Modelling and simulation of unsteady beat transfer for aerospacecraft trajectory optimization

Heat input reduction by optimal trajectory control is considered for the ra nge cruise of a hypersonic flight system propelled by a turbo/ram jet engin es combination. A mathematical model is developed for describing the unstea dy heat transfer through the thermal protection system. This model is coupl ed to the equations of motion of the vehicle. An efficient optimization tec hnique is applied for constructing st solution. The results show that a sig nificant heat input reduction can be achieved with only a small increase in fuel consumption. (C) 2000 Published by Elsevier Science B.V. on behalf of IMACS.