Abstract
We consider the system identification problem associated with determining the aerothermodynamic heating environment of the Space Shuttle Orbiter Columbia during reentry. A mathematical characterization of this environment is required for mission capability assessment as well as operational flight planning. The identification problem is one of estimating certain parameters in a fairly complete nonlinear, nonstationary partial differential equation (diffusion) model of the heat transfer characteristics of the orbiter thermal protection system (tiles) interacting with the surface boundary phenomena of aerodynamic forced convection and radiation. Cur solution uses a maximum likelihood technique that incorporates discrete, depth-wise (thermocouple) temperature measurements and reentry trajectory data. Results of analyzing flight test data collected during the first flight of the Columbia are included for illustrative purposes.
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