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- An empirical heating model, thermal protection system unit weight correlation, and trajectory analysis were used to develop a computation procedure for studying the sensitivity of thermal protection system weights to variations in pertinent trajectory parameters. The analytical techniques used in developing this computer program are described. Application of the analysis to a Space Shuttle Orbiter configuration was performed to demonstrate gross thermal protection system weight trends with selected entry trajectory parameters.
- Other Subject(s):
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 19740009532.
Accession ID: 74N17645.
- No Copyright.
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