H-II
H-II familyMitsubishi Heavy IndustriesRetired
The H-II rocket was a Japanese satellite launch system which flew seven times between 1994 and 1999 with 5 successes. It was developed by NASDA in order to give Japan a capability to launch larger satellites in the 1990s. It was the first two stage liquid fuelled rocket Japan made using only domestic technologies.
Specifications
- Thrust
- 4,158 kN
- Height
- 49 m
- Diameter
- 4 m
- Launch mass
- 260 t
- Stages
- 2
- LEO capacity
- 10,060 kg
- GTO capacity
- 3,930 kg
Specifications from Launch Library. Figures the operator has not published are omitted.
Flight record
7flightswith a definitive outcome
85.7%success rate6 of 7
1failureincluding partial failures
0success streakcurrent
First flight February 3, 1994 · latest November 15, 1999
Counted from padside's own launch record, the same basis as the stats page.
Flights per year
- Successful
- Failed
Show the numbers for H-II flights per year
| Year | Successful | Failed | Total |
|---|---|---|---|
| 1994 | 2 | 0 | 2 |
| 1995 | 1 | 0 | 1 |
| 1996 | 1 | 0 | 1 |
| 1997 | 1 | 0 | 1 |
| 1998 | 1 | 0 | 1 |
| 1999 | 0 | 1 | 1 |