Development status of H-II rocket cryogenic propulsion systems
Abstract
The development of H-II launch vehicle was initiated by the National Space Development Agency of Japan in 1985 and has reached its final stage. Based on experiences of the H-I development, both the 1st and the 2nd stages of H-II rocket have employed advanced cryogenic propulsion systems to inject a 4 ton-class payload into geostationary transfer orbit. The second stage is powered by an upgraded version of the H-I's LE-5 cryogenic engine, LE-5A. The qualification firing tests of LE-5A completed in March, 1991 and the captive firing tests of the second stage system are under way. These test results show that its performance and reliability is satisfactory. The first stage uses a newly developed, high performance LH2/LOX engine, LE-7. In the course of the LE-7 development, some technical difficulties were encountered and lead to the delay of the engine qualification firing test and the 1st stage system firing test. This paper presents the current development status of the cryogenic propulsion systems for H-II launch vehicle, placing an emphasis on the test results.
- Publication:
-
Acta Astronautica
- Pub Date:
- 1992
- DOI:
- 10.1016/0094-5765(92)90017-D
- Bibcode:
- 1992AcAau..28..127K