Hybrid deorbit motor design feasibility

Abstract

This paper addresses the feasibility of using a hybrid rocket motor to deorbit the large booster stage of the proposed NLS. A hybrid motor was of interest because it could utilize the residual low pressure Gox from the boosters main engine Lox tank. The resulting study determines that the concept would be feasible and should be given further consideration. Also, a preliminary design for a deorbit motor was proposed which would weigh much less than an equivalent hypergolic system. The hybrid deorbit concept and design has the potential of yielding a simpler cost effective system that could also be applicable to future launch systems with similar missions.