Английская Википедия:H-I
Шаблон:Short description Шаблон:Infobox Rocket The H–I or H–1 was a Japanese liquid-fuelled carrier rocket, consisting of a licence-produced American first stage and set of booster rockets, and all-Japanese upper stages. The H in the name represented the use of liquid hydrogen fuel in the second stage. It was launched nine times between 1986 and 1992. It replaced the N-II, and was subsequently replaced by the H-II, which used the same upper stages with a Japanese first stage.
The first stage of the H–I was a licence-built version of the Thor-ELT, which was originally constructed for the US Delta 1000 rocket. The stage had already been produced under licence in Japan for the N-I and N-II rockets. The second stage was entirely Japanese, using an LE-5 engine, the first rocket engine in Japan to use a cryogenic fuel. On launches to Geosynchronous transfer orbits, a Nissan–built UM-69A solid motor was used as a third stage. Depending on the mass of the payload, either six or nine US Castor 2 SRMs were used as booster rockets.
Launch history
| Flight No. | Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Payload mass | Orbit | Customer | Launch outcome |
|---|---|---|---|---|---|---|---|---|
| 15(F) | 12 August 1986, 20:45 |
H-I | Osaki Launch Complex | EGP (Ajisai) | LEO | Шаблон:Success | ||
| 9 SRMs, 2 stages | ||||||||
| 17(F) | 27 August 1987, 09:20 |
H-I | Osaki Launch Complex | ETS-5 (Kiku-5) | GTO | Шаблон:Success | ||
| 9 SRMs, 3 stages | ||||||||
| 18(F) | 19 February 1988, 10:05 |
H-I | Osaki Launch Complex | CS-3A (Sakura-3A) | GTO | Шаблон:Success | ||
| 9 SRMs, 3 stages | ||||||||
| 19(F) | 16 September 1988, 09:59 |
H-I | Osaki Launch Complex | CS-3B (Sakura-3B) | GTO | Шаблон:Success | ||
| 9 SRMs, 3 stages | ||||||||
| 20(F) | 5 September 1989, 19:11 |
H-I | Osaki Launch Complex | GMS-4 (Himawari-4) | GTO | Шаблон:Success | ||
| 6 SRMs, 3 stages | ||||||||
| 21(F) | 7 February 1990, 01:33 |
H-I | Osaki Launch Complex | MOS-1B (Momo-1B) | LEO | Шаблон:Success | ||
| 9 SRMs, 2 stages | ||||||||
| 22(F) | 28 August 1990, 09:05 |
H-I | Osaki Launch Complex | BS-3A (Yuri-3A) | GTO | Шаблон:Success | ||
| 9 SRMs, 3 stages | ||||||||
| 23(F) | 25 August 1991, 08:40 |
H-I | Osaki Launch Complex | BS-3B (Yuri-3B) | GTO | Шаблон:Success | ||
| 9 SRMs, 3 stages | ||||||||
| 24(F) | 11 February 1992, 01:50 |
H-I | Osaki Launch Complex | JERS-1 (FUYO-1) | LEO | Шаблон:Success | ||
| 9 SRMs, 2 stages | ||||||||
When the H–1 was announced in 1986, company representative Tsuguo Tatakawe clarified that it would only be used to launch indigenous (i.e. Japanese) payloads, that only two launches per year could be mounted, and that the launch window consisted of a four-month period in which Japanese fishing fleets were not active (the falling launch boosters may damage fishing nets in the ocean waters).[1]
See also
- Delta rocket
- H-II
- H-IIA
- PGM-17 Thor
- Comparison of orbital launchers families
- Comparison of orbital launch systems
References
Шаблон:Expendable launch systems Шаблон:Japanese launch systems Шаблон:Mitsubishi Heavy Industries Шаблон:Thor and Delta rockets
- ↑ Japan's H–1 and H–2 rockets, Air & Space/Smithsonian, February/March 1987, p. 19
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