![]() The N-II rocket | |
Function | Carrier rocket |
---|---|
Manufacturer | McDonnell Douglas (design) Mitsubishi Heavy Industries (production) |
Country of origin | United States (design) Japan (production) |
Size | |
Height | 35 m (114 ft 10 in) |
Diameter | 2.44 m (8 ft 0 in) |
Mass | 132,690 kg (292,530 lb) |
Stages | 2 or 3 |
Capacity | |
Payload to LEO | |
Mass | 2,000 kg (4,400 lb) |
Payload to GTO | |
Mass | 730 kg (1,610 lb) |
Associated rockets | |
Family | Delta |
Based on | N-I |
Derivative work | H-I |
Launch history | |
Status | Retired |
Launch sites | Tanegashima,Osaki |
Total launches | 8 |
Success(es) | 8 |
First flight | 11 February 1981 |
Last flight | 19 February 1987 |
Boosters –Castor 2 | |
No. boosters | 9 |
Maximum thrust | 258.9 kN (58,200 lbf) |
Specific impulse | 262 s (2.57 km/s) |
Burn time | 37 seconds |
Propellant | Solid |
First stage –Thor-ELT | |
Powered by | 1 × MB-3-3 |
Maximum thrust | 866.7 kN (194,800 lbf) |
Specific impulse | 290 s (2.8 km/s) |
Burn time | 270 seconds |
Propellant | RP-1 / LOX |
Second stage –Delta-F | |
Powered by | 1 × AJ-10-118F |
Maximum thrust | 41.3 kN (9,300 lbf) |
Specific impulse | 280 s (2.7 km/s) |
Burn time | 335 seconds |
Propellant | HNO3 / UDMH |
Third stage (optional) –Star-37E | |
Maximum thrust | 68 kN (15,000 lbf) |
Specific impulse | 284 s (2.79 km/s) |
Burn time | 42 seconds |
Propellant | Solid |
Third stage (optional) –Burner II | |
Maximum thrust | 43.6 kN (9,800 lbf) |
Specific impulse | 285 s (2.79 km/s) |
Burn time | 42 seconds |
Propellant | Solid |
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|isp}}ond 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.
Flight No. | Date / time (UTC) | Rocket, Configuration | Launch site | Payload | Payload mass | Orbit | Customer | Launch outcome |
---|---|---|---|---|---|---|---|---|
F7 | 11 February 1981 08:30 | Tanegashima,Osaki | ETS-4 (Kiku-3) [1] | GTO | Success | |||
F8 | 10 August 1981 20:03 | Tanegashima,Osaki | GMS-2 (Himawari-2) [2] | GTO | Success | |||
F10 | 4 February 1983 08:37 | Tanegashima,Osaki | CS-2A (Sakura-2A) [3] | GTO | Success | |||
F11 | 5 August 1983 20:29 | Tanegashima,Osaki | CS-2B (Sakura-2B) [3] | GTO | Success | |||
F12 | 23 January 1984 07:58 | Tanegashima,Osaki | BS-2A (Yuri-2A) [4] | GTO | Success | |||
F13 | 2 August 1984 20:30 | Tanegashima,Osaki | GMS-3 (Himawari-3) [2] | GTO | Success | |||
F14 | 12 February 1986 07:55 | Tanegashima,Osaki | BS-2B (Yuri-2B) [4] | GTO | Success | |||
F16 | 19 February 1987 01:23 | Tanegashima,Osaki | MOS-1 (Momo-1) [5] | LEO | Success | |||