Abstract
The purpose of this study is to apply a multidisciplinary optimization method for the conceptual designs of hypersonic experimental vehicles with advanced airbreathing engines. Using this method, we obtain the necessary vehicle sizes and optimal flight trajectories. The vehicle has a lifting body shape. First, we integrate analytical methods into the optimization problem, the solution of which yields the smallest gross weight of the vehicle. The results indicate a vehicle that is about 12 m in total length and 4-5 Mg in gross weight This information allows us to determine the optimal vehicle configuration and flight trajectory for a highly feasible hypersonic vehicle. In addition, the trajectory optimizations enable the vehicle to glide back to a takeoff point without consuming propellant. This study confirms the effectiveness of the proposed analysis and optimization method.
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