Modelling and simulation of unsteady heat transfer for aerospacecraft trajectory optimization

Heat input reduction by optimal trajectory control is considered for the range cruise of a hypersonic flight system propelled by a turbo/ram jet engines combination. A mathematical model is developed for describing the unsteady heat transfer through the thermal protection system. This model is coupled to the equations of motion of the vehicle. An efficient optimization technique is applied for constructing a solution. The results show that a significant heat input reduction can be achieved with only a small increase in fuel consumption.