Effects of rocket engine on single-stage-to-orbit vehicle

Introduction W ITH progress in liquid rocket engines and vehicle materials and design, the rocket-engine-powered, single-stage-toorbit vehicle is now feasible and practical. For the next-generation vehicle, it is economical to develop the fully reusable single-stageto-orbit vehicle. The launch cost of the single-stage-to-orbit vehicle is related to the vehicle dry mass because the vehicle with less dry mass will cost less to launch. So for the rocket-engine-powered, single-stage-to-orbit vehicle, it is important to assess the effects of the liquid rocket engine on the vehicle dry mass. This Note analyzes the effects of the main propulsion system on the dry mass of the single-stage-to-orbit vehicle, the propulsion system being made up of the existing and new liquid rocket engines. For the Space Shuttle main engine (SSME)-derivative-engine-powered, single-stage-to-orbit vehicle, the effects of the engine expansion ratio, specific impulse, and mass on the vehicle dry mass are also calculated with the payload fixed.