Abstract
Geometry, aero/aerothermal, trajectory, and thermal protection selection and sizing tools are linked together in a collaborative engineering environment to form a multidisciplinary analysis model of a reusable launch vehicle performing atmospheric entry. This entry model can determine the effects of vehicle shape and trajectory on the aerothermal environment that must be endured by the thermal protection system. The aerothermal environment in turn determines the size and weight of the thermal protection system required by the vehicle. The importance of interdisciplinary coupling on the design of the vehicle thermal protection system is demonstrated for a wing-body vehicle. Results of a parametric study of the influence of wing thickness on maximum cross-range and thermal protection weight are reported. Difficulties encountered with trajectory optimization are discussed.
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