Long March 2C
 |
|
| Function | Carrier rocket |
|---|---|
| Manufacturer | CALT |
| Country of origin | People's Republic of China |
| Size | |
| Height | 42 metres (138 ft) |
| Diameter | 3.35 metres (11.0 ft) |
| 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:
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.
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Wikipedia