N-I
Mitsubishi Heavy IndustriesRetired
The N-I or N-1 was a derivative of the American Thor-Delta rocket, produced under licence in Japan. It used a Thor-ELT first stage, a Mitsubishi Heavy Industries-designed LE-3 engine was used as a second stage, and three Castor SRMs. Seven were launched between 1975 and 1982, before it was replaced by the N-II.
Specifications
- Thrust
- 1,643 kN
- Height
- 34 m
- Diameter
- 2.44 m
- Launch mass
- 131 t
- Stages
- 3
- LEO capacity
- 1,200 kg
- GTO capacity
- 360 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
2success streakcurrent
First flight September 9, 1975 · latest September 3, 1982
Counted from padside's own launch record, the same basis as the stats page.
Flights per year
- Successful
- Failed
Show the numbers for N-I flights per year
| Year | Successful | Failed | Total |
|---|---|---|---|
| 1975 | 1 | 0 | 1 |
| 1976 | 1 | 0 | 1 |
| 1977 | 1 | 0 | 1 |
| 1978 | 1 | 0 | 1 |
| 1979 | 0 | 1 | 1 |
| 1980 | 1 | 0 | 1 |
| 1981 | 0 | 0 | 0 |
| 1982 | 1 | 0 | 1 |