The N-II or N-2 was a derivative of the American Delta rocket, produced under licence in Japan. It replaced the N-I-rocket in Japanese use. It used a Thor-ELT first stage, a Delta-F second stage, nine Castor SRMs, and on most flights either a Star-37E or Burner-2 upper stage, identical to the US Delta 0100 series configurations. Eight were launched between 1981 and 1987, before it was replaced by the H-I, which featured Japanese-produced upper stages. All eight launches were successful.
Quick Facts Function, Manufacturer ...
 The N-II rocket |
Function | Carrier rocket |
---|
Manufacturer | McDonnell Douglas (design) Mitsubishi Heavy Industries (production) |
---|
Country of origin | United States (design) Japan (production) |
---|
|
Height | 35 metres (115 ft) |
---|
Diameter | 2.44 metres (8.0 ft) |
---|
Mass | 132,690 kilograms (292,530 lb) |
---|
Stages | 2 or 3 |
---|
|
|
Mass | 2,000 kilograms (4,400 lb) |
---|
|
Mass | 730 kilograms (1,610 lb) |
---|
|
---|
|
Family | Delta |
---|
|
Status | Retired |
---|
Launch sites | Tanegashima, Osaki |
---|
Total launches | 8 |
---|
Success(es) | 8 |
---|
First flight | 11 February 1981 |
---|
Last flight | 19 February 1987 |
---|
|
|
No. boosters | 9 |
---|
Powered by | 1 TX-354-3 |
---|
Maximum thrust | 258.9 kilonewtons (58,200 lbf) |
---|
Specific impulse | 262 sec |
---|
Burn time | 37 seconds |
---|
Propellant | Solid |
---|
|
Powered by | 1 MB-3-3 |
---|
Maximum thrust | 866.7 kilonewtons (194,800 lbf) |
---|
Specific impulse | 290 sec |
---|
Burn time | 270 seconds |
---|
Propellant | RP-1/LOX |
---|
|
Powered by | 1 AJ-10-118F |
---|
Maximum thrust | 41.3 kilonewtons (9,300 lbf) |
---|
Specific impulse | 280 sec |
---|
Burn time | 335 seconds |
---|
Propellant | HNO3/UDMH |
---|
|
Powered by | 1 solid |
---|
Maximum thrust | 68 kilonewtons (15,000 lbf) |
---|
Specific impulse | 284 sec |
---|
Burn time | 42 seconds |
---|
Propellant | Solid |
---|
|
Powered by | 1 solid |
---|
Maximum thrust | 43.6 kilonewtons (9,800 lbf) |
---|
Specific impulse | 285 sec |
---|
Burn time | 42 seconds |
---|
Propellant | Solid |
---|
|
|
Close