Optimization and parametric studies of two-stage-to-orbit liquid oxygen/paraffin hybrid rocket vehicles

Abstract

A framework was developed to perform conceptual design studies of hybrid rocket launch vehicles. The framework generates vehicle designs considering the propulsion, structures, aerodynamics, and trajectory/guidance sub-disciplines. The launch vehicles investigated use paraffin wax and liquid oxygen propellants. The payload fraction was assessed for vehicles with either an electric pump-fed or pressure-fed system. A particle swarm optimization found optimal two-stage-to-orbit configurations for both feed systems investigated. Electric pump-fed systems had a payload fraction increase over pressure-fed systems. A parametric study of the vehicle design variables provides verification of finding the local optimum and sensitivity of the payload fraction to change in each design variables.