 High Altitude for Rocket Engine Test Facility |
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The rocket engine is used for the upper stage while the launch vehicles
are operating in high altitude environment, which is extremely low
atmospheric pressure. In developing the rocket engine, the vacuum
specific impulse and ignition properties of the engine in high altitude
environment are the most important parameters affecting engine performance.
The simulated altitude is approximately 30 km in this facility and
it's the first one made in Japan. It has been used for the development
of H-I and H-II launch vehicle.
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The picture above show's the rocket engine high altitude test facility
(under combustion test). The exhaust system of the facility consists
of a two-stage sSection ejector and super-sonic diffusers connected to
a liquid rocket engine test capsule.
Click to enlarge
Performance test of a reaction control system (RCS) 1200 N thrust engine
composed of a carbon/carbon composite coated with C/Sic FGM is under
way in an high altitude environment.
Main Characteristics
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Engines to be tested
- Propulsion: 100kN (mas)
- Horizontal Stand with Gimbals
- Propellant: LOX/liquid hydogen, liquified natural gas, gaseous
hydrogen and gaseous methane
Gas plant (charge and discharge gas)
- Discharge system: diffuser and sSection driven double-banked ejector
- Boiler pressure: 4.3MPa (saturate)
- SSection accumulater pressure: 4.2MPa
- SSection ejector pressure: 1.3MPa
- SSection volume: 1.7kg/s
- SSection generate volume: 160kg/s x 180s
- First stage sSection flow rate: 40kg/s
- Second stage sSection flow rate: 120kg/s
- Test pressure at egnition: 4kPa
at Steady combustion: 1kPa (for Liquid rocket engine with 50kN of propulsion)
Measurement facility
- Degital: 63ch
- Analog: 12ch
Completion: FY1972 |
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