N-II (rocket)

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.

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

Launch history

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

See also

• Comparison of orbital launchers families
• Delta rocket
• H-I
• H-II
• H-IIA
• N-I rocket
• PGM-17 Thor