Conceptual Design of a Reusable Unmanned Space Vehicle Using Multidisciplinary Optimization

In this paper, a conceptual design for a reusable unmanned space vehicle was studied with multiple objective functions. To achieve this goal, a multi-objective genetic algorithm was used, and the performance of the space vehicle was evaluated based on weight, propulsion, aerothermodynamics, and trajectory analysis. Minimization of weight and landing speed and maximization of the highest C L in the supersonic flight regime were selected as the objective functions. The maximum limits in the dynamic pressure and the heat flux were applied as constraints. All objective functions are in trade-off relationships with each other. The geometry that produced the smallest weight had a very small wing size. Also, the vehicle that had the maximum C L in the supersonic flight regime had a closer angle between the flow and the lower surface of the wing, which showed the highest C L on the flat surface. The vehicle design with the lowest landing speed had the largest wing, which generated sufficient lift.