Encyclopedia Astronautica
CZ-2C



cz2c.jpg
CZ-2C launch
Chinese orbital launch vehicle. The CZ-2C was the definitive low earth orbit launch vehicle derived from DF-5 ICBM. It became the basis for an entire family of subsequent Long March vehicles. Many adaptive modifications were made to the configuration of the CZ-2A to handle a variety of new satellites and upper stages. The CZ-2C had improved technical performance and payload capacity compared to the CZ-2A, with later versions having a payload capability of 2,800 kg into a 200 km circular orbit.

The CZ-2C could be launched from either the Jiuquan or Taiyuan launch sites. After its first FSW reconnaissance satellite mission on 9 September 1982 the CZ-2C launch vehicle successfully orbited six applications and two new recoverable satellites into space. On October 6, 1992, the Swedish Freja satellite was successfully launched as a co-passenger on the CZ-2C's thirteenth flight.

LEO Payload: 2,500 kg (5,500 lb) to a 200 km orbit at 52.00 degrees. Payload: 2,200 kg (4,800 lb) to a 200 km polar orbit. Launch Price $: 25.000 million in 1999 dollars.

Stage Data - CZ-2C

  • Stage 1. 1 x CZ-2C-1. Gross Mass: 153,000 kg (337,000 lb). Empty Mass: 10,000 kg (22,000 lb). Thrust (vac): 3,295.000 kN (740,745 lbf). Isp: 291 sec. Burn time: 122 sec. Isp(sl): 261 sec. Diameter: 3.35 m (10.99 ft). Span: 6.00 m (19.60 ft). Length: 20.52 m (67.32 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: YF-20A. Other designations: L-140. Status: In Production.
  • Stage 2. 1 x CZ-2C-2. Gross Mass: 39,000 kg (85,000 lb). Empty Mass: 4,000 kg (8,800 lb). Thrust (vac): 761.900 kN (171,282 lbf). Isp: 295 sec. Burn time: 130 sec. Isp(sl): 270 sec. Diameter: 3.35 m (10.99 ft). Span: 3.35 m (10.99 ft). Length: 7.50 m (24.60 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: YF-22A/23A. Other designations: L-35. Status: In Production.

AKA: Long March 2C; Chang Zheng 2C; Chang Zheng-2C.
Status: Active.
Gross mass: 192,000 kg (423,000 lb).
Payload: 2,500 kg (5,500 lb).
Height: 35.15 m (115.32 ft).
Diameter: 3.35 m (10.99 ft).
Thrust: 2,960.00 kN (665,430 lbf).
Apogee: 200 km (120 mi).
First Launch: 1975.11.26.
Last Launch: 2011.08.18.
Number: 29 .

More... - Chronology...


Associated Countries
Associated Spacecraft
  • FSW Chinese military surveillance satellite. 24 launches, 1974.11.05 (FSW-0) to 2006.09.09 (SJ-8). More...
  • Freja Swedish earth magnetosphere satellite. 2 launches, 1992.10.06 (Freja) and (Freja). Freja was designed to image the aurora and measure particles and fields in the upper ionosphere and lower magnetosphere. More...
  • HY-1 Chinese earth land resources satellite. Operational, launched from 2002.05.15 (Hai Yang 1). More...
  • Double Star Chinese earth magnetosphere satellite. 2 launches, 2003.12.29 (Tan Ce 1) to 2004.07.25 (Tan Ce 2). Double Star was a joint ESA - China project to supplement ESA's Cluster satellites in characterizing the earth's magnetosphere. More...
  • OlympicSat Chinese technology satellite. One launch, 2004.04.18, Naxing 1. It was announced in July 2001 would China will launch two small satellites on one rocket. The first would be an engineering test satellite developed by Tsinghua University. More...
  • Shiyan Chinese civilian surveillance satellite. 2 launches, 2004.04.18 (Tansuo 1) to 2008.11.05 (Shiyan Weixing 3). The first 'Experiment Satellite', with a mass of 204 kg, was China's first transmission-type small satellite capable of stereo mapping. More...
  • KOMPSAT-2 South Korean civilian surveillance satellite. One launch, 2006.07.28, Kompsat 2. More...
  • HJ-1 Chinese civilian surveillance satellite. 2 launches, 2008.09.06 (Huan Jing-1A) to 2008.09.06 (Huan Jing-1B). More...

Associated Engines
  • YF-20B Beijing Wan Yuan N2O4/UDMH rocket engine. 816.3 kN. In production. Isp=289s. Boosted CZ-2C, CZ-2D, CZ-2E, CZ-2E(A), CZ-3A, CZ-3B, CZ-3C, CZ-4A. First flight 1988. More...
  • YF-22A/23A Beijing Wan Yuan N2O4/UDMH rocket engine. 762 kN. Out of production. Cluster of YF-22A and 4 x YF-23 verniers. Isp=295s. Boosted CZ-2C, CZ-3. First flight 1975. More...
  • YF-20A Beijing Wan Yuan N2O4/UDMH rocket engine. 750.2 kN. Out of production. Isp=289s. Boosted CZ-2A, CZ-2C, CZ-2E(A), CZ-3, FB-1. First flight 1972. More...

See also
  • CZ China's first ICBM, the DF-5, first flew in 1971. It was a two-stage storable-propellant rocket in the same class as the American Titan, the Russian R-36, or the European Ariane. The DF-5 spawned a long series of Long March ("Chang Zheng") CZ-2, CZ-3, and CZ-4 launch vehicles. These used cryogenic engines for upper stages and liquid-propellant strap-on motors to create a family of 12 Long-March rocket configurations capable of placing up to 9,200 kg into orbit. In 2000 China began development of a new generation of expendable launch vehicles using non-toxic, high-performance propellants with supposedly lower operating costs. However these encountered development delays, and it seemed the reliable Long March series of rockets would continue in operational use for nearly fifty years before being replaced. More...

Associated Manufacturers and Agencies
  • CALT Chinese manufacturer of rockets, spacecraft, and rocket engines. China Academy of Launch Vehicle Technology, Beijing, China. More...

Associated Launch Sites
  • Jiuquan China's first launch center, also known as Shuang Cheng Tzu. Jiuquan Satellite Launch Centre, situated at 100 degrees East, 41 degrees North, is located in the Jiuquan Region, Gansu province, north-western China. It was China's first ballistic missile and satellite launch centre. More...
  • Taiyuan China's launch site for launch of polar orbiting satellites, also known as Wuzhai. Taiyuan Satellite Launch Center (TSLC) is situated in Kelan County, the northwest part of Shanxi Province, 280 km by road from Taiyuan City. More...
  • Xichang China's launch site for geosynchronous orbit launches. Xichang Satellite Launch Centre is situated in Xichang, Sichuan Province, south-western China. The launch pad is at 102.0 degrees East and 28.2 degrees North. The head office of the launch centre is located in Xichang City, about 65 kilometers away. Xichang Airport is 50 km away. A dedicated railway and highway lead directly to the launch site. More...
  • Jiuquan SLS CZ launch complex. New launch complex for the CZ-2F manned spacecraft launcher. Vehicle processed at nearby Vertical Assembly Facility. More...

Associated Stages
  • CZ-2C-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 39,000/4,000 kg. Thrust 761.90 kN. Vacuum specific impulse 295 seconds. More...
  • CZ-2C-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 153,000/10,000 kg. Thrust 3,295.00 kN. Vacuum specific impulse 291 seconds. More...

CZ-2C Chronology


1975 November 26 - . 03:29 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-1 (4).
  • FSW-0 No. 1 - . Payload: FSW-0 No. 01. Mass: 2,500 kg (5,500 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 2.00 days. Decay Date: 1975-12-29 . USAF Sat Cat: 8452 . COSPAR: 1975-111A. Apogee: 483 km (300 mi). Perigee: 183 km (113 mi). Inclination: 63.0000 deg. Period: 91.10 min. First orbital test of Chinese recoverable photo surveillance satellite. The spacecraft was brought down early, after three days in orbit, due to problems with the attitude control system cold gas supply. Along the skirt of the return capsule some wires and instruments were burnt during re-entry and capsule impacted far from its planned landing point. However usable film was obtained from the capsule. The Chinese Academy of Space Technology organised a team to determine the cause, and improvements were made in the next spacecraft of the model. Additional Details: here....

1976 December 7 - . 04:38 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-2 (5).
  • FSW-0 No. 2 - . Payload: FSW-0 No. 02. Mass: 2,500 kg (5,500 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 2.00 days. Decay Date: 1977-01-02 . USAF Sat Cat: 9587 . COSPAR: 1976-117A. Apogee: 489 km (303 mi). Perigee: 172 km (106 mi). Inclination: 59.4000 deg. Period: 91.10 min. Summary: Photo surveillance; film capsule recovered 9 December. First completely successful test of the FSW spy satellite. Many improvements in comparison to the first FSW orbited..

1978 January 26 - . 04:58 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-3 (6).
  • FSW-0 No. 3 - . Payload: FSW-0 No. 03. Mass: 2,500 kg (5,500 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 5.00 days. Decay Date: 1978-02-07 . USAF Sat Cat: 10611 . COSPAR: 1978-011A. Apogee: 507 km (315 mi). Perigee: 186 km (115 mi). Inclination: 57.0000 deg. Period: 91.40 min. Summary: Photo surveillance; film capsule; capsule returned January 30. Second fully successful FSW mission..

1982 September 9 - . 07:19 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-4 (7).
  • FSW-0 No. 4 - . Payload: FSW-0 No. 04. Mass: 2,500 kg (5,500 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 5.00 days. Decay Date: 1982-09-21 . USAF Sat Cat: 13521 . COSPAR: 1982-090A. Apogee: 392 km (243 mi). Perigee: 172 km (106 mi). Inclination: 63.0000 deg. Period: 90.20 min. Summary: Photo surveillance; film capsule recovered 14 September..

1983 August 19 - . 06:00 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-5 (8).
  • FSW-0 No. 5 - . Payload: FSW-0 No. 05. Mass: 2,500 kg (5,500 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 5.00 days. Decay Date: 1983-09-03 . USAF Sat Cat: 14288 . COSPAR: 1983-086A. Apogee: 493 km (306 mi). Perigee: 170 km (100 mi). Inclination: 63.3000 deg. Period: 91.20 min. Summary: Photo surveillance; film capsule recovered 24 August..

1984 September 12 - . 05:44 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-6 (11).
  • FSW-0 No. 6 - . Payload: FSW-0 No. 06. Mass: 2,500 kg (5,500 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 5.00 days. Decay Date: 1984-09-29 . USAF Sat Cat: 15279 . COSPAR: 1984-098A. Apogee: 398 km (247 mi). Perigee: 172 km (106 mi). Inclination: 67.9000 deg. Period: 90.20 min. Summary: Photo surveillance; film capsule recovered 17 September..

1985 October 21 - . 05:04 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-7 (12).
  • FSW-0 No. 7 - . Payload: FSW-0 No. 07. Mass: 2,500 kg (5,500 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 5.00 days. Decay Date: 1985-11-07 . USAF Sat Cat: 16177 . COSPAR: 1985-096A. Apogee: 393 km (244 mi). Perigee: 171 km (106 mi). Inclination: 63.0000 deg. Period: 90.20 min. Summary: Fanhui Shi Weixing photo surveillance satellite; film capsule recovered 26 October..

1986 October 6 - . 05:40 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-8 (14).
  • FSW-0 No. 8 - . Payload: FSW-0 No. 08. Mass: 2,500 kg (5,500 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 5.00 days. Decay Date: 1986-10-23 . USAF Sat Cat: 17001 . COSPAR: 1986-076A. Apogee: 337 km (209 mi). Perigee: 169 km (105 mi). Inclination: 57.0000 deg. Period: 89.60 min. Summary: Fanhui Shi Weixing recoverable satellite; capsule re-entered October 11 after five day mission..

1987 August 5 - . 06:39 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-9 (15).
  • FSW-0 No. 9 - . Payload: FSW-0 No. 09. Mass: 2,500 kg (5,500 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 5.00 days. Decay Date: 1987-08-23 . USAF Sat Cat: 18306 . COSPAR: 1987-067A. Apogee: 366 km (227 mi). Perigee: 169 km (105 mi). Inclination: 63.0000 deg. Period: 89.90 min. Summary: Fanhui Shi Weixing recoverable satellite; carried microgravity experiments; return capsule recovered August 10 after five days in space..

1987 September 9 - . 07:15 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-10 (16).
  • FSW-1 No. 1 - . Payload: FSW-1 No. 01. Mass: 2,100 kg (4,600 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 8.00 days. Decay Date: 1987-10-04 . USAF Sat Cat: 18341 . COSPAR: 1987-075A. Apogee: 222 km (137 mi). Perigee: 181 km (112 mi). Inclination: 63.0000 deg. Period: 88.50 min. Summary: Fanhui Shi Weixing recoverable satellite; return capsule recovered September 17 after eight days in space..

1988 August 5 - . 07:29 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-11 (18).
  • FSW-1 No. 2 - . Payload: FSW-1 No. 02. Mass: 2,100 kg (4,600 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 8.00 days. Decay Date: 1988-08-13 . USAF Sat Cat: 19368 . COSPAR: 1988-067A. Apogee: 311 km (193 mi). Perigee: 204 km (126 mi). Inclination: 63.0000 deg. Period: 89.70 min. Summary: German crystal growth experiment in recoverable capsule. Results marred by hard landing..

1990 October 5 - . 06:14 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-12 (25).
  • FSW-1 No. 3 - . Payload: FSW-1 No. 03. Mass: 2,100 kg (4,600 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Decay Date: 1990-10-23 . USAF Sat Cat: 20838 . COSPAR: 1990-089A. Apogee: 312 km (193 mi). Perigee: 208 km (129 mi). Inclination: 57.0000 deg. Period: 89.70 min. Summary: Fanhui Shi Weixing recoverable satellite; carried biological research experiments..

1992 October 6 - . 06:20 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. Launch Pad: LA2B?. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-13 (29).
  • Freja - . Payload: FSW-1 4 / Freja. Mass: 259 kg (570 lb). Nation: Sweden. Agency: SSC. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Freja. USAF Sat Cat: 22161 . COSPAR: 1992-064A. Apogee: 1,763 km (1,095 mi). Perigee: 590 km (360 mi). Inclination: 63.0000 deg. Period: 108.90 min. Ionospheric, auroral, amgnetospheric studies. Freja is a Swedish/German satellite designed for research into the aurora. The satellite was launched piggyback on a Long March 2C (CZ-2C) rocket and weighs 214 kg in orbit. It is a sun-pointing spinner (10 rpm) with a 2.2 m diameter. It will make high re solution measurements in the upper ionosphere and lower magnetosphere. Data will be received at Esrange, Kiruna, Sweden and at the Prince Albert Satellite Station in Canada's Saskatchewan Province. Launch time 0620 UT.
  • Freja - . Nation: Sweden. Agency: PRC. Spacecraft: Freja. USAF Sat Cat: 22161 . COSPAR: 1992-064xx. Apogee: 1,782 km (1,107 mi). Perigee: 521 km (323 mi). Inclination: 63.0000 deg. Period: 108.40 min.
  • FSW-1 No. 4 - . Payload: FSW-1 No. 04. Mass: 2,100 kg (4,600 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 6.00 days. Decay Date: 1992-10-31 . USAF Sat Cat: 22162 . COSPAR: 1992-064B. Apogee: 309 km (192 mi). Perigee: 213 km (132 mi). Inclination: 63.0000 deg. Period: 89.70 min. Summary: Fanhui Shi Weixing recoverable imaging satellite; carried remote sensing, microgravity experiments; capsule recovered October 13 after 6 days in orbit..

1993 October 8 - . 08:00 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. Launch Pad: LA2B?. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-14 (31).
  • FSW-1 No. 5 - . Payload: Jian Bing 93. Mass: 2,099 kg (4,627 lb). Nation: China. Agency: CASC. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Decay Date: 1993-10-28 . USAF Sat Cat: 22859 . COSPAR: 1993-063A. Apogee: 2,860 km (1,770 mi). Perigee: 181 km (112 mi). Inclination: 56.6000 deg. Period: 116.50 min. The only FSW-1 mission conducted during 1993-1994 was launched into an orbit of 209 km by 300 km at an inclination of 57.0 deg. In addition to an Earth observation Payload, FSW-1 5 carried microgravity research equipment and a diamond-studded medallion commemorating the 100th anniversary of Chairman Mao Tse-Tung's birth. The spacecraft operated normally until 16 October when an attempt to recover the satellite failed. An attitude control system failure aligned the spacecraft 90 deg from its desired position, causing the re-entry capsule to be pushed into a higher elliptical orbit (179 km by 3031 km) instead of returning to Earth. Natural decay did not bring the capsule back until March 12, 1996.

2003 December 29 - . 19:06 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. Launch Pad: LC1?. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-22 (75).
  • Tan Ce 1 - . Payload: Double Star 1, DSP-E. Mass: 350 kg (770 lb). Nation: China. Agency: SISE. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Double Star. Decay Date: 2007-10-14 . USAF Sat Cat: 28140 . COSPAR: 2003-061A. Apogee: 78,051 km (48,498 mi). Perigee: 555 km (344 mi). Inclination: 28.5000 deg. Summary: Equatorial member of a pair of Chinese-European magnetospheric research satellites carrying surplus instrumentation from the ESA Cluster program. First CZ-2C launch from Xichang..

2004 April 18 - . 15:59 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. Launch Pad: LC1?. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-23 (76).
  • Tansuo 1 - . Payload: Shiyan 1. Mass: 204 kg (449 lb). Nation: China. Agency: Harbin. Class: Technology. Type: Navigation technology satellite. Spacecraft: Shiyan. USAF Sat Cat: 28220 . COSPAR: 2004-012A. Apogee: 616 km (382 mi). Perigee: 598 km (371 mi). Inclination: 97.7000 deg. Period: 96.80 min. China's first transmission-type small satellite capable of stereo mapping. It was jointly designed by the Harbin Polytechnic University, Chinese Research Institute of Space Technology, Changchun Photomechanical Institute of the Chinese Academy of Sciences (CAS)and Xi'an Surveys and Designs Institute. The experiment satellite carried out photographic surveys of China's land resources, monitored the geographical environment and conducted scientific research on mapping. It was handed over for use to the Satellite Remote-Sensing Ground Station of CAS following the on-orbit testing.
  • Naxing 1 - . Mass: 25 kg (55 lb). Nation: China. Agency: Tsinghua. Class: Surveillance. Type: Military surveillance radar satellite. Spacecraft: OlympicSat. USAF Sat Cat: 28221 . COSPAR: 2004-012B. Apogee: 616 km (382 mi). Perigee: 599 km (372 mi). Inclination: 97.7000 deg. Period: 96.80 min. Summary: Naxing 1 (a contraction of Nami Weixing 'Nanosatellite') was designed for high-tech experiments. The satellite was developed and will be used by the elite Qinghua University and the Aerospace Qinghua Satellite Technologies Co. Ltd..
  • Unannounced Chinese satellite? - . Nation: China. Agency: PLA. Class: Surveillance. Type: Military surveillance radar satellite. Decay Date: 2004-08-21 . USAF Sat Cat: 28223 . COSPAR: 2004-012D. Apogee: 532 km (330 mi). Perigee: 339 km (210 mi). Inclination: 97.7000 deg. Period: 93.30 min. The announced mass of the two satellites launched was far less than the payload capability of the CZ-2C. It was believed that an unannounced military satellite may have been orbited. Object 2004-12D was in a much lower perigee orbit of 350 x 606 km x 97 deg and may have separated prior to second stage vernier cutoff.

2004 July 25 - . 07:05 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-24 (77).
  • Tan Ce 2 - . Payload: Double Star 2, DSP-P. Mass: 660 kg (1,450 lb). Nation: China. Agency: SISE. Manufacturer: DFH. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Double Star. USAF Sat Cat: 28382 . COSPAR: 2004-029A. Apogee: 38,574 km (23,968 mi). Perigee: 655 km (406 mi). Inclination: 90.0000 deg. Period: 695.10 min. Summary: Delayed from June, July 20.

2004 August 29 - . 07:50 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-25 (78).
  • FSW-3 No. 2 - . Payload: FSW-19. Mass: 2,100 kg (4,600 lb). Nation: China. Agency: SISE. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 26.67 days. Decay Date: 2004-11-07 . USAF Sat Cat: 28402 . COSPAR: 2004-033A. Apogee: 547 km (339 mi). Perigee: 168 km (104 mi). Inclination: 63.0000 deg. Period: 91.70 min. Recoverable satellite officially stated to be conducting space scientific research, land surveying, mapping and other scientific experiments. Said to have improved experimental technology, with higher orientation precision and more complex on-board computers and software. Controlled from the Xian Satellite Monitoring and Control Centre. Successfully re-entered and recovered after 27 days in space at 23:55 GMT on 24 September.

2004 November 18 - . 10:45 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. Launch Pad: LC1?. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-26 (83).
  • Shiyan Weixing 2 - . Payload: TANSUO 2. Mass: 300 kg (660 lb). Nation: China. Agency: SISE. Manufacturer: DFH. Class: Earth. Type: Earth resources satellite. Spacecraft: Shiyan Weixing. USAF Sat Cat: 28479 . COSPAR: 2004-046A. Apogee: 711 km (441 mi). Perigee: 694 km (431 mi). Inclination: 98.2000 deg. Period: 98.80 min. Summary: Remote Sensing Technology..

2005 August 2 - . 07:30 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-27 (86).
  • FSW-3 No. 4 - . Payload: FSW-21. Mass: 3,000 kg (6,600 lb). Nation: China. Agency: CAST. Manufacturer: SAST. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 27.00 days. Decay Date: 2005-08-29 . USAF Sat Cat: 28776 . COSPAR: 2005-027A. Apogee: 259 km (160 mi). Perigee: 153 km (95 mi). Inclination: 63.0000 deg. Period: 88.60 min. Summary: Military reconnaisance satellite, which maneuvered to raise its apogee on Aug 5 and 7 to a 166 x 552 km x 63.0 orbit; and again to the same altitude on Aug 19 after the apogee decayed to 535 km. Return capsule with film aboard recovered on 29 August..

2006 September 9 - . 07:00 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-28 (90).
  • SJ-8 - . Mass: 3,000 kg (6,600 lb). Nation: China. Agency: CASC. Manufacturer: SAST. Class: Technology. Type: Navigation technology satellite. Spacecraft: FSW. Duration: 14.82 days. Decay Date: 2006-11-01 . USAF Sat Cat: 29385 . COSPAR: 2006-035A. Apogee: 336 km (208 mi). Perigee: 173 km (107 mi). Inclination: 63.0000 deg. Period: 89.60 min. Summary: Long delayed Seed Satellite, an experiment in which a large payload of seeds were exposed to te space environment for two weeks. The modified FSW optical reconnaisance satellite capsule was recovered in Sichuan at 02:43 GMT on September 24..

2007 April 11 - . 03:27 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-29 (96).
  • Haiyang 1B - . Mass: 360 kg (790 lb). Nation: China. Agency: CASC. Manufacturer: DFH. Class: Earth. Type: Sea satellite. Spacecraft: HY-1. USAF Sat Cat: 31113 . COSPAR: 2007-010A. Apogee: 815 km (506 mi). Perigee: 782 km (485 mi). Inclination: 98.6000 deg. Period: 100.80 min. Summary: Oceanographic satellite equipped with a 10-band ocean color scanner, a 4-band CCD imager with 250-meter resolution, and an infrared water profile radiometer..

2008 September 6 - . 03:25 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: CZ-2C.
  • Huan Jing-1A - . Nation: China. Agency: SISE. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: HJ-1. USAF Sat Cat: 33320 . COSPAR: 2008-041A. Apogee: 662 km (411 mi). Perigee: 628 km (390 mi). Inclination: 98.0000 deg. Period: 97.60 min. Summary: 'Environment' satellites that carried visible and infrared sensors..
  • Huan Jing-1B - . Nation: China. Agency: SISE. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: HJ-1. USAF Sat Cat: 33321 . COSPAR: 2008-041B. Apogee: 672 km (417 mi). Perigee: 626 km (388 mi). Inclination: 98.0000 deg. Period: 97.70 min.

2009 April 14 - . 16:16 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: CZ-2C s/n CZ3C2.
  • Beidou G2 - . Mass: 3,100 kg (6,800 lb). Nation: China. Agency: SISE. Spacecraft: Beidou. USAF Sat Cat: 34779 . COSPAR: 2009-018A. Apogee: 35,799 km (22,244 mi). Perigee: 35,783 km (22,234 mi). Inclination: 0.7000 deg. Period: 1,436.30 min. Summary: Second of second generation operational Beidou navigation satellites..

2009 April 22 - . 02:55 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: CZ-2C s/n CZ2-32.
  • Yaogan 6 - . Nation: China. Agency: SISE. Spacecraft: Yaogan. USAF Sat Cat: 34839 . COSPAR: 2009-021A. Apogee: 512 km (318 mi). Perigee: 512 km (318 mi). Inclination: 97.6000 deg. Period: 94.90 min.

2009 November 12 - . 02:45 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2C.
  • SJ-11-01 - . Nation: China. Agency: SISE. Spacecraft: SJ-11. USAF Sat Cat: 36088 . COSPAR: 2009-061A. Apogee: 705 km (438 mi). Perigee: 688 km (427 mi). Inclination: 98.3000 deg. Period: 98.70 min. Summary: Experimental Satellite, believed to carry infrared surveillance system sensors..

2011 July 6 - . 04:28 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2C.
  • SJ-11-3 - . Nation: China. Spacecraft: SJ-11. USAF Sat Cat: 37730 . COSPAR: 2011-030A. Apogee: 702 km (436 mi). Perigee: 691 km (429 mi). Inclination: 98.2000 deg. Period: 98.70 min. Summary: Military satellite, believed to be equipped with infrared sensors, perhaps for ballistic missile launch detection..

2011 July 29 - . 07:42 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2C.
  • SJ-11-02 - . Nation: China. Spacecraft: SJ-11. USAF Sat Cat: 37765 . COSPAR: 2011-039A. Apogee: 705 km (438 mi). Perigee: 688 km (427 mi). Inclination: 98.1000 deg. Period: 98.70 min. Summary: Believed to carry infrared surveillance system sensors..

2011 August 18 - . 09:28 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2C. FAILURE: Second stage vernier engine suffered a mechanical failure.. Failed Stage: 2.
  • SJ11-04 - . Nation: China. Spacecraft: SJ-11. COSPAR: 2011-0F02. Summary: Fourth satellite of the SJ-11 infrared surveillance system failed to reach orbit when the second stage vernier engine suffered a mechanical failure..

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