The current status of a liquid propelled rocket engine conceptual design program undertaken in order to meet the low cost, high reliability requirements associated with future launching services, is reported. Studies performed in accordance with the following criteria are presented: reduced number of parts, integrated in a simplified architecture, use of low cost materials and manufacturing processes. These concentrate on the engine cycle and operating parameters determination, as well as on the design of main subsystems, such as the field turbopump, the gas generator, the nozzle extension and the valves. The engine overall layout, designed to make it as accessible as possible and hence reduce operational costs, is considered.
Conceptual Design of a High Thrust Vulcain-Derived Low-Cost Rocket Engine
1992
8 pages
Report
Keine Angabe
Englisch