Integrated design-trajectory optimization for hybrid rocket motors

Abstract

Hybrid rocket motors present a competitive edge among space applications, as they are flexible, safe, reliable, and low cost. The motor design and operation are contingent on the type of designated mission; therefore, it is useful to couple design and trajectory optimization. This approach is especially needed for hybrid rockets in which a unique combustion process links thrust and specific impulse. In this chapter, a multidisciplinary optimization code is described for the use of designing hybrid rocket motors. There are few parameters which define the design of the hybrid engine, whereas the trajectory optimization is characterized by continuous controls. Due to the difference between these unknowns, a mixed optimization procedure has been developed. To maximize mission performance, direct optimization of engine design variables is coupled with the trajectory indirect optimization.Some interesting applications of the aforementioned procedure are presented.