Optimization criteria for HM60 engine design
Abstract
Thrust in vacuum and at sea level, combustion pressure, and differences between a staged combustion cycle (integrated flow) and a gas generator cycle (derived flow) were studied for the HM 60 engine. A 100 ton maximum derived flow engine is recommended.
- Publication:
-
In CNES The Future of Launchers in Europe
- Pub Date:
- 1982
- Bibcode:
- 1982cnes.rept..245B
- Keywords:
-
- Ariane Launch Vehicle;
- High Thrust;
- Liquid Propellant Rocket Engines;
- Optimization;
- Rocket Engine Design;
- Combustion Efficiency;
- Cost Reduction;
- Propulsion System Configurations;
- Propulsion System Performance;
- Rocket Thrust;
- Launch Vehicles and Space Vehicles