Japan’s first, full-fledged combustion test facility conducted in a high altitude environment
Rocket engines used in the upper stage (2nd stage, 3rd stage) of a rocket will operate in high altitudes with very low pressure. Investigating factors including actual engine propulsion in an environment close to a vacuum and ignition performance is very important to the development and research of this engine. In light of this, a high altitude simulation test that can be conducted on ground is necessary. This facility is Japan’s first for conducting full-fledged combustion tests at a high altitude environment (altitude of around 30 km). Construction of this facility was completed in FY 1982. This facility is substantially contributing to rocket development in Japan, including the H-I rocket and H-II rocket.
| Department | Space Technology Directorate I |
|---|---|
| Propulsion level | approx. 20 kN |
| Exhaust capacity | 13 torr |
| Test time | approx. 100 seconds |
| Nozzle exit diameter | approx. 900 mm |
| Propellant | Liquid oxygen Liquid hydrogen Liquid methane, etc. |
| Year of completion | FY 1972, *1: FY 1978, *2: FY 2001 |
