The purpose of this paper is to describe the design, development and flight-testing of the U.S. Army 4200 sq ft parafoil recovery system built under NASA Contract NAS 9-00076. The 4200 f? parafoil described herein was a potential candidate to fulfill the U.S. Army requirement for a 10,000 lb useable payload precision guided recovery system. Design heritage as well as specific features, like lower surface inlets, confluence fitting, upper surface energy modulator design, deployment bag design and 60 ft diameter Ringslot drogue will be discussed. Initial flight test results, ground testing of various components to verify design margin and configuration changes will also be discussed. The 4200 sq ft parafoil recovery system completed three flight tests during 2003 at payload weights of over 15,000 Ibs
Design, Development and Flight Testing of the U.S. Army 4200 sq ft Parafoil Recovery System
18th AIAA Aerodynamic Decelerator System Technology Conference and Seminar ; 2005 ; Munich, Germany
2005-05-23
Conference paper
No indication
English
NTIS | 1971
|AIAA | 1970
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