Feasibility Study on Single Stage to Orbit Space Plane with RBCC Engine

Abstract

In this study, a Turbine-Based Combined-Cycle (TBCC) engine propelling a Single-Stage To Orbit (SSTO) space plane was replaced with a Rocket-Based Combined-Cycle (RBCC) engine for two purposes: to examine whether it would be capable of achieving orbital injection as a SSTO, and to determine what influence the engine replacement would have on the guidelines governing design of the airframe and planning of the flight path. By definition, a multidisciplinary optimization is necessary in order to obtain exact answers to these questions. For this study, the airframe weight and aerodynamics were estimated and only the airframe design and flight path were optimized in order to reduce the calculation. The following findings were established. In order to achieve a minimal structural weight for the SSTO, ultimately, a RBCC-powered craft was calculated to have clear advantages over a TBCC-powered craft. Secondly, the wings should be designed with as small an area as possible for takeoff, in both TBCCand RBCC-powered space planes. It was also found to be essential for the TBCC-powered craft to operate in an equivalent dynamic pressure flight regime, while the time history of the angle of attack of the RBCC-powered craft must incorporate a steep climb in the ducted rocket mode and horizontal flight in the ramjet mode.