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Effects of aerodynamic heating and TPS thermal performance uncertainties on the Shuttle OrbiterA procedure for estimating uncertainties in the aerodynamic-heating and thermal protection system (TPS) thermal-performance methodologies developed for the Shuttle Orbiter is presented. This procedure is used in predicting uncertainty bands around expected or nominal TPS thermal responses for the Orbiter during entry. Individual flowfield and TPS parameters that make major contributions to these uncertainty bands are identified and, by statistical considerations, combined in a manner suitable for making engineering estimates of the TPS thermal confidence intervals and temperature margins relative to design limits. Thus, for a fixed TPS design, entry trajectories for future Orbiter missions can be shaped subject to both the thermal-margin and confidence-interval requirements. This procedure is illustrated by assessing the thermal margins offered by selected areas of the existing Orbiter TPS design for an entry trajectory typifying early flight test missions.
Document ID
19800054544
Acquisition Source
Legacy CDMS
Document Type
Other - Collected Works
Authors
Goodrich, W. D.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Derry, S. M.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Maraia, R. J.
(NASA Johnson Space Center Structures and Mechanics Div., Houston, Tex., United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1980
Subject Category
Space Transportation
Report/Patent Number
AIAA PAPER 79-1042
Accession Number
80A38714
Distribution Limits
Public
Copyright
Other

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