H-I
The H-I rocket |
| Function |
Carrier rocket |
| Manufacturer |
Mitsubishi Heavy Industries |
| Country of origin |
 Japan |
| Size |
| Height |
42 metres (138 ft) |
| Diameter |
2.44 metres (8.0 ft) |
| Mass |
142,260 kilograms (313,600 lb) |
| Stages |
2 or 3 |
| Capacity |
Payload to
LEO |
3,200 kilograms (7,100 lb) |
Payload to
GTO |
1,100 kilograms (2,400 lb) |
| Associated rockets |
| Family |
Thor |
| Comparable |
Delta |
| Launch history |
| Status |
Retired |
| Launch sites |
LA-N, Tanegashima |
| Total launches |
9 |
| Successes |
9 |
| First flight |
12 August 1986 |
| Last flight |
11 February 1992 |
| Boosters (Stage 0) - Castor 2 |
| No boosters |
6 or 9 |
| Engines |
1 TX-354-3 |
| Thrust |
258.9 kilonewtons (58,200 lbf) |
| Specific impulse |
262 sec |
| Burn time |
37 seconds |
| Fuel |
Solid |
| First Stage - Thor-ELT |
| Engines |
1 MB-3-3 |
| Thrust |
866.7 kilonewtons (194,800 lbf) |
| Specific impulse |
290 sec |
| Burn time |
270 seconds |
| Fuel |
RP-1/LOX |
| Second Stage |
| Engines |
1 LE-5 |
| Thrust |
102.9 kilonewtons (23,100 lbf) |
| Specific impulse |
450 sec |
| Burn time |
370 seconds |
| Fuel |
LH2/LOX |
| Third Stage (optional) |
| Engines |
1 UM-129A |
| Thrust |
77.4 kilonewtons (17,400 lbf) |
| Specific impulse |
291 sec |
| Burn time |
68 seconds |
| Fuel |
Solid |
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. 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 licence produced in Japan for the N-I and N-II rockets. The second stage was entirely Japanese, using an LE-5 engine. On launches to Geosynchronous transfer orbits, a Nissan-produced UM-129A solid motor was used as a third stage. Depending on the mass of the payload, either six or nine US Castor 2 SRMs would be used as booster rockets.
[edit] Launch history
| Date/Time (GMT) |
S/N |
Payload |
Orbit |
Remarks |
| 12 August 1986, 20:45 |
15(F) |
EGP (Ajisai) |
LEO |
9 SRMs, 2 stages |
| 27 August 1987, 09:20 |
17(F) |
ETS-5 (Kiku-5) |
GTO |
9 SRMs, 3 stages |
| 19 February 1988, 10:05 |
18(F) |
CS-3A (Sakura-3A) |
GTO |
9 SRMs, 3 stages |
| 16 September 1988, 09:59 |
19(F) |
CS-3B (Sakura-3B) |
GTO |
9 SRMs, 3 stages |
| 5 September 1989, 18:11 |
20(F) |
GMS-4 (Himawari-4) |
GTO |
6 SRMs, 3 stages |
| 7 February 1990, 01:33 |
21(F) |
MOS-1B (Momo-1B) |
LEO |
9 SRMs, 2 stages |
| 28 August 1990, 09:05 |
22(F) |
BS-3A (Yuri-3A) |
GTO |
9 SRMs, 3 stages |
| 25 August 1991, 08:40 |
23(F) |
BS-3B (Yuri-3B) |
GTO |
9 SRMs, 3 stages |
| 11 February 1992, 01:50 |
24(F) |
JERS-1 (FUYO-1) |
LEO |
9 SRMs, 2 stages |
[edit] See also
[edit] References
- Wade, Mark. "Delta". Encyclopedia Astronautica. Retrieved 2008-08-31.
- McDowell, Jonathan. "Thor". Orbital and Suborbital Launch Database. Jonathan's Space Report. Retrieved 2008-08-31.
- Krebs, Gunter. "H-1". Gunter's Space Page. Retrieved 2008-08-31.
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- ‡ – Falcon 1 and 9 were designed for partial reuse, which was never achieved and has now been abandoned, however a fully-reusable Falcon 9 and Falcon Heavy are under long-term development.
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