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Apollo experience report: Thermal protection subsystemThe Apollo command module was the first manned spacecraft to be designed to enter the atmosphere of the earth at lunar-return velocity, and the design of the thermal protection subsystem for the resulting entry environment presented a major technological challenge. Brief descriptions of the Apollo command module thermal design requirements and thermal protection configuration, and some highlights of the ground and flight testing used for design verification of the system are presented. Some of the significant events that occurred and decisions that were made during the program concerning the thermal protection subsystem are discussed.
Document ID
19740007423
Document Type
Other - NASA Technical Note (TN)
Authors
Pavlosky, J. E.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
St.leger, L. G.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1974
Subject Category
Space Vehicles
Report/Patent Number
NASA-TN-D-7564
JSC-S-383
Accession Number
74N15536
Funding Number(s)
PROJECT: RTOP 914-50-00-00-72
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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