Sensitivity of power plant mass to such variables as vehicle thrust requirements, precompression surface incidence, intake and nozzle designs and turbo machinery design constraints is described for an example of turboramjet power plant propelling the first stage of a two stage to orbit launcher. The propulsion system consisted of a turbojet engine behind a rectangular ramp intake with the reheat system operating as a ramjet burner for flight beyond approximately Mach 3. The core engine was isolated from the airflow at these conditions. Several of the aspects of overall vehicle performance are described where these interact with the power plant design, and the influence of mission definition on power plant optimization is discussed.
Parametric Assessment of Propulsion System Mass for Airbreathing Launcher Configurations
1989
7 pages
Report
No indication
English
Propulsion System for Airbreathing Launcher in the French PREPHA Program
British Library Conference Proceedings | 1996
|Springer Verlag | 2007