Payload ratio of a single-stage-to-orbit vehicle with several propulsive modes
Abstract
The relation between the payload ratio of a single-stage-to-orbit (SSTO) vehicle and its velocity increment capability is studied. Examples of payload ratio calculations as a function of the propellant ratio for two and three propulsive phases are presented. It is observed that air breathing has the potential for increasing the performance and flexibility of satellite launch vehicles and for making the development of SSTO vehicles possible.
- Publication:
-
Innsbruck International Astronautical Federation Congress
- Pub Date:
- October 1986
- Bibcode:
- 1986inns.iafcS....V
- Keywords:
-
- Payload Mass Ratio;
- Propulsion System Configurations;
- Single Stage To Orbit Vehicles;
- Propellant Mass Ratio;
- Launch Vehicles and Space Vehicles