Accession Number:
AD0387521
Title:
ADVANCED MANEUVERING PROPULSION TECHNOLOGY PROGRAM.
Descriptive Note:
Quarterly rept. no. 1, 1 Nov 67-31 Jan 68.
Corporate Author:
ROCKETDYNE CANOGA PARK CALIF
Personal Author(s):
Report Date:
1968-02-01
Pagination or Media Count:
380.0
Abstract:
Analysis and design effort on the Advanced Maneuvering Propulsion System AMPS was initiated. Engine system tradeoff studies for selection of the pump drive cycle and engine mixture ratio were completed and the basic engine design parameters were defined. Engine, thrust chamber, turbopump, and controls design analyses were started. The space and thermal environments of the propulsion system were established and design analysis was begun on the main propellant tanks. Engine critical component demonstration testing was accomplished on the main engine thrust chamber segment hardware. Successful operation at full design condition of 650 psia chamber pressure, injector mixture ratio of 141, and fuel injector inlet temperature of 1000 F was demonstrated with the fan-type injector design. Author
Descriptors:
- *LIQUID PROPELLANT ROCKET ENGINES
- *MANEUVERING SATELLITES
- LIQUID PROPELLANT ROCKET ENGINES
- LAUNCH VEHICLES
- TURBOPUMPS
- FUEL PUMPS
- COMBUSTION CHAMBERS
- ROCKET NOZZLES
- REGENERATIVE COOLING
- WALLS
- VIBRATION
- PROPELLANT TANKS
- SPACE ENVIRONMENTS
- SURFACE TEMPERATURE
- ACCELERATION
- WIND
- LIQUEFIED GASES
- HYDROGEN
- FLUORINE
- THRUST
- COMBUSTION CHAMBERS
- CRYOGENIC PROPELLANTS
- FUEL INJECTORS
- POLAR ORBIT TRAJECTORIES
- STORAGE
- HIGH TEMPERATURE
- RENDEZVOUS SPACECRAFT
- PRESSURE
Subject Categories:
- Liquid Propellant Rocket Engines
- Ground Support Systems and Facilities for Space Vehicles