Computational algorithm for hybrid rocket motor preliminary design

Abstract

Hybrid rockets present a compromise between solid and liquid rockets. It has a simpler design than liquid rockets and higher performance than solid rockets. It is constructed from an oxidizer tank followed by a solid fuel grain. Therefore, the combustion is controlled. This paper presents an algorithm to construct the design space of the hybrid rocket motor for a single cylindrical port. A simple regression rate formula is used to treat the combustion. The inner diameter of the grain, outer diameter of the grain, and length of the grain are used as parameters to construct the design space and a single design point is chosen. The performance of this design point is presented with the combustion time.