way, Fairbanks, Alaska, 1st Edition Sept. 1990.

4. Silbert, M.N., "Parachute Recovery Location Aids", 7th Conference on Sounding Rockets, Balloons and Related Space Systems, (AIAA 86-2545)

5. Cockrell, D.J., "The Aerodynamics of Parachutes", AGARDOgraph No. 295, July 1987.

6. Lingard, J.S., "Aerodynamics 2 (Unsteady)", Parachute Systems Technology Short Cours , Univ. of Minnesota, Minneapolis, MN., Oct 26-30, 1998.

7. Oler, J. and Strickland J.L., "Prediction of Parachute Collapse Due to Wake Recontact", 10th AIAA ADS Technology Conference, Cocoa Beach, Florida, April 18-20, 1989.
(AIAA 89-0901-CP)

8. Strickland J. and macha, J., "Preliminary Characterizations of Parachute Wake Recontact", 10th AIAA ADS Technology Conference, Cocoa Beach, Florida, April 18-20, 1989.
(AIAA 89-0897A-CP)

9. Maydew, R.C. and Peterson, C.W., Design and Testing of High Performance Parachutes, AGARDOgraph No. 319, NTIS, Springfield, VA., Nov. 1991, (ISBN 92-835-0649-9)

10. Doherr, K.F., "Parachute Trajectory Simulation and Analysis", Parachute Systems Technology Short Course, Univ. of Minnesota, Minneapolis, MN., Oct. 26-30, 1998.

11. Knacke, T.W., Parachute Recovery System Design Manual, Para Publishing, Santa Barbara, CA., 1992. 12. Garrad, W.L., "Canopy Inflation", Parachute Systems Technology Short Course, Univ. of Minnesota, Minneapolis, Mn, Oct. 26-30, 1998.