Mission and concepts of orbital propulsion systems
Abstract
Medium thrust Earth storable bipropellant engine feasibility was studied. Representative mission types were analyzed in order to define thrust level. A mission model based on spacecraft masses in accordance with the ARIANE 3, 4 and 5 launch vehicle performance into low Earth orbit and STS masses of 5 to 25 tons was elaborated. With a constant thrust vector turn rate optimized for different accelerations and limitations for the payload loss (approx. 5 %) as well as for the burnout acceleration a thrust level between 4 kN and 12 kN covers the 67 missions investigated. Tandem and single tank configurations and feed system alternatives were examined. Engine length, performance and development cost criteria favor a 5 kN pressure-fed engine which can be uprated to a pump-fed 15 kN engine.
- Publication:
-
In CNES The Future of Launchers in Europe
- Pub Date:
- 1982
- Bibcode:
- 1982cnes.rept..275K
- Keywords:
-
- Ariane Launch Vehicle;
- Earth Orbits;
- Interplanetary Flight;
- Propulsion System Configurations;
- Propulsion System Performance;
- Spacecraft Propulsion;
- Feed Systems;
- Fuel Pumps;
- Fuel Tanks;
- Gas Generators;
- Liquid Rocket Propellants;
- Propellant Mass Ratio;
- Rocket Thrust;
- Turbine Pumps;
- Launch Vehicles and Space Vehicles