Thermal modeling of Shuttle solid rocket motors on the launch pad

Abstract

A three-dimensional thermal model of the Space Transportation System redesigned solid rocket motors has been developed. The thermal model, which employs the SINDA-85 code, was developed to provide a reliable methodology for predicting motor surface and component temperatures. A discussion of the model development and the required boundary conditions, including the calculation of the convective and radiative fluxes, is presented. Predicted surface temperatures are shown to be in good agreement with available data on experimental measurements. The method has also been used to predict the propellant mean bulk temperature. This methodology provides not only reliable predictions of temperatures in critical locations but also global thermal information, and it possibly provides a substitute for the instrumentation.