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