An air-breather-based three-stage-to-orbit reusable launch system is proposed. The first and the second reusable winged stages use turboramjet and scramjet engines, respectively. The rocket-powered third stage is expendable. The present system is designed to insert an unmanned 2 ton payload to 300 km circular orbit inclined at 52°. The mission abort cases are also examined. To enhance the operational effectiveness, the landing sites for the first and die second stages are chosen to be at the same location. The calculations are made for the cases where this system is used in Japan, die United States, and between India and Indonesia It is shown that the present three-stage-to-orbit launch system can exploit the potential benefit of the scramjet propulsion.
|Publication status||Published - 1998|
|Event||36th AIAA Aerospace Sciences Meeting and Exhibit, 1998 - Reno, United States|
Duration: 1998 Jan 12 → 1998 Jan 15
|Other||36th AIAA Aerospace Sciences Meeting and Exhibit, 1998|
|Period||98/1/12 → 98/1/15|
ASJC Scopus subject areas
- Space and Planetary Science