Ramjet and Scramjet Engine Cycle Analysis for a Generic Hypersonic Vehicle

Horizontal take -off and horizontal landing vehicles continue to be a subject of great interest for future space launch missions. For a hypersonic vehicl e, in order to operate through all Mach regimes, a combined -cycle propulsion system is the most promising concept. This paper describes the cycle analysis for a ramjet/ scramjet system consisting of an airbreathing core with a variable geometry inlet. This combined cycle engine model can be used within any hypersonic vehicle conceptual design framework . The propulsion model for this configuration study is developed using a two dimensional forebody, inlet , and nozzle. A one dimensional model is used for the isolator and the combus tor. This mathematical model of the engine is implemented in MATLAB . The effect of the flight path angle and the angle of attack are investigated. The engine mode l is used in the development of a six degrees of freedom simula tion .