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- W2000736077 abstract "A 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." @default.
- W2000736077 created "2016-06-24" @default.
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- W2000736077 date "1979-06-04" @default.
- W2000736077 modified "2023-09-24" @default.
- W2000736077 title "Effects of aerodynamic heating and TPS thermal performance uncertainties on the Shuttle Orbiter" @default.
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- W2000736077 doi "https://doi.org/10.2514/6.1979-1042" @default.
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