Multidisciplinary design optimization of reusable launch vehicles

Reusable launch vehicles are once again becoming an attractive proposition, due to recent advancements in technology, and the opportunity to massively expand our accessibility to space. This paper discusses the optimization software under ongoing development at the University of Glasgow, that can be applied to such vehicles. Considering the wide diversity of previous and existing concepts, this work seeks to rapidly produce novel configurations using low-fidelity analysis methods. At present, surface inclination methods for high-speed aerodynamic computation are coupled with a simple six degree-of-freedom finite element beam model. The resulting aerostructural system is then utilized in a population based design optimization framework. Discussions of these methodologies are provided, along with an overall outline of their combination in a typical design optimization. Descriptions of the design variables employed are provided, along with an analysis of the methods utilized to constrain geometric properties and performance characteristics, in order to avoid undesirable characteristics or infeasible configurations. Finally, an aerostructural trim optimization is carried out, with comparison to a prior reusable launch vehicle concept.