SHAR for a TSTO launcher

The goal of this paper is to investigate the challenge of a fast and frequent access to space for small satellite in LEO by means of a Rocket Based Combined Cycle (RBCC) integrated by a solid booster, a reusable scramjet (wave-rider). Rocket-based combined-cycle (RBCC) engine has the potential to combine both advantages of high thrust-to-weight ratio of a rocket engine and high specific impulse of an air-breathing engine by behaving as a rocket in the static to trans-atmospheric flight regime, as a scramjet in supersonic to hypersonic speed flight, and as a pure rocket near orbital speeds. A three-stage launcher with an overall mass estimation of 9791.51 kg, with the capability of delivering 100 kg payload has been designed with a configuration of a solid booster, a scramjet, and a hybrid rocket at respectively first, second and third stages. The third stage will be an integral part of the scramjet stage’s payload bay until it reaches its launching conditions. The final stage launches the satellite into its designed orbit when it reaches its destined altitude.