The combined optimization of the three-dimensional range cruise and the ascent trajectory of a two-stage hypersonic flight system with airbreathing engines is subject of this paper. The flight system performs a cruise until separation after which the carrier stage returns to its launch site and the orbital stage conducts an ascent to its orbit. The cruise trajectory is highly unsteady, even for a cruise distance as large as 6000 km. Particular emphasis is put on the modelling of the vehicles in order to achieve realistic results. The modelling includes control and state variable constraints which exert a significant influence in hypersonic Fight. Efficient mathematical optimization methods and computational techniques are required which are capable of coping with the addressed points and of providing a solution for the optimization problem. A parameterization optimization was successfully applied. [References: 12]
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