抄録
The present application of liquid hydrogen in Japan is essentially limited to the space program. The development of the second stage propulsion system, which is intended for installation in the H-I launch vehicle for the 500-kg class geostationary satellite, has been performed by National Space Develoment Agency of Japan. The 10-ton-thrust class LOX/LH2 rocket engine will be used as the engine for the second stage propulsion system, and the basic research for this rocket engine has been carried out by using the firing test facility for a LOX/LH2 rocket engine.
This paper describes theoretically and experimentally heat transfer characteristics such as the cool-down and evaporation rate of runtanks for this firing test facility.
