Long March 2C
Function | Carrier rocket |
---|---|
Manufacturer | CALT |
Country of origin | People's Republic of China |
Size | |
Height | 42 metres (138 ft)[1] |
Diameter | 3.35 metres (11.0 ft)[1] |
Mass | 233,000 kilograms (514,000 lb) |
Stages | 2 |
Capacity | |
Payload to LEO | 3,850 kilograms (8,490 lb) |
Payload to SSO |
2C: 1,400 kilograms (3,100 lb) 2C/SMA: 1,900 kilograms (4,200 lb) |
Payload to GTO | 2C/SM: 1,250 kilograms (2,760 lb) |
Associated rockets | |
Family | Long March |
Launch history | |
Status | Active |
Launch sites |
LA-2/138 & LA-4/SLS-2, JSLC LA-7 & LA-9, TSLC LA-3, XSLC |
Total launches | 41 |
Successes | 40 |
Failures | 1 |
First flight | 9 September 1982 |
First stage | |
Length | 25.72 m |
Diameter | 3.35 m |
Propellant mass | 162,706 kg (358,705 lb) |
Engines | 4 YF-21C |
Thrust | 2,961.6 kN (665,800 lbf) |
Specific impulse | 2,556.5 m/s (260.69 s) |
Fuel | N2O4/UDMH |
Second stage | |
Length | 7.757 m |
Diameter | 3.35 m |
Propellant mass | 54,667 kg (120,520 lb) |
Engines |
1 YF-24E (1 x YF-22E (Main)) (4 x YF-23C (Vernier)) |
Thrust |
741.4 kN (166,700 lbf) (Main) 47.1 kN (10,600 lbf) (Vernier) |
Specific impulse |
2,922.37 m/s (297.999 s) (Main) 2,834.11 m/s (288.999 s) (Vernier) |
Fuel | N2O4/UDMH |
Third stage - (optional) | |
Length | 1.5 m |
Diameter | 2.7 m |
Propellant mass | 125 kg (276 lb) |
Engines | 1 solid |
Thrust | 10.78 kN (2,420 lbf) |
Specific impulse | 2,804 m/s (285.9 s) |
Fuel | HTPB |
Long March 2C (LM-2C), or Chang Zheng 2C (CZ-2C) as in Chinese pinyin is a member of the Long March 2 rocket family, an expendable launch system operated by the People's Republic of China. This vehicle was developed by the China Academy of Launch Vehicle Technology, and the first launch occurred on September 9, 1982. It is a two-stage launch vehicle with storable propellants, consisting of Nitrogen Tetroxide and Unsymmetrical Dimethyl Hydrazine. The rocket was derived from the Long March 2A launch vehicle.
Several variants of this launch vehicle have been built, all using an optional third solid motor stage:[2]
- 2C/SD — Commercial satellite launcher with a multi-satellite smart dispenser allowing delivery of two satellites simultaneously
- 2C/SM — Version for delivery of small satellites to high orbits
- 2C/SMA — Improved version of the 2C/SM
List of launches
Flight number | Date (UTC) | Launch site | Upper stage (if used) | Payload | Orbit | Result |
---|---|---|---|---|---|---|
1 | September 9, 1982 07:19 |
LA-2/138, JSLC | FSW-0 No.4 | LEO | Success | |
2 | August 19, 1983 06:00 |
LA-2/138, JSLC | FSW-0 No.5 | LEO | Success | |
3 | September 12, 1984 05:44 |
LA-2/138, JSLC | FSW-0 No.6 | LEO | Success | |
4 | October 21, 1985 05:04 |
LA-2/138, JSLC | FSW-0 No.7 | LEO | Success | |
5 | October 6, 1986 05:40 |
LA-2/138, JSLC | FSW-0 No.8 | LEO | Success | |
6 | August 5, 1987 06:39 |
LA-2/138, JSLC | FSW-0 No.9 | LEO | Success | |
7 | September 9, 1987 07:15 |
LA-2/138, JSLC | FSW-1 No.1 | LEO | Success | |
8 | August 5, 1988 07:29 |
LA-2/138, JSLC | FSW-1 No.2 | LEO | Success | |
9 | October 5, 1990 06:14 |
LA-2/138, JSLC | FSW-1 No.3 | LEO | Success | |
10 | October 6, 1992 06:20 |
LA-2/138, JSLC | FSW-1 No.4 Freja |
LEO | Success | |
11 | October 8, 1993 08:00 |
LA-2/138, JSLC | FSW-1 No.5 | LEO | Success | |
12 | September 1, 1997 14:00 |
LA-7, TSLC | 2C/SD | Iridium mass simulator A Iridium mass simulator B |
LEO | Success |
13 | December 8, 1997 07:16 |
LA-7, TSLC | 2C/SD | Iridium 42 Iridium 44 |
LEO | Success |
14 | March 25, 1998 17:01 |
LA-7, TSLC | 2C/SD | Iridium 51 Iridium 61 |
LEO | Success |
15 | May 2, 1998 09:16 |
LA-7, TSLC | 2C/SD | Iridium 69 Iridium 71 |
LEO | Success |
16 | August 19, 1998 23:01 |
LA-7, TSLC | 2C/SD | Iridium 76 Iridium 78 |
LEO | Success |
17 | December 19, 1998 11:39 |
LA-7, TSLC | 2C/SD | Iridium 88 Iridium 89 |
LEO | Success |
18 | June 11, 1999 17:15 |
LA-7, TSLC | 2C/SD | Iridium 92 Iridium 93 |
LEO | Success |
19 | December 29, 2003 19:06 |
LA-3, XSLC | 2C/SM | Double Star 1 | HEO | Success |
20 | April 18, 2004 15:59 |
LA-3, XSLC | Shiyan-1 Nano Satellite 1 |
SSO | Success | |
21 | July 25, 2004 07:05 |
LA-7, TSLC | 2C/SM | Double Star 2 | HEO | Success |
22 | August 29, 2004 07:50 |
LA-4/SLS-2, JSLC | FSW-4 No.1 | LEO | Success | |
23 | November 18, 2004 10:45 |
LA-3, XSLC | Shiyan-2 | SSO | Success | |
24 | August 2, 2005 07:30 |
LA-4/SLS-2, JSLC | FSW-4 No.2 | LEO | Success | |
25 | September 9, 2006 07:00 |
LA-4/SLS-2, JSLC | Shijian 8 | LEO | Success | |
26 | April 11, 2007 03:27 |
LA-7, TSLC | Haiyang-1B | SSO | Success | |
27 | September 6, 2008 03:25 |
LA-7, TSLC | 2C/SMA | Huanjing-1A Huanjing-1B |
SSO | Success |
28 | April 22, 2009 02:55 |
LA-7, TSLC | Yaogan 6 | SSO | Success | |
29 | November 12, 2009 02:45 |
LA-4/SLS-2, JSLC | Shijian 11-01 | SSO | Success | |
30 | July 6, 2011 04:28 |
LA-4/SLS-2, JSLC | Shijian 11-03 | SSO | Success | |
31 | July 29, 2011 07:42 |
LA-4/SLS-2, JSLC | Shijian 11-02 | SSO | Success | |
32 | August 18, 2011 09:28 |
LA-4/SLS-2, JSLC | Shijian 11-04 | SSO | Failure | |
33 | November 29, 2011 18:50 |
LA-9, TSLC | Yaogan 13 | SSO | Success | |
34 | October 6, 2012 03:25 |
LA-9, TSLC | 2C/SMA | Shijian 9A Shijian 9B |
SSO | Success |
35 | November 18, 2012 22:53 |
LA-9, TSLC | Huanjing-1C Xinyan 1 Fengniao 1 |
SSO | Success | |
36 | July 15, 2013 09:27 |
LA-4/SLS-2, JSLC | Shijian 11-05 | SSO | Success | |
37 | October 29, 2013 02:50 |
LA-9, TSLC | Yaogan 18 | SSO | Success | |
38 | March 31, 2014 02:46 |
LA-4/SLS-2, JSLC | Shijian 11-06 | SSO | Success | |
39 | September 28, 2014 05:13 |
LA-4/SLS-2, JSLC | Shijian 11-07 | SSO | Success | |
40 | October 27, 2014 06:59 |
LA-4/SLS-2, JSLC | Shijian 11-08 | SSO | Success | |
41 | November 14, 2014 18:53 |
LA-9, TSLC | Yaogan 23 | SSO | Success | |
Launch failures
Shijian 11-04 launch failure
On August 18, 2011, a Long March 2C rocket failed during the launch of the Shijian 11-04 satellite. During the powered flight phase of the second stage, the connecting mechanism between vernier engine no.3 and the servo-control mechanism of the second stage failed, which led to loss of attitude control on the second stage.[3]
References
- 1 2 "LM-2C". China Great Wall Industry Corporation. Retrieved 9 August 2015.
- ↑ "Chang Zheng-2C (Long March-2C)". SinoDefence. Retrieved 9 August 2015.
- ↑ "Malfunction at devices connection blamed for orbiter launch failure". Xinhua News Agency. 6 September 2011. Retrieved 9 August 2015.
- "LM-2C USER'S MANUAL". CALT. 1999.
- Gunter Dirk Krebs. "CZ-2 (Chang Zheng-2)". Gunter's Space Page. Retrieved 9 August 2015.