HI
The HI was a Japanese launcher . It was based on the Japanese N-II , which was an American Delta rocket built under license . Like the N-II, the HI consisted of a Thor lower level with 6 or 9 Castor II boosters , but compared to the N-II, a much larger upper level . This stage was powered by an LE-5 engine developed entirely in Japan . All launches of the 139 t rocket were successful, but because of the high price, a commercial payload was never carried. For GTO missions, the HI could be started with a third solid stage. It was first launched on March 13, 1986 (local time), the last on February 11, 1992.
Start chronicle
| Date (UTC) | S / N | payload | orbit | Remarks |
|---|---|---|---|---|
| August 12, 1986, 8:45 pm | 15 (F) | EGS (Ajisai), JAS 1 | LEO | 9 boosters, 2 levels |
| August 27, 1987, 9:20 am | 17 (F) | ETS-5 ( Kiku-5 ) | GTO | 9 boosters, 3 levels |
| February 19, 1988, 10:05 | 18 (F) | CS-3A ( Sakura-3A ) | GTO | 9 boosters, 3 levels |
| September 16, 1988, 9:59 am | 19 (F) | CS-3B ( Sakura-3B ) | GTO | 9 boosters, 3 levels |
| September 5, 1989, 6:11 pm | 20 (F) | GMS-4 ( Himawari-4 ) | GTO | 6 boosters, 3 levels |
| 7 February 1990, 1:33 | 21 (F) | MOS-1B ( Momo-1B ), JAS 1B | LEO | 9 boosters, 2 levels |
| August 28, 1990, 9:05 am | 22 (F) | BS-3A ( Yuri-3A ) | GTO | 9 boosters, 3 levels |
| 25 August 1991, 8:40 am | 23 (F) | BS-3B ( Yuri-3B ) | GTO | 9 boosters, 3 levels |
| 11 February 1992, 1:50 | 24 (F) | JERS-1 ( FUYO-1 ) | LEO | 9 boosters, 2 levels |
Technical specifications
The first stage engines use RP-1 and liquid oxygen (LOX) as fuel, the upper stage engines use liquid oxygen and hydrogen. The boosters and the optional third stage worked on solid fuel. The satellites were housed in a payload fairing almost 8 m long, 2.44 m in diameter and 600 kg in weight.
| Model | HI |
|---|---|
| stages | 2-3 + boosters |
| height | 40-42 m |
| diameter | 2.44 m |
| Takeoff mass | 139 t |
| Start thrust | ??? |
| payload | 3,200 kg LEO 1,100 kg GTO |
| 0th level | |
| Type | Castor 2 |
| number | 6 or 9 |
| height | 7.25 m |
| diameter | 0.79 m |
| Empty mass | 0.696 t |
| Takeoff mass | 4,424 t |
| Engine | TX-354-5 with 259 kN thrust |
| Burn time | 37 p |
| 1st stage | |
| Type | Thor-ELT |
| height | 22.4 m |
| diameter | 2.44 m |
| Empty mass | 4.4 t |
| Takeoff mass | 85.8 t |
| Engine | an MB-3-3 with 867 kN thrust |
| Burn time | 270 s |
| 2nd stage | |
| Type | SSPS-H-1 |
| height | 10.32 m |
| diameter | 2.49 m |
| Empty mass | 1.8 t |
| Takeoff mass | 10.7 t |
| Engine | an LE-5 with 103 kN thrust |
| Burn time | 433 s |
| 3rd level (optional) | |
| Type | UM 129A |
| height | 2.34 m |
| diameter | 2.44 m |
| Empty mass | 0.36 t |
| Takeoff mass | 2.2 t |
| Engine | a UM-129A with 77.45 kN thrust |
| Burn time | 68 p |
