H-I Launch Vehicle

Operation Finished

Overview


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The H-I, which drew on the results from the development of the N-I and N-II launch vehicles, is a three-stage rocket created for responding to Japan's satellite launching needs of the late 1980's.
The H-I's first-stage and strap-on boosters are identical to those of the N-II. The second-stage engine (LE-5) and propellant, third stage solid propellant rocket motor and inertial guidance system are all products of Japan's technology.
The H-I which was utilized in a total of 9 launches from 1986 to 1991 are no longer in use but the technology used in developing the H-I was exploited for developing the H-II.


Main characteristics

Overall length 40.30m
Diameter 2.49m (Second stage)
Total weight 139.3t (payload not included)
Guidance system Inertial guidance system

Launch Records

Flight No.Launch DatePayload
H15F 8/13/1986 Experimental Geodetic Satellite "Ajisai"(EGS)
Magnetic Bearing Flywheel Experimental System "JINDAI"(MABES)
Japan Amateur Satellite-1 "FUJI-1"(JAS-1)
H17F 8/27/1987 Engineering Test Satellite V "KIKU-5"(ETS-V)
H18F 2/19/1988 Communication Satellite-3a "Sakura-3a"(CS3a)
H19F 9/16/1988 Communication Satellite-3a "Sakura-3a"(CS3a)
H20F 9/6/1989 Geostationary Meteorological Satellite-4 "Himawari-4"(GMS-4)
H21F 2/7/1990 Marine Observation Satellite-1b "Momo-1b"(MOS-1b)
Deployable Boom and Umprella Test "ORIZURU"(DEBUT)
Japan Amateur Satellite-1b "FUJI-2"(JAS-1b)
H22F 8/28/1990 Broadcasting Satellite-3a "Yuri-3a"(BS3a)
H23F 8/25/1991 Broadcasting Satellite-3b "Yuri-3b"(BS3b)
H24F 2/11/1992 Japanese Earth Resources Satellite-1 "FUYO-1"(JERS-1)