N-I (rocket)
 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 (289,530 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 |
| Partial failures | 1 |
| First flight | 9 September 1975 |
| Last flight | 3 September 1982 |
| Boosters - 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 |
Mock up of N-1
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
References
- 1 2 3 4 5 Wade, Mark. "Delta". Encyclopedia Astronautica. Retrieved 3 September 2008.
- 1 2 "JAXA Digital Archives". Japan Aerospace Exploration Agency. Retrieved 1 October 2009.
- ↑ "N-Iロケット開発の歩み". Yukihiko Takenaka, NASDA. Retrieved 10 February 2011.
- ↑ "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. Retrieved 10 February 2011.
- ↑ "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. Retrieved 10 February 2011.
- ↑ Krebs, Gunter. "N-1". Gunter's Space Page. Retrieved 31 August 2008.
- 1 2 3 4 5 6 7 McDowell, Jonathan. "Thor". Orbital and Suborbital Launch Database. Jonathan's Space Report. Retrieved 31 August 2008.
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