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Summary of Attached Inflatable Decelerator (AID) DevelopmentAttached inflatable decelerators (AID) were tested in an environmental chamber, a spin tunnel, and a wind tunnel. Deployment tests were conducted in environmental chamber to examine guided and unguided water alcohol vapor inflation. Subsonic performance tests were conducted in the spin tunnel. The full-scale wind tunnel was used for AID gust and supersonic performance tests. The supersonic tests were conducted at Mach number 3.0 with 12 ounces of fluid and Mach number 2.2 with six ounces of fluid.
Document ID
20070030992
Acquisition Source
Langley Research Center
Document Type
Video
External Source(s)
http://lisar.larc.nasa.gov/MOVIES/MEDIUM/LV-2007-00058.mov
http://lisar.larc.nasa.gov/MOVIES/LARGE/LV-2007-00058.mov
Date Acquired
August 24, 2013
Publication Date
April 8, 1968
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
L-997
Report Number: L-997
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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