N-I (rocket)

This article is about the Japanese rocket. For the Soviet rocket, see N1 rocket.

N-I

The N-I rocket[1]
Function	Carrier rocket
Manufacturer	Mitsubishi Heavy Industries
Country of origin	USA (design)  Japan (production)
Size
Height	34 metres (112 ft)[1]
Diameter	2.44 metres (8.0 ft)
Mass	131,330 kilograms (289,500 lb)[1]
Stages	2 or 3
Capacity
Payload to LEO	1,200 kilograms (2,600 lb)[1]
Payload to GTO	360 kilograms (790 lb)[1]
Associated rockets
Family	Delta
Launch history
Status	Retired
Launch sites	LA-N, Tanegashima
Total launches	7
Successes	6
Failures	1
Maiden flight	9 September 1975
Last flight	3 September 1982
Boosters (Stage 0) - Castor 2
No boosters	3[2]
Engines	1 TX-354-3
Thrust	258.9 kilonewtons (58,200 lbf)
Specific impulse	262 sec
Burn time	37 seconds
Fuel	Solid
First Stage - Thor-ELT
Engines	1 MB-3-3
Thrust	866.7 kilonewtons (194,800 lbf)
Specific impulse	290 sec
Burn time	270 seconds
Fuel	RP-1/LOX
Second Stage
Engines	1 LE-3
Thrust	52.9 kilonewtons (11,900 lbf)
Specific impulse	290 sec
Burn time	246 seconds
Fuel	NTO/A-50
Third Stage (optional) - Star-37N
Engines	1 solid
Thrust	45 kilonewtons (10,000 lbf)
Specific impulse	290 sec
Burn time	42 seconds
Fuel	Solid

The N-I or N-1 was a derivative of the American 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,^[3][4][5] and three Castor SRMs.^[2][6] Seven were launched between 1975 and 1982, before it was replaced by the N-II. Six of the seven launches were successful, however on the fifth flight, there was recontact between the satellite and the third stage, which caused the satellite to fail.

On 29 February 1976, the second N-I conducted the only orbital launch to occur on a leap day (as of year 2008).

Launch history

Date/Time (GMT)	S/N	Payload	Orbit	Remarks
9 September 1975, 05:30[7]	1(F)	ETS-1 (JETS-1/Kiku-1)	LEO
29 February 1976, 03:30[7]	2(F)	ISS-1 (JISS-1/Ume-1)	LEO
23 February 1977, 08:50[7]	3(F)	ETS-2 (Kiku-2)	GTO	3rd stage used
15 February 1978, 04:00[7]	4(F)	ISS-2 (JISS-2/Ume-2)	LEO
6 February 1979, 08:46[7]	5(F)	ECS-A (Ayame-1)	GTO	3rd stage used Failure – Recontact between satellite and upper stage.
22 February 1980, 08:35[7]	6(F)	ECS-B (Ayame-2)	GTO	3rd stage used
3 September 1982, 05:00[7]	9(F)	ETS-3 (Kiku-3)	LEO

See also

• Delta rocket
• H-I
• H-II
• H-IIA
• PGM-17 Thor

References

1. ^ ^{a b c d e} Wade, Mark. "Delta". Encyclopedia Astronautica. http://www.astronautix.com/lvs/delta.htm. Retrieved 3 September 2008. 
2. ^ ^{a b} "JAXA Digital Archives". Japan Aerospace Exploration Agency. http://jda.jaxa.jp/jda/p1_e.php. Retrieved 1 October 2009. 
3. ^ "N-Iロケット開発の歩み". Yukihiko Takenaka, NASDA. http://www.journalarchive.jst.go.jp/jnlpdf.php?cdjournal=jjsass1969&cdvol=32&noissue=362&startpage=127&lang=ja&from=jnlabstract. Retrieved 10 February 2011. 
4. ^ "三菱重工 名古屋誘導推進システム製作所 事業所紹介 沿革". Mitsubishi Heavy Industries. http://202.228.55.2/ngpsw/introduction/history/index.html. Retrieved 10 February 2011. 
5. ^ "第1部 創造性豊かな科学技術を求めて 第2章 自主技術開発への展開 第3節 先導的・基盤的科学技術分野における自主技術開発の展開 2.宇宙開発". Ministry of Education, Culture, Sports, Science and Technology. http://www.mext.go.jp/b_menu/hakusho/html/hpaa198201/hpaa198201_2_030.html. Retrieved 10 February 2011. 
6. ^ Krebs, Gunter. "N-1". Gunter's Space Page. http://space.skyrocket.de/doc_lau_det/n-1.htm. Retrieved 31 August 2008. 
7. ^ ^{a b c d e f g} McDowell, Jonathan. "Thor". Orbital and Suborbital Launch Database. Jonathan's Space Report. http://planet4589.org/space/lvdb/launch/Thor. Retrieved 31 August 2008.