Integrated performance of hypersonic vehicle and turbine based combined cycle propulsion system

A hypersonic vehicle concept as a first stage of TSTO is developed with a turbine based combined cycle propulsion system. The install and uninstall performance characteristics of engine are calculated by numerical simulation software. Based on equal shock intensity method, a hypersonic mix-pressure inlet is designed and the regulation is described in this dissertation. In addition, an SREN with linear extend afterbody is designed. At last, the flight performance of the vehicle with two kinds of different fuels are calculated from take off to Mach 4.