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|
Liquid methane, etc.
|Year of completion||FY 1972, *1: FY 1978, *2: FY 2001|