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Landing characteristics of the Apollo spacecraft with deployed-heat-shield impact attenuation systemsImpact acceleration and landing system characteristics of Apollo spacecraft command module configurations with deployed heat shield
Document ID
19660005612
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Stubbs, S. M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
January 1, 1966
Subject Category
Space Sciences
Report/Patent Number
NASA-TN-D-3059
Accession Number
66N14901
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
LANDING SYSTEM
APOLLO SPACECRAFT
COMMAND MODULE
IMPACT ACCELERATION

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