Integrated modular propulsion for launch vehicles
Abstract
The paper proposes a modular approach to rocket propulsion which offers a versatile method for realizing the goals of low cost, safety, reliability, and ease of operation. It is shown that, using practical modules made up of only 4-6 individual elements, it is possible to achieve thrust levels of 2-3 mln lbf and more, using turbomachinery, thrust chambers, lines, and valves about the size of SSME hardware. The approach is illustrated by a LOX/LH2 configuration.
- Publication:
-
Joint Propulsion Conference and Exhibit
- Pub Date:
- June 1993
- Bibcode:
- 1993jpmc.confW....K
- Keywords:
-
- Design To Cost;
- Hydrogen Oxygen Engines;
- Launch Vehicle Configurations;
- Propulsion System Configurations;
- Systems Integration;
- Cost Effectiveness;
- Liquid Hydrogen;
- Liquid Oxygen;
- Low Cost;
- Spacecraft Propulsion and Power