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This paper presents a preliminary 3-phase design, in which hardware was developed to fully test a flight worthy and operational sounding rocket parachute recovery system. This recovery 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 3.8:1 (0,263), packed into a 6-in diameter parachute canister. Construction with nylon, kevlar and spectra provide low weight and packing bulk. The complete recovery systelm weighs 4.5-lb and packs into a length of &-in. System is designed for 25-lb to 55-lb payloads with impact velocities of 22 to 29 ftfsec, and can be used up to 80-lb at 35 ftlsec: Design heritage from a large cross parachute recovery system by the author (AIAA 97-1531), led to development of this recovery system, which further addresses issues of performance and parameters contributing to wake recontact. VT W x\* Nomenclature Ballistic parameter (W / (C,S),) Drag coefficient Projected (inflated) parachute diameter (ft) Froude number (V'/DJ Projected parachute drag area (ft') Reefed parachut.e drag area (ft') Parachute opening force (lb) Atmospheric pressure ratio Atmospheric density ratio Dynamic pressure (lb/ft2

Author

Randy Thomas

Publisher

American Institute of Aeronautics and Astronautics

Published

1999

Language

EN