Encyclopedia Astronautica
CZ



qczfam2.jpg
CZ
Credit: (c) Mark Wade
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.

Tsien Hsue-Shen, America's leading theoretician in rocket and high-speed flight theory, returned to his native China in 1955. He assisted in negotiation of a 1956 agreement with the Soviet Union for transfer of rocket and nuclear technology to China, including training of Chinese students at Russian universities. However building rocket technology in China was a long process. Achieving the indigenous technologies in metallurgy, machinery, and electronics was an enormous task The Russians provided an R-2 rocket, an improved version of the V-2, as a starting point. But in 1960 the Soviet government discontinued further cooperation with China. Nevertheless later that year Tsien launched the first Chinese-built R-2.

Chinese political upheavals - the Great Leap Forward, the Cultural Revolution, Tsien's backing of the disgraced Lin Biao - further delayed progress. Nevertheless by 1971 China had tested its first ICBM (the DF-5). China's space industry developed new cryogenic engines and used a modular approach to create a family of 12 Long-March rocket configurations based on the CZ-2 design capable of placing up to 9,200 kg into orbit. China launched 27 foreign-made satellites in 1985-2000. However then a US embargo over improper technology transfer and collapse of the MEO satellite market led to a sharp reduction in commercial launches. China established three land-locked launch sites to reach various orbits. These were Jiuquan, for launch to mid-inclination orbits, Xichang for launch to geosynchronous orbit, and Taiyuan for polar orbits.

In April 1992 the Chinese leadership decided that an independent manned space program could be afforded. New launch facilities were built at the Jiuquan launch site for the CZ-2F manned launch vehicle. The project culminated in the launch of China's first astronaut in 2003. China's ten-year space objectives established in 2000 included development of a new generation of expendable launch vehicles using non-toxic, high-performance propellants with 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... - Chronology...


Associated Spacecraft
  • Oscar International series of amateur radio communications satellites. Operational, first launch 1961.12.12. Launched in a variety of configurations and by many nations. More...
  • JSSW Chinese military surveillance satellite. 6 launches, 1973.09.18 (JSSW 1) to 1976.11.10 (JSSW 6). Mysterious early Chinese satellite, orbited by the cancelled FB-1 launch vehicle. More...
  • FSW Chinese military surveillance satellite. 24 launches, 1974.11.05 (FSW-0) to 2006.09.09 (SJ-8). More...
  • SJ Chinese communications technology satellite. First launch 1979.07.28. SJ (Shijian) series were Chinese scientific research, technological experiment and military operational satellites of a variety of configurations. More...
  • HS 376 American communications satellite. 56 launches, 1980.11.15 (SBS 1) to 2003.09.27 (E-Bird). Mass 654 kg at beginning-of-life in geosynchronous orbit. Spin stabilized at 50 rpm by 4 hydrazine thrusters with 136 kg propellant. More...
  • DFH-2 Chinese military communications satellite. 7 launches, 1984.01.29 (STTW-T1) to 1991.12.28 (Zhongxing-4). The DFH-2 was a spin-stabilized, drum-shaped military communications satellite with a despun antenna, a diameter of 2.1 m, and a height of 3.1 m. More...
  • FY-1 Chinese earth weather satellite. 4 launches, 1988.09.06 (FY-1A) to 2002.05.15 (SJ-6A). The Feng Yun 1 meteorological satellites were launched into sun-synchronous 900 km, 99 deg inclination orbits by CZ-4 boosters from Taiyuan. More...
  • FS-1300 American communications satellite bus. Operational, first launch 1989.06.05. More...
  • HS 601 American communications satellite bus. First launch 1990.01.09. 3-axis unified ARC 22 N and one Marquardt 490 N bipropellant thrusters, Sun and Barnes Earth sensors and two 61 Nms 2-axis gimbaled momentum bias wheels. More...
  • Badr Pakistani communications technology satellite. 3 launches, 1990.07.16 (Badr-A) to 2008.07.07 (Badr B). Pakistani experimental series with a variety of payloads. 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...
  • AS 7000 American communications satellite. 13 launches, 1993.12.16 (Telstar 401) to 1998.06.18 (Intelsat 805). 3-axis stabilized. Two large solar panels with 1-axis articulation. More...
  • DFH-3 Chinese military communications satellite using indigenous technologies. Operational, first launch 1994.02.08. More...
  • AS 2100 American communications satellite. Operational, first launch 1996.09.08 (GE 1). Cost per satellite $100 million for the spacecraft including ground support equipment, but not including launch costs. 3-axis stabilized. More...
  • LM 700 American communications satellite. 98 launches, 1997.05.05 (Iridium 8) to 2002.06.20 (Iridium SV98 ). The LM 700 had its first use in the Iridium system, a commercial communications network comprised of a minimum of 66 LEO spacecraft. More...
  • FY-2 Chinese earth weather satellite. 5 launches, 1997.06.10 (FY-2A) to 2008.12.23 (FY-2C). The Feng Yun 2 spin-stabilized geosynchronous meteorological spacecraft was slightly more massive than China's DFH-2 communications satellite. More...
  • SACI Brazilian technology satellite. 2 launches, 1999.10.14 (SACI 1) and 1999.12.11 (SACI-2). INPE experimental scientific satellites; carried a magnetometer, particle detectors and an atmospheric experiment. More...
  • ZY Chinese earth land resources satellite. 6 launches, 1999.10.14 (ZY-1) to 2007.09.19 (ZY-2C). From 1985 China and Brazil jointly developed a sun synchronous imaging satellite bus, the Zi Yuan-1 (Resouce-1) based on the Shi Jian 3 design. More...
  • Shenzhou Chinese manned spacecraft. Operational, first launch 1999.11.19. The Chinese Shenzhou manned spacecraft resembled the Russian Soyuz spacecraft, but was of larger size and all-new construction. More...
  • FH-1 Chinese military communications satellite. 2 launches, 2000.01.25 (Zhongxing-22) to 2006.09.12 (Zhongxing 22A). In May 1999 Aviation Week reported that a new communication satellite, Fenghuo-1 (FH-1), would be launched by a CZ-3A by the end of 1999. More...
  • Beidou Chinese navigation satellite. Operational, first launch 2000.10.30. Beidou ('Big Dipper') was the satellite component of an independent Chinese satellite navigation and positioning system. More...
  • HY-1 Chinese earth land resources satellite. 2 launches, 2002.05.15 (Hai Yang 1) to 2007.04.11 (Haiyang 1B). More...
  • Shenzhou OM Chinese manned spacecraft module. Operational, first launch 1999.11.19. The orbital module provided quarters for the crew during the space mission, and could be fitted out with different internal and external equipment according to mission requirements. More...
  • CX-1 Chinese communications technology satellite. 2 launches, 2003.10.21 (CX-1) and 2008.11.05 (Chuanxin-1-02). 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...
  • SJ-6 Chinese military naval signals reconnaisance satellite. Operational, first launch 2004.09.08. More...
  • Spacebus 4000 European communications satellite bus. Operational, first launch 2005.02.03. The Spacebus 4000 represented a new larger platform to meet customer demand. More...
  • Yaogan Chinese synthetic aperture radar military surveillance radar and ELINT satellite. Operational, first launch 2006.04.26. More...
  • DFH-4 Large Chinese communications satellite bus using a blend of Chinese and subcontracted European technologies. Operational, first launch on 2006.10.28 (Xinnuo 2). More...
  • Zheda Pixing Chinese technology satellite. Experimental microelectronics research picosatellite. Launched 2007.05.25, More...
  • Chang'e Chinese unmanned lunar orbiter. Two launched, 2007.10.24 and 2010.10.01. Originally announced in March 2003 with the first spacecraft to reach the moon by the end of 2005. More...
  • FY-3 Chinese new generation polar orbit weather satellite. Operational, first launched 2008.05.27. The FY-3 was equipped with new global, all-weather, multi-spectral, three-dimensional sensors. More...
  • HJ-1 Chinese civilian surveillance satellite. 2 launches, 2008.09.06 (Huan Jing-1A) to 2008.09.06 (Huan Jing-1B). More...
  • Ban Xing Chinese technology satellite. One launch, 2008.09.25, BX-1. BanXing (companion satellite) subsatellite released by Shenzhou. If maneuvered away and back to the Shenzhou orbital module after the mission. More...

Associated Launch Vehicles
  • CZ Chinese orbital launch vehicle. 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...
  • DF-5 Development of the the DF-5 began in 1964. The goal was an ICBM capable of reaching the United States. Although deployed in very limited numbers as an ICBM, this rocket became the basis for an entire family of space launch vehicles and the foundation of the Chinese space program. More...
  • FB-1 Chinese orbital launch vehicle. The FB-1, like the CZ-2 launch vehicle begun the following year, was a two-stage booster developed from the DF-5 intercontinental ballistic missile. Payload for the booster was the JSSW, believed to have been a television-transmission military reconnaissance satellite. The incredible decision to develop two nearly identical rockets concurrently can be blamed on the turbulent factional politics after the Cultural Revolution. More...
  • CZ-2A Chinese orbital launch vehicle. The CZ-2 was originally designed for launch of the FSW-1 recoverable military reconnaissance satellite. More...
  • CZ-2C 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. More...
  • CZ-2 Spaceplane Launcher Chinese orbital launch vehicle. Tsien's manned spacecraft design proposed in the late 1970's was a winged spaceplane, launched by a CZ-2 core booster with two large strap-on boosters. It so strongly resembled the cancelled US Dynasoar of 15 years earlier that US intelligence analysts wondered if it wasn't based on declassified Dynasoar technical information. More...
  • DF-5A Chinese intercontinental ballistic missile. Modernised DF-5 incorporating guidance and propulsion improvements developed for the CZ-series of launch vehicles. More...
  • CZ-3 Chinese orbital launch vehicle. The Long March 3 was a three-stage launch vehicle designed for delivery of satellites of 1,500 kg mass into geosynchronous transfer orbit. The first and second stages were based on the CZ-2C, and designed and manufactured by the Shanghai Academy of Spaceflight Technology. The majority of the technology and flight hardware used in the CZ-3 had been qualified and proven on the CZ-2C. The third stage, manufactured by CALT, was equipped with an LOX/LH2 cryogenic engine. Long March 3 was also capable of placing spacecraft into an elliptical or circular low earth orbit and sun synchronous orbit. More...
  • CZ-4A Chinese orbital launch vehicle. The CZ-4 was developed and manufactured by the Shanghai Academy of Spaceflight Technology. Its first stage was essentially the same as that of the CZ-3 and the second stage was identical to that of the CZ-3. The CZ-4's third stage, however, was a development, featuring a thin wall common intertank bulkhead tankage and two-engine cluster with both engines gimbling about two perpendicular axes. The third stage engine cluster connected to the tank aft bulkhead through the engine bay. The CZ-4 had two payload fairing configurations: Type-A and Type-B. The CZ-4 was designed for launching satellites into polar and sun-synchronous orbits. More...
  • CZ-2E Chinese orbital launch vehicle. The CZ-2E added four liquid rocket booster strap-ons to the basic CZ-2 core to achieve a low earth orbit payload capability approaching the Russian Proton, US Titan, or European Ariane rockets. The Long March 2E had a maximum payload capability of 9,500 kg to low earth orbit. More...
  • CZ-2D Chinese orbital launch vehicle. The Long March 2D was a two-stage launch vehicle with storable propellants, suitable for launching a variety of low earth orbit satellites. Developed and manufactured by the Shanghai Academy of Spaceflight Technology, the CZ-2D had a typical payload capability of 3,500kg in a 200 km circular orbit. Its first stage was identical to that of the CZ-4. The second stage was essentially the same as that of the CZ-4, except for an improved vehicle equipment bay. More...
  • CZ-3A Chinese three-stage orbital launch vehicle. The Long March 3A, by incorporating the mature technologies of the CZ-3 and adding a more powerful cryogenic third stage and more capable control system, had a greater geosynchronous transfer orbit capability, greater flexibility for attitude control, and better adaptability to a variety of launch missions. More...
  • CZ-3B Chinese orbital launch vehicle. The Long March 3B was the most powerful Long March launch vehicle. It could inject a 5,000 kg payload into geosynchronous transfer orbit. The CZ-3B was developed on the basis of the CZ-3A, but had enlarged propellant tanks, larger fairing, and four boosters strapped onto the core stage. The CZ-3B boosters were identical to those of the CZ-3A. More...
  • CZ-2C/SD On April 28, 1993, the Chinese Great Wall Industrial Corporation and Motorola signed a launch services contract for multiple launch of Iridium communications satellites using CZ-2C/SD launch vehicles. The main differences between the CZ-2C and the CZ-2C/SD were: a modified fairing with a diameter of 3.35m; a newly developed Smart Dispenser; improved second stage fuel and oxidizer tanks; and second stage engines with higher expansion ratio nozzles. More...
  • CZ-4B Chinese orbital launch vehicle. The CZ-4B introduced in 1999 was an improved model of the CZ-4B with an enhanced third stage and fairing. It measured 44.1 metres in length with a first stage thrust of 300 tonnes. More...
  • CZ-2F Chinese orbital launch vehicle. Man-rated version of CZ-2E, designed for launch of the Shenzhou spacecraft. Little difference externally. Modifications were related to improved redundancy of systems, strengthened upper stage to handle large 921-1 spacecraft fairing and launch escape tower. President Jiang Zemin gave the name 'Shenjian' ('Divine Arrow') to the CZ-2F after the successful launch of the Shenzhou-3 mission. More...
  • CZ-3B(A) Chinese orbital launch vehicle. In February 1999 the China Great Wall Company announced it was developing more powerful Long March rockets using larger-size liquid propellant strap-on motors. The Long March 3B(A) would be available in 2002. More...
  • CZ-2E(A) Planned upgrade of CZ-2E with enlarged liquid boosters. Probably intended for launch of Chinese space station modules in the 21st century. Fairing was 5.20 m in diameter and 12.39 m long. More...
  • CZ-4C Chinese orbital launch vehicle. The CZ-4C, first flown in 2007, had an upgraded second-stage engine that could be restarted in space. The vehicle also had structural rings at the base of the first and second stages, an interstage weather cover,ejected at liftoff, and the larger payload shroud introduced on the CZ-4B. All of these indicated that the vehicle was designed to take larger payloads to higher, more precise orbits than the CZ-4B. More...
  • CZ-3C Chinese orbital launch vehicle. Launch vehicle combining CZ-3B core with two boosters from CZ-2E. The standard fairing was 9.56 m long, 4.0 m in diameter. On August 23, 2001, the CZ-3C launcher passed its critical design review. CZ-3C development had begun in 1995 but was suspended in 1996-2000 due to the 1996 CZ-3B failure. First launch was in 2008. 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...

CZ Chronology


1964 September 12 - . LV Family: CZ; DF-2; DF-3. Launch Vehicle: DF-1; DF-3 Tsien; DF-4.
  • Chinese missiles redesignated and new development plan adopted. - . Nation: China. Related Persons: Tsien. Program: Long March. Tsien had conducted a series of meetings with the Chinese leadership during the year to redefine China's missile development plans. There are clashes between Tsien, who favours an American engineering approach, and his staff, who were trained in Russian and favour the Soviet approach. Finally the missiles were defined by their target objectives, and a new development plan was adopted, with definite goals. The 1059 missile (copy of Russian R-2) was redesignated DF-1. The DF-2 was to be improved to carry an atomic bomb to a range sufficient to hit Japan. The DF-3 ICBM was cancelled, and the new DF-3 project would involve development of a nuclear-tipped missile capable of reaching the Philippines (earlier referred to as the DF-1). The DF-4 was to be capable of hitting Guam, and the DF-5 would be an ICBM capable of reaching the United States. The DF-2, DF-3 and DF-4 would use strap-down accelerometer guidance packages, while the DF-5 was to be equipped with a full-fledged inertial guidance unit.

1971 September 10 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: DF-5.
  • - . Nation: China. Agency: PRC. Apogee: 1,000 km (600 mi). Summary: Research and Development Suborbital Flight.

1972 August 10 - . 00:32 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701-02.
  • Shiyan Peizhong - . Nation: China. Agency: PRC. Apogee: 200 km (120 mi). Summary: Research and Development Suborbital Flight.

1973 September 18 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701-03. FAILURE: Failure. Failed Stage: U.
  • JSSW 1 - . Payload: JSSW 1. Nation: China. Agency: PRC. Spacecraft: JSSW. COSPAR: F730918A.

1974 July 14 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701-04. FAILURE: Vehicle lost attitude stability and destroyed by range safety.. Failed Stage: G.
  • JSSW 2 - . Payload: JSSW 2. Nation: China. Agency: PRC. Spacecraft: JSSW. COSPAR: F740714A.

1974 November 5 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2A. LV Configuration: Chang Zheng 2A CZ2A-1 (3). FAILURE: Cable carrying pitch rate gyro signal disconnected.. Failed Stage: G.
  • FSW-0 - . Payload: FSW-0 No. A. Nation: China. Agency: PRC. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Decay Date: 1974-11-05 . COSPAR: F741105A.

1975 July 26 - . 13:28 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701-05.
  • JSSW 3 - . Payload: JSSW 3. Mass: 1,107 kg (2,440 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: JSSW. Decay Date: 1975-09-14 . USAF Sat Cat: 8053 . COSPAR: 1975-070A. Apogee: 455 km (282 mi). Perigee: 190 km (110 mi). Inclination: 69.0000 deg. Period: 90.90 min. Summary: Photo surveillance; radio transmission. .

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....

1975 December 16 - . 09:19 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701-06.
  • JSSW 4 - . Payload: JSSW 4. Mass: 1,110 kg (2,440 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: JSSW. Decay Date: 1976-01-27 . USAF Sat Cat: 8488 . COSPAR: 1975-119A. Apogee: 387 km (240 mi). Perigee: 186 km (115 mi). Inclination: 69.0000 deg. Period: 90.30 min. Summary: Photo surveillance; radio transmission. .

1976 August 30 - . 11:53 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701-07.
  • JSSW 5 - . Payload: JSSW 5. Mass: 1,108 kg (2,442 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: JSSW. Decay Date: 1978-11-25 . USAF Sat Cat: 9394 . COSPAR: 1976-087A. Apogee: 2,145 km (1,332 mi). Perigee: 195 km (121 mi). Inclination: 69.2000 deg. Period: 108.80 min.

1976 November 10 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701-08. FAILURE: Failure. Failed Stage: U.
  • JSSW 6 - . Payload: JSSW 6. Nation: China. Agency: PRC. Spacecraft: JSSW. COSPAR: F761110A.

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..

1977 September 14 - . 00:15 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701(II)-01.
  • DDDS test - . Nation: China. Agency: PRC. Apogee: 200 km (120 mi).

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..

1978 February - . LV Family: CZ. Launch Vehicle: CZ-2 Spaceplane Launcher.
  • First public announcement of a Chinese manned program - . Nation: China. Spacecraft: Chinese Manned Capsule 1978. Summary: First public announcement of a Chinese manned program came in February, 1978. By November the head of the Chinese Space Agency, Jen Hsin-Min, confirmed that China was working on a manned space capsule and a 'Skylab' space station..

1978 April 15 - . 16:39 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701(II)-02.
  • DDDS test - . Nation: China. Agency: PRC. Apogee: 200 km (120 mi).

1979 January 7 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. Launch Pad: LA2B?. LV Family: CZ. Launch Vehicle: DF-5.
  • - . Nation: China. Agency: PRC. Apogee: 1,000 km (600 mi). Summary: Other sources say launch was from Taiyuan..

1979 July 15 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. Launch Pad: LA2B?. LV Family: CZ. Launch Vehicle: DF-5.
  • - . Nation: China. Agency: PRC. Apogee: 1,000 km (600 mi). Summary: Other sources say launch was from Taiyuan..

1979 July 28 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 XCZ-1-02. FAILURE: Second stage failure.. Failed Stage: 2.
  • SJ-1 - . Payload: Shi Jian 1. Mass: 221 kg (487 lb). Nation: China. Agency: PRC. Spacecraft: SJ. COSPAR: F790728A. Summary: The SJ-1 was similar in appearance to the American Telstar and conducted communications technology tests..

1979 August 21 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. Launch Pad: LA2B?. LV Family: CZ. Launch Vehicle: DF-5.
  • - . Nation: China. Agency: PRC. Apogee: 1,000 km (600 mi). Summary: Other sources say launch was from Taiyuan on 2 August..

1979 September 4 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. Launch Pad: LA2B?. LV Family: CZ. Launch Vehicle: DF-5.
  • - . Nation: China. Agency: PRC. Apogee: 1,000 km (600 mi). Summary: Other sources say launch was from Taiyuan..

1979 November 26 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. Launch Pad: LA2B?. LV Family: CZ. Launch Vehicle: DF-5.
  • - . Nation: China. Agency: PRC. Apogee: 1,000 km (600 mi). Summary: Other sources say launch was from Taiyuan on 15 October..

1980 January - . LV Family: CZ. Launch Vehicle: CZ-2 Spaceplane Launcher.
  • Chinese astronauts in training - . Nation: China. Spacecraft: Chinese Manned Capsule 1978. The Chinese press reported a visit with the Chinese astronaut trainees at the Chinese manned spaceflight training centre. Photographs appeared of the astronauts in training. Pressure suited astronauts were shown in pressure chamber tests. Other trainees were shown at the controls of a space shuttle-like spaceplane cockpit.

1980 February 15 - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: DF-5.
  • Last DF-5 partial range test. - . Nation: China. Program: Long March. Summary: Other sources do not list this test..

1980 May 18 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. Launch Pad: LA2B?. LV Family: CZ. Launch Vehicle: DF-5.
  • Test mission - . Nation: China. Agency: PRC. Apogee: 1,000 km (600 mi).

1980 May 21 - . 02:00 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. Launch Pad: LA2B?. LV Family: CZ. Launch Vehicle: DF-5.
  • Test mission - . Nation: China. Agency: PRC. Apogee: 1,000 km (600 mi).

1981 September 19 - . 21:28 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 XCZ-1-02.
  • SJ-2A - . Payload: Shi Jian 2B. Mass: 257 kg (566 lb). Nation: China. Agency: MAI. Class: Technology. Type: Navigation technology satellite. Spacecraft: SJ. Decay Date: 1981-09-26 . USAF Sat Cat: 12842 . COSPAR: 1981-093A. Apogee: 1,598 km (992 mi). Perigee: 232 km (144 mi). Inclination: 59.5000 deg. Period: 103.30 min.
  • SJ-2B - . Payload: Shi Jian C. Mass: 28 kg (61 lb). Nation: China. Agency: MAI. Class: Technology. Type: Navigation technology satellite. Spacecraft: SJ. Decay Date: 1982-10-06 . USAF Sat Cat: 12843 . COSPAR: 1981-093B. Apogee: 1,615 km (1,003 mi). Perigee: 233 km (144 mi). Inclination: 59.4000 deg. Period: 103.50 min. Summary: Balloon for drag studies..
  • SJ-2 - . Payload: Shi Jian 2. Mass: 483 kg (1,064 lb). Nation: China. Agency: MAI. Class: Technology. Type: Navigation technology satellite. Spacecraft: SJ. Decay Date: 1982-08-17 . USAF Sat Cat: 12845 . COSPAR: 1981-093D. Apogee: 1,608 km (999 mi). Perigee: 232 km (144 mi). Inclination: 59.4000 deg. Period: 103.40 min.

1981 December 7 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. Launch Pad: LA2B?. LV Family: CZ. Launch Vehicle: DF-5.
  • - . Nation: China. Agency: PRC. Apogee: 1,000 km (600 mi). Summary: Other sources say launch was from Taiyuan..

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 January 29 - . 12:25 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-1 (9). FAILURE: Third stage failed to ignite.. Failed Stage: 3.
  • STTW-T1 - . Payload: STTW-T1. Mass: 900 kg (1,980 lb). Nation: China. Agency: MAI. Class: Communications. Type: Civilian communications satellite. Spacecraft: DFH-2. USAF Sat Cat: 14670 . COSPAR: 1984-008A. Apogee: 6,446 km (4,005 mi). Perigee: 484 km (300 mi). Inclination: 36.1000 deg. Period: 162.00 min. Summary: First launch of a prototype DFH-2 communications satellite. Payload stranded in low earth orbit, but all subsystems including the communications payload were completely checked and tested..

1984 April 8 - . 11:20 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-2 (10).
  • STTW-T2 - . Payload: STTW-T2. Mass: 900 kg (1,980 lb). Nation: China. Agency: MAI. Class: Communications. Type: Civilian communications satellite. Spacecraft: DFH-2. Completed Operations Date: 1988-06-28 . USAF Sat Cat: 14899 . COSPAR: 1984-035A. Apogee: 35,796 km (22,242 mi). Perigee: 35,733 km (22,203 mi). Inclination: 6.1000 deg. Period: 1,435.00 min. Prototype of DFH-2 communications satellite. After on-orbit testing and check out of the satellite and the ground stations, the satellite system was declared operational, and was used experimentally for the transmission of television, telephone, and data messages with good results. It stayed in operation for more than four years, exceeding the design life of three years by a comfortable margin. Operated in geosynchronous orbit at 125 deg E in 1984-1988. As of 4 September 2001 located at 40.81 deg E drifting at 0.320 deg W per day. As of 2007 Feb 27 located at 133.57E drifting at 0.079W degrees per day.

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 February 1 - . 12:37 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-3 (13).
  • STTW 1 - . Payload: STTW 1. Mass: 1,024 kg (2,257 lb). Nation: China. Agency: MAI. Class: Communications. Type: Civilian communications satellite. Spacecraft: DFH-2. Completed Operations Date: 1990-06-01 . USAF Sat Cat: 16526 . COSPAR: 1986-010A. Apogee: 35,819 km (22,256 mi). Perigee: 35,774 km (22,228 mi). Inclination: 9.8000 deg. Period: 1,436.60 min. Second successful DFH-2 launch. Also designated STW-2, the satellite was positioned at 103 deg E. In comparison to the first two DFH-2's, a parabolic antenna reflector replaced the horn antenna. Operated in geosynchronous orbit at 103 deg E in 1986-1990. As of 3 September 2001 located at 102.75 deg E drifting at 0.030 deg W per day. As of 2007 Mar 10 located at 46.50E drifting at 0.019E degrees per day.

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 March 7 - . 12:41 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-4 (17).
  • Zhongxing-1 - . Payload: STTW 2. Mass: 1,024 kg (2,257 lb). Nation: China. Agency: Chinasat. Class: Communications. Type: Military communications satellite. Spacecraft: DFH-2. Completed Operations Date: 1997-07-01 . USAF Sat Cat: 18922 . COSPAR: 1988-014A. Apogee: 35,789 km (22,238 mi). Perigee: 35,786 km (22,236 mi). Inclination: 0.5000 deg. Period: 1,436.20 min. Summary: Operated in geosynchronous orbit at 87 deg E in 1988-1997. As of 28 August 2001 located at 87.94 deg E drifting at 0.038 deg E per day. As of 2007 Mar 11 located at 64.00E drifting at 0.067E degrees per day..

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..

1988 September 6 - . 20:30 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-4A. LV Configuration: Chang Zheng 4 CZ4-1 (19).
  • FY-1A - . Payload: Feng Yun 1A. Mass: 750 kg (1,650 lb). Nation: China. Agency: MAI. Class: Technology. Type: Weather technology satellite. Spacecraft: FY-1. USAF Sat Cat: 19467 . COSPAR: 1988-080A. Apogee: 895 km (556 mi). Perigee: 875 km (543 mi). Inclination: 98.8000 deg. Period: 102.70 min. Summary: Experimental weather satellite. First use of new launch site and launch vehicle. Failed after 38 days due to problems with attitude control system..

1988 December 22 - . 12:40 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-5 (20).
  • Zhongxing-2 - . Payload: STTW 3. Mass: 1,024 kg (2,257 lb). Nation: China. Agency: Chinasat. Class: Communications. Type: Military communications satellite. Spacecraft: DFH-2. USAF Sat Cat: 19710 . COSPAR: 1988-111A. Apogee: 35,791 km (22,239 mi). Perigee: 35,787 km (22,236 mi). Inclination: 0.1000 deg. Period: 1,436.20 min. Summary: Operated in geosynchronous orbit at 110 deg E in 1989-1999. As of 27 August 2001 located at 91.92 deg E drifting at 0.244 deg E per day. As of 2007 Mar 10 located at 83.40E drifting at 0.283W degrees per day..

1990 February 4 - . 12:28 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-6 (21).
  • Zhongxing-3 - . Payload: STTW 4. Mass: 1,024 kg (2,257 lb). Nation: China. Agency: Chinasat. Class: Communications. Type: Military communications satellite. Spacecraft: DFH-2. Completed Operations Date: 1998-07-01 . USAF Sat Cat: 20473 . COSPAR: 1990-011A. Apogee: 35,795 km (22,241 mi). Perigee: 35,783 km (22,234 mi). Inclination: 0.0000 deg. Period: 1,436.30 min. National operational communications satellite. Designation 1990-2. Operated in geosynchronous orbit at 98 deg E in 1990-1998. As of 4 September 2001 located at 52.36 deg E drifting at 0.045 deg W per day. As of 2007 Mar 10 located at 96.88E drifting at 0.061W degrees per day.

1990 April 7 - . 13:30 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-7 (22).
  • Asiasat 1 - . Mass: 1,442 kg (3,179 lb). Nation: China. Agency: Asiasat. Manufacturer: El Segundo. Program: Asiasat. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 20558 . COSPAR: 1990-030A. Apogee: 35,789 km (22,238 mi). Perigee: 35,786 km (22,236 mi). Inclination: 2.7000 deg. Period: 1,436.20 min. First commercial Chinese launch; Stationed at 105 deg E; formerly Westar 6 (retrieved by STS-51A and refurbished). Fixed-satellite telecommunication services and transmission of television signals. Operational life about 10 years. Orbital position 105.5E. Owner/operator: Asia Satellite Telecommunications Co, Ltd. 23-24/F, East Exchange Tower, 38-40 Leighton Rd, Hong K ong. Telex 68345 ASAT HX Fax 852 576 4111. Operated in geosynchronous orbit at 105 deg E in 1990-1999; 122 deg E in 1999-2000. As of 3 September 2001 located at 121.97 deg E drifting at 0.009 deg E per day. As of 2007 Mar 10 located at 23.96E drifting at 3.706W degrees per day.

1990 July 16 - . 00:40 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-2E. LV Configuration: Chang Zheng 2E CZ2E-1 (23).
  • Badr-A - . Payload: Badr 1 + R&D. Mass: 52 kg (114 lb). Nation: Pakistan. Agency: Suparco. Class: Technology. Type: Communications technology satellite. Spacecraft: Badr. Decay Date: 1990-12-08 . USAF Sat Cat: 20685 . COSPAR: 1990-059A. Apogee: 988 km (613 mi). Perigee: 208 km (129 mi). Inclination: 28.5000 deg. Period: 96.70 min. Summary: First launch of new Chinese launch vehicle. Experimental Pakistani payload..
  • HS-601 Model - . Nation: China. Agency: PRC. COSPAR: 1990-059xx. Summary: First launch of new Chinese launch vehicle..

1990 September 3 - . 00:53 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-4A. LV Configuration: Chang Zheng 4 CZ4-2 (24).
  • FY-1B - . Payload: Feng Yun 1B. Mass: 881 kg (1,942 lb). Nation: China. Agency: MAI. Class: Technology. Type: Weather technology satellite. Spacecraft: FY-1. USAF Sat Cat: 20788 . COSPAR: 1990-081A. Apogee: 897 km (557 mi). Perigee: 875 km (543 mi). Inclination: 98.8000 deg. Period: 102.70 min. Summary: Experimental weather satellite. Operated for over a year..
  • QQW 1 - . Payload: QQW 1A. Mass: 4.00 kg (8.80 lb). Nation: China. Agency: MAI. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SJ. Decay Date: 1991-03-11 . USAF Sat Cat: 20789 . COSPAR: 1990-081B. Apogee: 811 km (503 mi). Perigee: 789 km (490 mi). Inclination: 99.0000 deg. Period: 100.90 min. Summary: QQW atmospheric balloon..
  • QQW 2 - . Payload: QQW 1B. Mass: 4.00 kg (8.80 lb). Nation: China. Agency: MAI. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SJ. Decay Date: 1991-07-24 . USAF Sat Cat: 20790 . COSPAR: 1990-081C. Apogee: 629 km (390 mi). Perigee: 596 km (370 mi). Inclination: 99.0000 deg. Period: 97.00 min. Summary: QQW atmospheric balloon..

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..

1991 December 28 - . 12:00 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-8 (26). FAILURE: Third stage failed to ignite. Partial Failure.. Failed Stage: 3.
  • Zhongxing-4 - . Payload: STTW 5. Mass: 1,025 kg (2,259 lb). Nation: China. Agency: Chinasat. Program: Chinasat. Class: Communications. Type: Military communications satellite. Spacecraft: DFH-2. USAF Sat Cat: 21833 . COSPAR: 1991-088A. Apogee: 34,041 km (21,152 mi). Perigee: 2,023 km (1,257 mi). Inclination: 32.3000 deg. Period: 632.60 min. Summary: Third stage failure; unusable orbit. DFH-2 operational communications satellite..

1992 August 9 - . 08:00 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. Launch Pad: LA2B?. LV Family: CZ. Launch Vehicle: CZ-2D. LV Configuration: Chang Zheng 2D CZ2D-1 (27).
  • FSW-2 No. 1 - . Payload: FSW-2 No. 01. Mass: 2,500 kg (5,500 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 15.00 days. Decay Date: 1992-09-01 . USAF Sat Cat: 22072 . COSPAR: 1992-051A. Apogee: 332 km (206 mi). Perigee: 171 km (106 mi). Inclination: 63.1000 deg. Period: 89.50 min. Summary: Fanhui Shi Weixing recoverable imaging satellite; carried microgravity experiments; capsule returned August 25 after 15 days in orbit..

1992 August 13 - . 23:00 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-2E. LV Configuration: Chang Zheng 2E CZ2E-2 (28).
  • Optus B1 - . Payload: Aussat B1. Mass: 2,760 kg (6,080 lb). Nation: Australia. Agency: Optus. Program: Aussat. Class: Communications. Type: Military communications satellite. Spacecraft: HS 601. USAF Sat Cat: 22087 . COSPAR: 1992-054A. Apogee: 35,800 km (22,200 mi). Perigee: 35,774 km (22,228 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Stationed at 160 deg E. Commercial communications. Longitude 160 +/- 0.05 deg E. Launched fromn China. Positioned in geosynchronous orbit at 160 deg E in 1992-1999 As of 1 September 2001 located at 159.98 deg E drifting at 0.009 deg W per day. As of 2007 Mar 11 located at 163.63E drifting at 0.044E degrees per day.

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..

1992 December 21 - . 11:21 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-2E. LV Configuration: Chang Zheng 2E CZ2E-3 (30). FAILURE: Shortcomings in the guidance system lead to the vehicle not anticipating the true effects of horizontal wind-shear once the mountains surrounding the launch site were cleared. This caused the nose fairing to collapse 45 seconds after launch.. Failed Stage: G.
  • Aussat B2 / Optus B2 - . Payload: Optus B2 / Star 63F. Mass: 2,760 kg (6,080 lb). Nation: Australia. Agency: Hughes. Program: Aussat. Class: Communications. Type: Military communications satellite. Spacecraft: HS 601. Decay Date: 1995-06-29 . USAF Sat Cat: 22278 . COSPAR: 1992-090A. Apogee: 816 km (507 mi). Perigee: 206 km (128 mi). Inclination: 28.1000 deg. Period: 94.90 min. Summary: Despite collapse of the nose fairing and near-desctruction of the payload, the launch vehicle continued on to place the wreckage of Optus-B2, and the Star-63F Kick-Motor into low earth 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.

1994 February 8 - . 08:34 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-1 (32).
  • SJ-4 - . Payload: Shi Jian 4. Mass: 400 kg (880 lb). Nation: China. Agency: CASC. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SJ. USAF Sat Cat: 22996 . COSPAR: 1994-010A. Apogee: 26,837 km (16,675 mi). Perigee: 195 km (121 mi). Inclination: 28.7000 deg. Period: 465.40 min. Summary: Particles and fields research. .
  • KF-1 - . Payload: Kua Fu 1 / DFH-3 mockup. Mass: 2,200 kg (4,800 lb). Nation: China. Agency: CASC. Program: Chinastar. Class: Technology. Type: Navigation technology satellite. Spacecraft: DFH-3. Decay Date: 2002-02-07 . USAF Sat Cat: 23009 . COSPAR: 1994-010B. Apogee: 36,046 km (22,397 mi). Perigee: 178 km (110 mi). Inclination: 28.5000 deg. Period: 635.69 min. Summary: Mass model of DFH-3 satellite..

1994 July 3 - . 08:00 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. Launch Pad: LA2B?. LV Family: CZ. Launch Vehicle: CZ-2D. LV Configuration: Chang Zheng 2D CZ2D-2 (33).
  • FSW-2 No. 2 - . Payload: FSW-2 No. 02. Mass: 2,600 kg (5,700 lb). Nation: China. Agency: CASC. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 15.00 days. Decay Date: 1994-09-13 . USAF Sat Cat: 23145 . COSPAR: 1994-037A. Apogee: 350 km (210 mi). Perigee: 207 km (128 mi). Inclination: 62.9000 deg. Period: 90.08 min. The second Fanhui Shi Weixing FSW-2 was launched on 3 July 1994 into an orbit of 173 km by 343 km at an inclination of 63.0 deg. The spacecraft remained in orbit for 15 days, making four small manoeuvres before successfully returning to Earth. The payload included Earth observation systems, a biological experiment, and microgravity research instruments. The retrievable capsule was recovered in China on July 18

1994 July 21 - . 10:55 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-9 (34).
  • Apstar 1 - . Mass: 1,383 kg (3,048 lb). Nation: China. Agency: APT. Program: Apstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 23185 . COSPAR: 1994-043A. Apogee: 35,789 km (22,238 mi). Perigee: 35,785 km (22,235 mi). Inclination: 0.0000 deg. Period: 1,436.12 min. Summary: Asia-Pacific communications. Operated in geosynchronous orbit at 138 deg E in 1994-1999. As of 5 September 2001 located at 138.04 deg E drifting at 0.004 deg W per day. As of 2007 Mar 11 located at 141.96E drifting at 0.002W degrees per day..

1994 August 27 - . 23:10 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-2E. LV Configuration: Chang Zheng 2E CZ2E-4 (35).
  • Optus B3 - . Mass: 2,760 kg (6,080 lb). Nation: Australia. Agency: Optus. Program: Aussat. Class: Communications. Type: Military communications satellite. Spacecraft: HS 601. USAF Sat Cat: 23227 . COSPAR: 1994-055A. Apogee: 35,855 km (22,279 mi). Perigee: 35,718 km (22,194 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Telephone; TV; mobile communications; air traffic control. Stationed at 156 deg deg E. Positioned in geosynchronous orbit at 152 deg E in 1994-1995; 156 deg E in 1995-1999 As of 5 September 2001 located at 156.00 deg E drifting at 0.007 deg W per day. As of 2007 Mar 9 located at 151.97E drifting at 0.007W degrees per day.

1994 November 29 - . 17:02 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-2 (36).
  • Zhongxing-5 - . Mass: 2,230 kg (4,910 lb). Nation: China. Agency: Chinasat. Program: Chinasat. Class: Communications. Type: Military communications satellite. Spacecraft: DFH-3. Completed Operations Date: 1994-12-01 . USAF Sat Cat: 23415 . COSPAR: 1994-080A. Apogee: 35,957 km (22,342 mi). Perigee: 35,225 km (21,887 mi). Inclination: 0.1500 deg. Period: 1,426.15 min. The first test launch of a DFH-3 by a CZ-3A launch vehicle was successful in attaining the proper transfer orbit, but during the subsequent manoeuvres to achieve geostationary orbit, the DFH-3 failed due to a malfunction of the satellite on-board propulsion system. The satellite was positioned at 132 deg E prior to the failure. As of 4 September 2001 located at 113.80 deg E drifting at 2.499 deg E per day. As of 2007 Mar 2 located at 90.02E drifting at 2.513E degrees per day.

1995 January 25 - . 22:40 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-2E. LV Configuration: Chang Zheng 2E CZ2E-5 (37). FAILURE: Shortcomings in the guidance system lead to the vehicle not anticipating the true effects of horizontal wind-shear once the mountains surrounding the launch site were cleared. This caused the nose fairing to collapse and the spacecraft to be destroyed.. Failed Stage: G.
  • Apstar 2 - . Nation: China. Agency: PRC. Program: Apstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. Decay Date: 1995-01-25 . COSPAR: F950125A. Because the Apstar failure happened a few seconds later than Optus, the consequences were catastrophic. The vehicle was destroyed, and the falling wreckage landed on a village down-range of the launch site, killing at least 20 and perhaps as many as 120 people.

1995 November 28 - . 11:30 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-2E. LV Configuration: Chang Zheng 2E CZ2E-6 (38).
  • Asiasat 2 - . Mass: 3,485 kg (7,683 lb). Nation: China. Agency: Asiasat. Manufacturer: Lockheed. Program: Asiasat. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 7000. USAF Sat Cat: 23723 . COSPAR: 1995-064A. Apogee: 35,798 km (22,243 mi). Perigee: 35,777 km (22,230 mi). Inclination: 0.4000 deg. Period: 1,436.20 min. TV; 24 C-band and 9 Ku-band transponders. Stationed at 100.5 deg E. Positioned in geosynchronous orbit at 100 deg E in 1995-1999 As of 5 September 2001 located at 100.49 deg E drifting at 0.015 deg W per day. As of 2007 Mar 9 located at 100.49E drifting at 0.011W degrees per day.

1995 December 28 - . 11:50 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-2E. LV Configuration: Chang Zheng 2E CZ2E-7 (39).
  • Echostar 1 - . Mass: 3,288 kg (7,248 lb). Nation: USA. Agency: TCI. Manufacturer: Lockheed. Program: Echostar. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 7000. USAF Sat Cat: 23754 . COSPAR: 1995-073A. Apogee: 35,796 km (22,242 mi). Perigee: 35,777 km (22,230 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. 16 Ku-band transponders. Stationed at 119 deg W. Positioned in geosynchronous orbit at 119 deg W in 1996-1999 As of 5 September 2001 located at 147.96 deg W drifting at 0.007 deg E per day. As of 2007 Mar 9 located at 148.10W drifting at 0.008W degrees per day.

1996 February 14 - . 19:01 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3B. LV Configuration: Chang Zheng 3B CZ3B-1 (40). FAILURE: Guidance failure resulted in launch vehicle crashing 22 seconds after launch, killing or injuring 59 people.. Failed Stage: G.
  • Intelsat 708 - . Nation: International. Agency: PRC. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. COSPAR: F960214A. First attempted launch of a new version in the Long March family. Began to experience an anomaly in attitude about 2 seconds after launch, pitching down and yawing to the right. It augured in nose down at T+22 seconds and exploded violently, utterly destroying the launcher and its payload. The Chief-Designer of the launch vehicle organised an analysis team on the same day of the accident. Interpretation and analysis of the telemetered data indicated that the crash was caused by a change in the inertial reference. The explosion killed six and injured 57. Two of the killed were senior engineers with CASC.

1996 July 3 - . 10:47 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-10 (41).
  • Apstar 1A - . Mass: 2,800 kg (6,100 lb). Nation: China. Agency: APT. Program: Apstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 23943 . COSPAR: 1996-039A. Apogee: 35,791 km (22,239 mi). Perigee: 35,785 km (22,235 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: 24 C-band transponders; Operated in geosynchronous orbit at 134 deg E in 1996-1999. As of 6 September 2001 located at 134.02 deg E drifting at 0.013 deg W per day. As of 2007 Mar 10 located at 129.99E drifting at 0.007E degrees per day..

1996 August 18 - . 10:27 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-11 (42).
  • Zhongxing 7 - . Payload: Zhongxing 7. Nation: China. Agency: Chinasat. Program: Chinasat. Class: Communications. Type: Military communications satellite. Spacecraft: HS 376. USAF Sat Cat: 24282 . COSPAR: 1996-048A. Apogee: 46,499 km (28,893 mi). Perigee: 21,674 km (13,467 mi). Inclination: 26.3000 deg. Period: 1,350.20 min.

1996 October 20 - . 07:20 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2D. LV Configuration: Chang Zheng 2D CZ2D-3 (43).
  • FSW-2 No. 3 - . Payload: FSW-2 No. 03. Mass: 2,600 kg (5,700 lb). Nation: China. Agency: CASC. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 15.00 days. Decay Date: 1996-12-03 . USAF Sat Cat: 24634 . COSPAR: 1996-059A. Apogee: 133 km (82 mi). Perigee: 121 km (75 mi). Inclination: 63.0000 deg. Period: 87.00 min. Summary: Final launch in the FSW series. Landed in China on November 4 after 15 days in orbit..

1997 May 11 - . 16:17 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-3 (44).
  • Zhongxing-6 - . Mass: 2,200 kg (4,800 lb). Nation: China. Agency: Chinasat. Program: Chinasat. Class: Communications. Type: Military communications satellite. Spacecraft: DFH-3. USAF Sat Cat: 24798 . COSPAR: 1997-021A. Apogee: 35,797 km (22,243 mi). Perigee: 35,776 km (22,230 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. The telecommunications satellite, the most sophisticated and complex satellite ever built in China, was equipped with 24 transponders used for television, digital transmission and other telecommunications services. It had a design life eight years. After over one year of tests the satellite was delivered to the end user, China Telecommunications Broadcast Satellite Corporation (Chinasat) on August 12 1998. A long term operation contract for the redesignated Chinasat-6 was signed by the China Academy of Space Technology (CAST), Chinasat and the Xian Satellite Control Center. Chinasat-6 operated in geosynchronous orbit at 125 deg E in 1997-1999. As of 5 September 2001 located at 124.99 deg E drifting at 0.011 deg W per day. As of 2007 Mar 6 located at 123.93E drifting at 0.104W degrees per day.

1997 June 10 - . 12:01 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-12 (45).
  • FY-2A - . Payload: Fengyun 2A. Nation: China. Agency: CASC. Manufacturer: SARTI. Class: Earth. Type: Weather satellite. Spacecraft: FY-2. USAF Sat Cat: 24834 . COSPAR: 1997-029A. Apogee: 35,784 km (22,235 mi). Perigee: 35,783 km (22,234 mi). Inclination: 0.8000 deg. Period: 1,436.10 min. Geosynchronous weather satellite; also known as FY-2B. Operated in geosynchronous orbit at 105 deg E in 1997-2000; 85 deg E in 2000.. The FY-2A stopped transmission in April 1998 but was put back into partial operation in December 1998. Its imager then failed completely on 30 September 1998 and it was retired in April 2000. As of 4 September 2001 located at 83.55 deg E drifting at 0.074 deg W per day. As of 2007 Mar 11 located at 58.96E drifting at 0.025W degrees per day.

1997 August 19 - . 17:50 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3B. LV Configuration: Chang Zheng 3B CZ3B-2 (46).
  • Agila 2 - . Payload: Mabuhay. Nation: Philippines. Agency: MPSC. Manufacturer: Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 24901 . COSPAR: 1997-042A. Apogee: 35,803 km (22,246 mi). Perigee: 35,771 km (22,227 mi). Inclination: 0.0000 deg. Period: 1,436.20 min. Summary: Geosynchronous. Stationed over 146.0E Positioned in geosynchronous orbit at 146 deg E in 1997-1999 As of 5 September 2001 located at 145.99 deg E drifting at 0.009 deg W per day. As of 2007 Mar 11 located at 145.98E drifting at 0.017W degrees per day..

1997 September 1 - . 14:00 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-2C/SD. LV Configuration: Chang Zheng 2C-III/SD CZ2C-15 (47).
  • Iridium - . Payload: Iridium s/n MFS 1. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 24925 . COSPAR: 1997-048A. Apogee: 633 km (393 mi). Perigee: 620 km (380 mi). Inclination: 86.3400 deg. Period: 97.25 min. Summary: Plane 5. Ascending node 271.9 degrees. Dummy satellite..
  • Iridium - . Payload: Iridium s/n MFS 2. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 24926 . COSPAR: 1997-048B. Apogee: 634 km (393 mi). Perigee: 620 km (380 mi). Inclination: 86.3400 deg. Period: 97.26 min. Summary: Plane 5. Ascending node 272 degrees. Dummy satellite..

1997 October 16 - . 19:13 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3B. LV Configuration: Chang Zheng 3B CZ3B-3 (48).
  • Apstar 2R - . Nation: China. Agency: APT. Manufacturer: Palo Alto. Program: Apstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 25010 . COSPAR: 1997-062A. Apogee: 35,798 km (22,243 mi). Perigee: 35,774 km (22,228 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: Geosynchronous. Stationed over 76.5E Positioned in geosynchronous orbit at 76 deg E in 1997-1999 As of 5 September 2001 located at 76.48 deg E drifting at 0.001 deg W per day. As of 2007 Mar 11 located at 76.46E drifting at 0.002W degrees per day..

1997 December 8 - . 07:16 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-2C/SD. LV Configuration: Chang Zheng 2C-III/SD CZ2C-16 (49).
  • Iridium 42 - . Payload: Iridium s/n SV042. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25077 . COSPAR: 1997-077A. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 6. Ascending node 325.8 degrees..
  • Iridium 44 - . Payload: Iridium s/n SV044. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25078 . COSPAR: 1997-077B. Apogee: 780 km (480 mi). Perigee: 774 km (480 mi). Inclination: 86.3900 deg. Period: 100.40 min. Summary: Plane 6. Ascending node 325.8 degrees. Not in service..

1998 March 25 - . 17:01 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-2C/SD. LV Configuration: Chang Zheng 2C-III/SD CZ2C-17 (50).
  • Iridium 51 - . Payload: Iridium s/n SV051. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25262 . COSPAR: 1998-018A. Apogee: 756 km (469 mi). Perigee: 751 km (466 mi). Inclination: 86.4500 deg. Period: 99.90 min. Summary: Plane 4. Ascending node 262.5 degrees. Not in service..
  • Iridium 61 - . Payload: Iridium s/n SV061. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25263 . COSPAR: 1998-018B. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 4. Ascending node 262.5 degrees..

1998 May 2 - . 09:16 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-2C/SD. LV Configuration: Chang Zheng 2C-III/SD CZ2C-18 (51).
  • Iridium 69 - . Payload: Iridium s/n SV069. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25319 . COSPAR: 1998-026A. Apogee: 783 km (486 mi). Perigee: 777 km (482 mi). Inclination: 86.4000 deg. Period: 100.46 min. Summary: Plane 2. Ascending node 199.4 degrees. Not in service..
  • Iridium 71 - . Payload: Iridium s/n SV071. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25320 . COSPAR: 1998-026B. Apogee: 778 km (483 mi). Perigee: 775 km (481 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 2. Ascending node 199.3 degrees. Not in service..

1998 May 30 - . 10:00 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3B. LV Configuration: Chang Zheng 3B CZ3B-4 (52).
  • Zhongwei 1 - . Nation: China. Agency: Chinasat. Manufacturer: Lockheed. Program: Chinastar. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 25354 . COSPAR: 1998-033A. Apogee: 35,798 km (22,243 mi). Perigee: 35,777 km (22,230 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Also known as Chinastar 1; comsat to serve China, India, Korea and Southeast Asia with 18 C-band and 20 Ku-band transponders. Operated by the China Orient Telecommunications Satellite Company, part of the Chinese telecommunications ministry. Zhongwei 1 and the CZ-3B's final liquid hydrogen upper stage were placed in an initial supersynchronous 216 x 85,035 km x 24.4 deg transfer orbit. Geostationary at 87.6 degrees E. Positioned in geosynchronous orbit at 87 deg E in 1998-1999 As of 6 September 2001 located at 87.49 deg E drifting at 0.013 deg W per day. As of 2007 Mar 11 located at 87.64E drifting at 0.010W degrees per day.

1998 July 18 - . 09:20 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3B. LV Configuration: Chang Zheng 3B CZ3B-5 (53).
  • Sinosat - . Mass: 2,820 kg (6,210 lb). Nation: China. Agency: Eurasspa. Manufacturer: Cannes. Program: Sinosat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Spacebus 3000 . USAF Sat Cat: 25404 . COSPAR: 1998-044A. Apogee: 35,795 km (22,241 mi). Perigee: 35,779 km (22,231 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. The CZ-3B's liquid hydrogen upper stage and the Sinosat were placed in a 609 x 35958 km x 19.0 deg geostationary transfer orbit at 09:45 GMT. The first two liquid apogee burns were carried out on July 19 and 21. Sinosat, an Alcatel Spacebus 3000, was built in Cannes and owned temporarily by EurasSpace, a joint venture between Daimler-Benz Aerospace and the China Aerospace Corporation. After on-orbit testing it was delivered to the Sino Satellite Communications Company of Shanghai for communications services in China. The satellite carried 24 C-band transponders and 14 Ku-band transponders which covered the entire Asia-Pacific region. With a design life span of 15 years, the satellite was to provide multiple data transfer services for China's financial and air transportation control systems, as well as the Shanghai Information Port project, Sinosat operated in geosynchronous orbit at 110.5 deg E in 1998-1999. As of 5 September 2001 located at 110.55 deg E drifting at 0.012 deg W per day. As of 2007 Mar 10 located at 110.51E drifting at 0.001W degrees per day.

1998 August 19 - . 23:01 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-2C/SD. LV Configuration: Chang Zheng 2C-III/SD CZ2C-19 (54).
  • Iridium 3 - . Payload: Iridium s/n SV078. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25431 . COSPAR: 1998-048A. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 2. Ascending node 199.4 degrees..
  • Iridium 76 - . Payload: Iridium s/n SV076. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25432 . COSPAR: 1998-048B. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 2. Ascending node 199.4 degrees..

1998 December 19 - . 11:39 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-2C/SD. LV Configuration: Chang Zheng 2C-III/SD CZ2C-20 (55).
  • Iridium 11 - . Payload: Iridium s/n SV088?. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25577 . COSPAR: 1998-074A. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 2. Ascending node 197 degrees. Parking orbit..
  • Iridium 20 - . Payload: Iridium s/n SV089?. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25578 . COSPAR: 1998-074B. Apogee: 710 km (440 mi). Perigee: 709 km (440 mi). Inclination: 86.5000 deg. Period: 99.00 min. Summary: Plane 2. Ascending node 197.2 degrees. Parking orbit..

1999 March 11 - . LV Family: CZ. Launch Vehicle: CZ-2F.
  • Chinese Man-Rated Launch Vehicle Test Predicted - . Nation: China. Spacecraft: Shenzhou. Summary: It was reported on the Internet that the maiden flight of a new version of the CZ-2E designed to carry a manned vehicle would be made by mid-1999..

1999 May 1 - . LV Family: CZ. Launch Vehicle: CZ-2F.
  • Manned Program Delayed - . Nation: China. Spacecraft: Shenzhou. Summary: Far eastern newspapers reported an accident at Jiuquan Launch Center late May 1999. It was said that a fuel depot exploded, resulting in casualties and delaying the first manned vehicle launch originally scheduled for October..

1999 May 10 - . 01:33 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-4B. LV Configuration: Chang Zheng 4B CZ4B-1 (56).
  • FY-1C - . Payload: Feng Yun 1C. Nation: China. Agency: CASC. Manufacturer: Shanghai Institute of Satellite Engineering. Class: Earth. Type: Weather satellite. Spacecraft: FY-1. USAF Sat Cat: 25730 . COSPAR: 1999-025A. Apogee: 880 km (540 mi). Perigee: 846 km (525 mi). Inclination: 98.8000 deg. Period: 102.20 min. Summary: Operational weather satellite. First launch of stretched CZ-4B booster. After retirement the satellite was destroyed in the first test of the Chinese ASAT weapon on 11 January 2007..
  • SJ-5 - . Payload: Shi Jian 5. Nation: China. Agency: CASC. Manufacturer: Shanghai Institute of Satellite Engineering. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SJ. USAF Sat Cat: 25731 . COSPAR: 1999-025B. Apogee: 865 km (537 mi). Perigee: 841 km (522 mi). Inclination: 98.9000 deg. Period: 102.00 min. Summary: Research satellite carried as a secondary payload to study the radiation belts..

1999 June 9 - . LV Family: CZ. Launch Vehicle: CZ-2F.
  • CZ-2F Photograph Appears on the Internet - . Nation: China. Spacecraft: Shenzhou. A photograph of the CZ-2F manned spacecraft launch vehicle and its vertical assembly building was posted anonymously on the Internet. It was said to have been taken in May 1998 at the Jiuquan launch site by a contruction contractor. Some believed the photograph to be a phony but events later proved it to be real and a deliberate leak.

1999 June 11 - . 17:15 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-2C/SD. LV Configuration: Chang Zheng 2C-III/SD CZ2C-21 (57).
  • Iridium 14A - . Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25777 . COSPAR: 1999-032A. Apogee: 711 km (441 mi). Perigee: 708 km (439 mi). Inclination: 86.5000 deg. Period: 99.00 min.
  • Iridium 21A - . Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25778 . COSPAR: 1999-032B. Apogee: 711 km (441 mi). Perigee: 708 km (439 mi). Inclination: 86.5000 deg. Period: 99.00 min.

1999 August 15 - . LV Family: CZ. Launch Vehicle: CZ-2F.
  • China Upgrades Launch Facilities - . Nation: China. Tang Xianming, Director of the Xichang Launch Center, confirmed the construction of a new Vertical Assembly Facility at the Jiuquan Launch Center. He also affirmed that China would continue to use the Xichang Launch Center, which would be upgraded with improved data processing and control equipment.

1999 October 14 - . 03:15 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-4B. LV Configuration: Chang Zheng 4B CZ4B-2 (58).
  • ZY-1 - . Payload: Zi Yuan 1. Mass: 1,540 kg (3,390 lb). Nation: China. Agency: SISE. Manufacturer: CAST; INP. Class: Earth. Type: Earth resources satellite. Spacecraft: ZY. USAF Sat Cat: 25940 . COSPAR: 1999-057A. Apogee: 780 km (480 mi). Perigee: 773 km (480 mi). Inclination: 98.2000 deg. Period: 100.40 min. China-Brazil Earth Resources Satellite. China's first earth resources satellite, known as ZY-1, weighed 1,540 kilograms. Chief designer was Chen Yiyuan. The satellite, a joint project of China and Brazil, was designed to gather information on the environment, agriculture and urban planning through remote sensing images and data transmitted to China, Brazil and other countries. Planned lifetime was two years. The satellite circled the Earth 14 times a day and the groundtrack repeated after 26 days. By 23 February 2000 it had taken more than 20,000 high quality images. It was formally handed over for operational use on March 2 2000. The High Resolution CCD Camera had a resolution of 20 meters in the visible spectrum. The camera could point up to 32 degrees to either side of vertical, imaging the earth's surface stereoscopically. After 177 days the Wide Field Imager failed in early May 2000. Other devices, including the high resolution CCD camera, continue to work normally.
  • SACI 1 - . Nation: Brazil. Agency: SISE. Manufacturer: INPE. Class: Technology. Type: Navigation technology satellite. Spacecraft: SACI. USAF Sat Cat: 25941 . COSPAR: 1999-057B. Apogee: 731 km (454 mi). Perigee: 719 km (446 mi). Inclination: 98.7000 deg. Period: 99.30 min. Summary: INPE experimental scientific satellite with a magnetometer, particle detectors and an atmospheric experiment. INPE reportedly lost contact with the satellite in mid-October..

1999 November 19 - . 22:30 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS. LV Family: CZ. Launch Vehicle: CZ-2F. LV Configuration: Chang Zheng 2F CZ2F-1 (59).
  • Shenzhou - . Mass: 7,600 kg (16,700 lb). Nation: China. Agency: CASC. Manufacturer: CALT. Class: Manned. Type: Manned spacecraft. Spacecraft: Shenzhou. Duration: 0.88 days. Decay Date: 1999-11-20 . USAF Sat Cat: 25956 . COSPAR: 1999-061A. Apogee: 315 km (195 mi). Perigee: 195 km (121 mi). Inclination: 42.6000 deg. Period: 89.60 min. The unmanned first test flight of a prototype of the Chinese Project 921-1 spacecraft took place 49 days after the planned date of October 1, 1999. Shenzhou separated from its launch vehicle and went into orbit about ten minutes after lift-off. The spacecraft was controlled from the new Beijing Aerospace Directing and Controlling Centre. The spacecraft did not manoeuvre during the flight. The first attempt to return the spacecraft to earth came on orbitt 12, but the retrofire command would not be accepted by the spacecraft's computer. A retry on the next orbit also failed.

    The Yuanwang-3 tracking ship off the coast of Namibia picked up the spacecraft's signal at 18:49 UT, and commanded retro-fire. This time the spacecraft accepted the command, which probably saved the entire program. The spacecraft passed out of range of the tracking ship nine minutes later. Its trajectory arced over Africa, skimmed the coast of the Arabian peninsula, and then over Pakistan, before re-entering over Tibet.

    Following re-entry, the drogue chute deployed at an altitude of 30 km with the capsules soft-landing rockets firing 1.5 m above the ground. The capsule landed at 41 deg N, 105 deg E, (415 km East of its launch pad and 110 km north-west of Wuhai, Inner Mongolia), at November 20 19:41 UT. The spacecraft had completed 14 orbits of the earth in 21 hours and 11 minutes.

    After the flight it was reported that not a single primary spacecraft system had failed, so none of the back-up systems were tested. The touchdown point was only 12 km from the predicted position. The soft landing braking rocket worked well - no damage was found to the capsule structure, heat shield or the seals. The jettisoned heat shield, parachute hatch, and drogue chute were found within 5 km of the landing point. The orbital module, which separated prior to retro-fire, continued in controlled flight until 27 November, when it decayed and reentered the atmosphere. A primary payload returned by Shenzhou were 100 kg of seeds, considered valuable to the Chinese after one day of exposure to the space environment. The Chinese space tracking fleet returned from the Shenzhou mission between 12 December 1999 and 4 January 2000. During their 259-day voyage, the four ships traveled 185,000 km and experienced some heavy seas while tracking and communicating with the Shenzhou for a total of 150 minutes. Additional Details: here....


2000 January 25 - . 16:45 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-4 (60).
  • Zhongxing-22 - . Mass: 2,300 kg (5,000 lb). Nation: China. Agency: SISE. Manufacturer: CAST. Program: Chinasat. Class: Communications. Type: Military communications satellite. Spacecraft: FH-1. USAF Sat Cat: 26058 . COSPAR: 2000-003A. Apogee: 35,794 km (22,241 mi). Perigee: 35,781 km (22,233 mi). Inclination: 3.2000 deg. Period: 1,436.10 min. First Chinese military communications satellite. Perhaps an update of the DFH-3 design. Stationed at 98 deg E. The first in a planned constellation of satellites to be launched through 2010. Positioned in geosynchronous orbit at 98 deg E in 2000. As of 5 September 2001 located at 98.03 deg E drifting at 0.005 deg W per day. As of 2007 Mar 10 located at 97.95E drifting at 0.009W degrees per day.

2000 June 25 - . 11:50 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-13 (61).
  • Fengyun-2 - . Mass: 1,250 kg (2,750 lb). Nation: China. Agency: CASC. Manufacturer: Shanghai Institute of Satellite Engineering. Class: Earth. Type: Weather satellite. Spacecraft: FY-2. USAF Sat Cat: 26382 . COSPAR: 2000-032A. Apogee: 35,790 km (22,230 mi). Perigee: 35,786 km (22,236 mi). Inclination: 0.8000 deg. Period: 1,436.20 min. Second Fengyun-2 weather satellite, replacing the first FY-2 (retired in April after a three year service life). The spin-stabilised FY-2 fired its solid apogee motor early on Jun 26. By July 3, it was in a 35,791 x 35,804 km x 1.1 deg orbit drifting over the Pacific. Stationed at 104 deg E. Positioned in geosynchronous orbit at 110 deg E in 2000. As of 5 September 2001 located at 104.56 deg E drifting at 0.030 deg W per day. As of 2007 Mar 11 located at 34.70W drifting at 0.629W degrees per day.

2000 September 1 - . 03:25 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-4B. LV Configuration: Chang Zheng 4B CZ4B-3 (62).
  • ZY-2 - . Payload: Zi Yuan 2. Nation: China. Agency: SISE. Manufacturer: CAST. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: ZY. USAF Sat Cat: 26481 . COSPAR: 2000-050A. Apogee: 501 km (311 mi). Perigee: 489 km (303 mi). Inclination: 97.4000 deg. Period: 94.43 min. The ZY-2 (Ziyuan-2 ('Resource-2'), while disguised as a civilian earth monitoring system, was actually code-named Jianbing-3 and was China's first high-resolution military imaging satellite. The cover story of the official Xinhua news agency was that the civilian remote sensing system would be used primarily in territorial surveying, city planning, crop yield assessment, disaster monitoring and space science experimentation. However the satellite was placed at a much lower altitude than the ZY-1 satellite and US intelligence sources indicated that it was a photo-reconnaissance satellite for exclusively military purposes, such as targeting missiles at US and Taiwanese forces. The new satellite was believed to employ digital-imaging technology and to have a resolution of 2 m or less. The satellite was designed and built by the Chinese Academy of Space Technology and was developed indigenously. It was said to be more advanced than earlier sensing satellites and was expected to have an orbital life of two years. The camera provided more than three times the resolution of the ZY-1 earth resources satellite. The Zi Yuan 2 satellite may have used the CBERS Sino-Brazilian bus of the earlier ZY-1. However it was also said to be of new design and demonstrated the capability to maneuver in orbit, adjusting its orbit after launch. In October 2000 Chinese scientists denied that the ZY-2 satellite had a military mission. It was said to be a remote-sensing satellite equipped with CCD cameras and an infrared multispectral scanner that could only identify objects on the ground with a resolution of several dozen meters to 1 km.

2000 October 14 - . LV Family: CZ; CZ-1; CZ-NGLV.
  • China Reveals New Launcher Detail - . Nation: China. During the International Astronautical Federation (IAF) annual congress in Rio de Janeiro, China unveiled deatils of its new CZ-5 heavy launch vehicle family. Powered by kerosene/LOX/LH2 engines and four strap-on boosters, the new 800-ton, 50-55-meter high launcher would be capable of lifting 23 tonnes into LEO and 11 tonnes into geostationary transfer orbit. The CZ-2E(A), equipped with new avionics from the man-rated CZ-2F, was to be tested by 2003. The CZ-1D small launcher was slated to make its first flight in 2001, while yet another small launcher, a 4 stage solid rocket, was under design.

2000 October 30 - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-5 (63).
  • Beidou 1A - . Mass: 2,200 kg (4,800 lb). Nation: China. Agency: CNSA. Manufacturer: CAST. Class: Navigation. Type: Navigation satellite. Spacecraft: Beidou. USAF Sat Cat: 26599 . COSPAR: 2000-069A. Apogee: 35,805 km (22,248 mi). Perigee: 35,774 km (22,228 mi). Inclination: 2.6000 deg. Period: 1,436.20 min. Beidou was China's first experimental navigation technology satellite, developed by CAST/Beijing. The satellite was placed in an initial 195 x 41889 km x 25.0 deg orbit geostationary transfer orbit before entering its final geosynchornous orbit at around 0500 GMT on November 6. Stationed at 140 deg E, still maintaining its position within 0.1 deg as of 2007.

2000 December 20 - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-6 (64).
  • Beidou 1B - . Mass: 2,200 kg (4,800 lb). Nation: China. Agency: CNSA. Manufacturer: CAST. Class: Navigation. Type: Navigation satellite. Spacecraft: Beidou. USAF Sat Cat: 26643 . COSPAR: 2000-082A. Apogee: 35,821 km (22,258 mi). Perigee: 35,753 km (22,215 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Second Beidou geosynchronous navigation satellite. The CZ-3A rocket's third stage put Beidou in geostationary transfer orbit at around 1642 GMT. The Beidou satellite was based on the DFH-3 comsat and had a mass of around 2200 kg including its FY-25 solid apogee motor. On December 25 Beidou was in a 190 x 41870 km x 25.0 deg transfer orbit. The launch of this second Beidou completed the prototype two-satellite navigational system which was to provide positional information for highway, railway and marine transportation. Positioned in geosynchronous orbit at 80 deg E, still maintaining its position within 0.1 deg as of 2007.

2001 January 9 - . 17:00 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS. LV Family: CZ. Launch Vehicle: CZ-2F. LV Configuration: Chang Zheng 2F CZ2F-2 (65).
  • Shenzhou 2 - . Mass: 7,400 kg (16,300 lb). Nation: China. Agency: CASC. Manufacturer: CALT. Class: Manned. Type: Manned spacecraft. Spacecraft: Shenzhou. Duration: 6.77 days. Decay Date: 2001-01-16 . USAF Sat Cat: 26664 . COSPAR: 2001-001A. Apogee: 345 km (214 mi). Perigee: 330 km (200 mi). Inclination: 42.6000 deg. Period: 91.30 min. The second unmanned test flight of the Shenzhou manned spacecraft design carried a monkey, a dog and a rabbit in a test of the spaceship's life support systems. Shenzhou 2 was the first test of an all-up flight model of the spacecraft, with a functioning orbital module. It was also the most ambitious space science laboratory ever launched by China. It carried 64 scientific payloads: 15 in the re-entry module, 12 in the orbital module and 37 on the forward external pallet. These included a micro-gravity crystal growing device; life sciences experiments with 19 species of animals and plants, cosmic ray and particle detectors; and China's first gamma ray burst detectors.

    The launch was originally scheduled for January 5, but the second stage of the launch vehicle was dented by an access platform while being prepared for roll-out in the vehicle assembly building. This caused several days of delay until it was cleared for flight. Shenzhou 2 made three orbit-raising manoeuvres during its flight, reaching a 330 x 345 km orbit by the end of the initial phase of the mission. Ninety minutes before landing the orbital module depressurised, and the spacecraft went briefly out of control. However this was regained after venting of the atmosphere from the module ended. The descent module and service modules separated from the forward orbital module and external pallet normally. After retrofire by the service module, it separated and the descent module landed at 11:22 GMT on January 16 in Inner Mongolia. Lack of post-recovery photographs led to speculation that the recovery may not have been completely successful. The Shenzhou orbital module had its own solar panels and remained operational in orbit, conducting scientific experiments. It was actively controlled for six months, maneuvering in orbit several times (reaching a final orbit of 394 x 405 km). It then was allowed to decay and reentered the atmosphere at 09:05 GMT on August 24, 2001. The reentry point was near 33.1 deg S in latitude and 260.4 deg E in longitude, over the western Pacific Ocean between Easter Island and Chile.


2002 March 25 - . 14:15 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS. LV Family: CZ. Launch Vehicle: CZ-2F. LV Configuration: Chang Zheng 2F CZ2F-3 (66).
  • Shenzhou 3 - . Mass: 7,800 kg (17,100 lb). Nation: China. Agency: CAS. Manufacturer: CALT. Class: Manned. Type: Manned spacecraft. Spacecraft: Shenzhou. Duration: 6.78 days. Decay Date: 2002-04-01 . USAF Sat Cat: 27397 . COSPAR: 2002-014A. Apogee: 379 km (235 mi). Perigee: 374 km (232 mi). Inclination: 42.4000 deg. Period: 92.10 min. The third unmanned test of the Shenzhou spacecraft was delayed almost three months when a defective connector was found on the booster after roll-out to the pad in January 2002. The vehicle was disassembled, and all suspect connectors were replaced. The stand-down also revealed ten previously undetected defects in the space capsule. The spacecraft, the first all-up flight model with a functioning (but deactivated) launch escape system, was finally launched and placed into an initial 197 x 326 km x 42.4 deg orbit at 1425 UTC. At about 2120 UTC Shenzhou used its own engine to raise its orbit to 332 x 337 km. The capsule included a dummy astronaut instrumented to monitor life support systems. The descent module returned to Earth on April 1 at 0851 UTC, landing in Inner Mongolia. The orbital module remained in orbit to carry out further experiments, finally being deorbited on 12 November 2002. The spacecraft carried 44 scientific payloads, including a medium-resolution imaging radiometer developed by Chinese Academy of Sciences, installed on the instrument pallet atop the orbital module.

2002 May 15 - . 01:50 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-4B. LV Configuration: Chang Zheng 4B CZ4B-4 (67).
  • Haiyang 1 - . Mass: 360 kg (790 lb). Nation: China. Agency: CASC. Class: Earth. Type: Earth resources satellite. Spacecraft: HY-1. USAF Sat Cat: 27430 . COSPAR: 2002-024A. Apogee: 799 km (496 mi). Perigee: 785 km (487 mi). Inclination: 98.4000 deg. Period: 100.70 min. The HY-1 (Haiyang-1) marine observation satellite separated shortly after the FY-1D. The 360 kg HY-1 was based on the SJ-5 bus and carried an IR radiometer and CCD imager for oceanographic studies. Between May 21 and May 26, HY-1 lowered its orbit to 793 x 799 km using on-board propulsion.
  • Feng Yun 1D - . Mass: 960 kg (2,110 lb). Nation: China. Agency: CASC. Class: Earth. Type: Weather satellite. Spacecraft: FY-1. USAF Sat Cat: 27431 . COSPAR: 2002-024B. Apogee: 873 km (542 mi). Perigee: 850 km (520 mi). Inclination: 98.7000 deg. Period: 102.20 min. The second stage separated six minutes after launch, putting the stack on a suborbital trajectory. After a brief coast up to 860 km the third stage fired at around 0200 UTC to circularize the orbit. FY-1D, a 950 kg weather satellite with a 10-channel radiometer, separated from the stack followed by a small adapter. The final stage was left in a slightly lower 812 x 883 km orbit.

2002 October 27 - . 03:17 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-4B. LV Configuration: Chang Zheng 4B CZ4B-5 (68).
  • ZY-2 - . Payload: Zi Yuan 2-2. Nation: China. Agency: CAST. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: ZY. USAF Sat Cat: 27550 . COSPAR: 2002-049A. Apogee: 483 km (300 mi). Perigee: 470 km (290 mi). Inclination: 97.4000 deg. Period: 94.10 min. JB-3 2 was nominally a Chinese (PRC) remote sensing satellite, although US intelligence sources indicated it had primarily an intelligence imaging mission. JB-3 2 was the name adopted by the USSPACECOM. Most news reports from China and elsewhere use different names: ZY-2B (acronym for ZiYuan-2B, translated as Resource-2B), and Zhong Guo Zi Yuan Er Hao, translated as China Resource 2. No information was available on the instruments onboard the JB-3 2, but officially it was intended 'for territorial survey, environment monitoring and protection, urban planning, crop yield assessment, disaster monitoring, and space scientific experiments'. The initial orbital parameters of this sun-synchronous satellite were period 94.1 min, apogee 483 km, perigee 470 km, and inclination 97.4.

2002 December 29 - . 16:49 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS. LV Family: CZ. Launch Vehicle: CZ-2F. LV Configuration: Chang Zheng 2F CZ2F-4 (69).
  • Shenzhou 4 - . Mass: 7,794 kg (17,182 lb). Nation: China. Agency: CAS. Manufacturer: CALT. Class: Manned. Type: Manned spacecraft. Spacecraft: Shenzhou. Duration: 6.77 days. Decay Date: 2003-01-05 . USAF Sat Cat: 27630 . COSPAR: 2002-061A. Apogee: 337 km (209 mi). Perigee: 331 km (205 mi). Inclination: 42.4000 deg. Period: 91.20 min. Final unmanned test of the Shenzhou spacecraft. First night launch of the CZ-2F was viewed by Party leaders on a very cold but clear night. The spacecraft carried fifty-two science payloads in four main areas: microwave Earth observation, space environment monitoring, microgravity fluid physics, and biological technology research. The spacecraft's reentry capsule was successfully recovered on 5 January 2003 at 1116 UT. The Chinese released the news and photographs of the capsule in the dusk snow only an hour later. The landing site was 40 km from Hohhot (40.51deg N, 111.38 deg E). As in prior missions, the orbital module continued in orbit. Chinese astronauts trained on the actual flight hardware before the launch and it was officially announced that this successful mission set the stage for a first Chinese manned spaceflight in the second half of 2003. Western observors noted that the orbit and ground track allowed launch of a second rendezvous vehicle, an indication of future manned space station missions. Shenzhou 4 carried 52 scientific payloads including a microwave radiometer using a reflector antenna, installed on top of the orbital module.

2003 May 24 - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-7 (70).
  • Beidou 2A - . Mass: 2,200 kg (4,800 lb). Nation: China. Agency: SISE. Class: Navigation. Type: Navigation satellite. Spacecraft: Beidou. USAF Sat Cat: 27813 . COSPAR: 2003-021A. Apogee: 35,836 km (22,267 mi). Perigee: 35,760 km (22,220 mi). Inclination: 0.3000 deg. Period: 1,436.70 min. Summary: Navigation technology satellite, joined Beidou 1A and 1B launched in December 2000. This third satellite was considered a back-up element, Positioned at 110 deg E, still maintaining its position within 0.1 deg as of 2007..

2003 October 15 - . 01:00 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS. LV Family: CZ. Launch Vehicle: CZ-2F.
  • Shenzhou 5 Orbital Module - . Mass: 1,100 kg (2,400 lb). Nation: China. Agency: SISE. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Shenzhou OM. Decay Date: 2004-05-30 . USAF Sat Cat: 28049 . COSPAR: 2003-045G. Apogee: 347 km (215 mi). Perigee: 338 km (210 mi). Inclination: 42.4000 deg. Period: 91.40 min. The Shenzhou 5 orbital module was essential an unmanned military reconnaisance satellite. It was never entered by the astronaut during the mission, and was equipped with two high resolution (1.6 m) surveillance cameras. It was expected to operate until at least spring 2004.
  • Shenzhou 5 - . Crew: Yang Liwei. Backup Crew: Zhai Zhigang. Support Crew: Nie Haisheng. Mass: 7,840 kg (17,280 lb). Nation: China. Related Persons: Yang Liwei; Zhai Zhigang; Nie Haisheng. Agency: PLAAF. Manufacturer: CALT. Class: Manned. Type: Manned spacecraft. Flight: Shenzhou 5. Spacecraft: Shenzhou. Duration: 0.89 days. Decay Date: 2003-10-16 . USAF Sat Cat: 28043 . COSPAR: 2003-045A. Apogee: 336 km (208 mi). Perigee: 332 km (206 mi). Inclination: 42.4192 deg. Period: 91.20 min. China's first manned spaceflight began with the lift-off of the CZ-2F booster into the clear blue morning sky. All went according to plan and China's first man in space, Yang Liwei, entered an initial 200 km x 343 km orbit ten minutes after launch. The naval vessels standing buy for rescue in the Sea of Japan were called back to port.

    The highly conservative mission plan was for Yang to remain in the Shenzhou re-entry capsule for the entire 21-hour mission, and not to enter the orbital module. He had two rest periods of three hours each, and was scheduled to eat once or twice meals of what was said to be a superior form of Chinese space food. Frequent communications sessions, including colour television links to the spacecraft, were made possible by China's four tracking ships deployed in the oceans of the world.

    As the spacecraft was in its 21st orbit, the orbital module separated. It would stay in the 343 km orbit for a planned six-month military imaging reconnaissance mission. Retrofire was commanded via a tracking ship in the Atlantic off the coast of Africa. Shenzhou-5 landed only 4.8 km from the aim-point in Inner Mongolia with the parachute being sighted by the ground recovery forces prior to landing. Yang landed after 21 hours 23 minutes aloft.


2003 October 21 - . 03:16 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-4B. LV Configuration: Chang Zheng 4B CZ4B-6 (72).
  • ZY-1-2 (CBERS-2) - . Payload: Zi Yuan 1B. Mass: 1,500 kg (3,300 lb). Nation: China. Agency: CAS. Class: Earth. Type: Earth resources satellite. Spacecraft: ZY. USAF Sat Cat: 28057 . COSPAR: 2003-049A. Apogee: 750 km (460 mi). Perigee: 731 km (454 mi). Inclination: 98.5000 deg. Period: 99.60 min. Summary: Delayed from late 2001, September 3 2002, March 14 and September 2003. Second China-Brazil Earth Resources Satellite (CBERS 2)..
  • CX-1 - . Payload: Chuang Xin 1. Nation: China. Agency: CAS. Class: Technology. Type: Communications technology satellite. Spacecraft: CX-1. USAF Sat Cat: 28058 . COSPAR: 2003-049B. Apogee: 759 km (471 mi). Perigee: 686 km (426 mi). Inclination: 98.5000 deg. Period: 99.20 min. Chuangxin-1 (or Innovation-1) was China's first experimental small satellite for store-and-forward short message data communications in low Earth orbit. With a mass less than 100 kg, the Chuangxin-1 was developed in light of national strategic demands. Starting from 1999 with support of the national Knowledge Innovation Program of the Chinese Academy of Sciences (CAS), the project was carried out jointly by researchers from the CAS Shanghai Institute of Microsystem Information Technology and the CAS Shanghai Institute of Technical Physics. The satellite used spread spectrum communication and subsystems included a communication transponder, onboard computer, attitude control, energy source, thermal control, and structure. The mission was to demonstrate data communications for such sectors as traffic and transportation, environment protection, oil and gas transportation, flood and drought control, detection of forest fire and earthquake monitoring.

2003 November 2 - . 07:20 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS-2. LV Family: CZ. Launch Vehicle: CZ-2D. LV Configuration: Chang Zheng 2D CZ2D-4 (73).
  • FSW-3 No. 1 - . Payload: FSW-18, FSW-3.1, Jianbing 4. Mass: 3,000 kg (6,600 lb). Nation: China. Agency: SAST. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Decay Date: 2003-12-18 . USAF Sat Cat: 28078 . COSPAR: 2003-051A. Apogee: 165 km (102 mi). Perigee: 141 km (87 mi). Inclination: 63.0000 deg. Period: 87.50 min. Summary: Expected to have been long-awaited 'seeds in space' mission but official announcements spoke only of photography..

2003 November 14 - . 16:01 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-8 (74).
  • Zhongxing 20 - . Payload: Feng Huo 2. Mass: 2,300 kg (5,000 lb). Nation: China. Agency: SISE. Program: Chinasat. Class: Communications. Type: Military communications satellite. Spacecraft: DFH-3. USAF Sat Cat: 28082 . COSPAR: 2003-052A. Apogee: 35,811 km (22,251 mi). Perigee: 35,762 km (22,221 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: Military communications satellite. As of 2007 Mar 11 located at 103.00E drifting at 0.010W degrees per day..

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 September 8 - . 23:14 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-4B. LV Configuration: Chang Zheng 4B CZ4B-7 (79).
  • SJ-6A - . Payload: Shi Jian 6B. Nation: China. Agency: SISE. Class: Technology. Type: Navigation technology satellite. Spacecraft: SJ-6. USAF Sat Cat: 28413 . COSPAR: 2004-035A. Apogee: 593 km (368 mi). Perigee: 578 km (359 mi). Inclination: 97.7000 deg. Period: 96.40 min. It was announced that the two satellites had a design life of at least two years, and would be used to probe the space environment, radiation and its effects, record space physical environment parameters, and conduct other related space experiments. The two satellites were built by the Shanghai Academy of Space Flight Technology and Dongfanghong Satellite Company under subcontract to the China Aerospace Science and Technology Corporation. The scientific instruments aboard the satellites were mainly manufactured by the China Electronics Technology Corporation. Some Western observors believed the mission of the satellites included electronic intelligence technology tests.
  • SJ-6B - . Payload: Shi Jian 6A. Nation: China. Agency: SISE. Class: Technology. Type: Navigation technology satellite. Spacecraft: SJ-6. USAF Sat Cat: 28414 . COSPAR: 2004-035B. Apogee: 602 km (374 mi). Perigee: 593 km (368 mi). Inclination: 97.7000 deg. Period: 96.60 min. Summary: CAST968 platform. Released one minute after SJ-6A..

2004 September 27 - . 08:00 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS. LV Family: CZ. Launch Vehicle: CZ-2D. LV Configuration: Chang Zheng 2D CZ2D-5 (80).
  • FSW-3 No. 3 - . Payload: FSW 20. Nation: China. Agency: SISE. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 17.78 days. Decay Date: 2004-11-09 . USAF Sat Cat: 28424 . COSPAR: 2004-039A. Apogee: 297 km (184 mi). Perigee: 205 km (127 mi). Inclination: 63.0000 deg. Summary: Recoverable military satellite. Returned to Earth at 02:48 GMT on October 15, falling through the roof of a house in the village of Penglai, Sichuan province..

2004 October 19 - . 01:20 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-9 (81).
  • FY-2C - . Mass: 1,380 kg (3,040 lb). Nation: China. Agency: SISE. Class: Earth. Type: Weather satellite. Spacecraft: FY-2. USAF Sat Cat: 28451 . COSPAR: 2004-042A. Apogee: 35,791 km (22,239 mi). Perigee: 35,786 km (22,236 mi). Inclination: 0.7000 deg. Period: 1,436.20 min. Third Fengyun-2 weather satellite. The apogee motor placed the satellite into a drifting geostationary orbit. As of the date of the launch, four FY-2 satellites had been launched. FY-2 01 was destroyed in a ground fire 1994. FY-2 02 / FY-2A was placed in reserve in May 2000 86 deg E; and FY-2 03 / FY-2B was operational at 123 deg E. As of 2007 Mar 11 located at 104.44E drifting at 0.026W degrees per day.

2004 November 6 - . 03:10 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-4B. LV Configuration: Chang Zheng 4B CZ4B-8 (82).
  • ZY-2C - . Nation: China. Agency: SISE. Class: Earth. Type: Earth resources satellite. Spacecraft: ZY. USAF Sat Cat: 28470 . COSPAR: 2004-044A. Apogee: 504 km (313 mi). Perigee: 479 km (297 mi). Inclination: 97.3000 deg. Period: 94.40 min. Summary: Zi Yuan 2-3 was a low earth orbit digital imaging spacecraft used by the Chinese government, probably for both civilian and military reconnaissance purposes..

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 April 12 - . 12:00 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3B. LV Configuration: Chang Zheng 3B CZ3B (84).
  • APSTAR 6 - . Payload: Apstar 5B / Spacebus 4000C2. Mass: 4,680 kg (10,310 lb). Nation: China. Agency: APT. Program: Apstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Spacebus 4000. USAF Sat Cat: 28638 . COSPAR: 2005-012A. Apogee: 35,795 km (22,241 mi). Perigee: 35,778 km (22,231 mi). Inclination: 0.0200 deg. Period: 1,436.09 min. Summary: Delayed from November, December 4, 2004. Ku and C band transponders. As of 2007 Mar 11 located at 133.99E drifting at 0.013W degrees per day..

2005 July 5 - . 22:40 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS-2. Launch Pad: SLS-2?. LV Family: CZ. Launch Vehicle: CZ-2D. LV Configuration: Chang Zheng 2D CZ2D-6 (85).
  • SJ-7 - . Payload: Shi Jian 7. Nation: China. Manufacturer: CASC. Spacecraft: SJ. USAF Sat Cat: 28737 . COSPAR: 2005-024A. Apogee: 573 km (356 mi). Perigee: 555 km (344 mi). Inclination: 97.6000 deg. Period: 95.90 min.

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..

2005 August 29 - . 08:45 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2D. LV Configuration: Chang Zheng 2D CZ2D-7 (87).
  • FSW-3 No. 5 - . Payload: FSW-22. Mass: 3,000 kg (6,600 lb). Nation: China. Agency: CAST. Manufacturer: SAST. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 49.00 days. Decay Date: 2005-10-17 . USAF Sat Cat: 28824 . COSPAR: 2005-033A. Apogee: 224 km (139 mi). Perigee: 178 km (110 mi). Inclination: 63.0000 deg. Period: 88.50 min. Summary: Decayed 17 October 2005..

2005 October 12 - . 01:00 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS. LV Family: CZ. Launch Vehicle: CZ-2F. LV Configuration: Chang Zheng 2F CZ2F-6 (88).
  • Shenzhou 6 - . Crew: Fei Junlong; Nie Haisheng. Backup Crew: Liu Buoming; Jing Haipen. Return Crew: Zhai Zhigang; Wu Jie. Mass: 8,040 kg (17,720 lb). Nation: China. Related Persons: Fei Junlong; Nie Haisheng; Liu Buoming; Jing Haipen; Zhai Zhigang; Wu Jie. Agency: SISE. Class: Manned. Type: Manned spacecraft. Flight: Shenzhou 6. Spacecraft: Shenzhou. Duration: 4.81 days. Decay Date: 2005-10-16 . USAF Sat Cat: 28879 . COSPAR: 2005-040A. Apogee: 338 km (210 mi). Perigee: 331 km (205 mi). Inclination: 42.4000 deg. Period: 91.20 min. Moved up from October 13. Second Chinese manned space mission. The two-astronaut crew spent 5 days in space, and worked in the Shenzhou orbital module for the first time. Aside from biomedical experiments, the nature of their work was not divulged, and few images of the interior of the orbital module (with its probable military experiments) were released.

2006 April 26 - . 22:48 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-4B. LV Configuration: Chang Zheng 4B CZ4B-9 (89).
  • Yaogan 1 - . Mass: 2,700 kg (5,900 lb). Nation: China. Agency: CNSA. Manufacturer: CASC. Class: Surveillance. Type: Military surveillance radar satellite. Spacecraft: Yaogan. USAF Sat Cat: 29092 . COSPAR: 2006-015A. Apogee: 630 km (390 mi). Perigee: 627 km (389 mi). Inclination: 97.8000 deg. Period: 97.30 min. Summary: Remote sensing satellite built by the Shanghai SAST Group. In reality it was the first Chinese synthetic aperture radar military surveillance satellite..

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..

2006 September 12 - . 16:02 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-10 (91).
  • Zhongxing 22A - . Mass: 2,300 kg (5,000 lb). Nation: China. Agency: CTBSC. Manufacturer: CAST. Program: Chinasat. Class: Communications. Type: Military communications satellite. Spacecraft: FH-1. USAF Sat Cat: 29398 . COSPAR: 2006-038A. Apogee: 35,817 km (22,255 mi). Perigee: 35,757 km (22,218 mi). Inclination: 0.4000 deg. Period: 1,000.00 min. Summary: Military communications satellite, launched to replace Zhongxing 22 in geosynchronous orbit at 98.0 E. As of 2007 Mar 10 located at 98.10E drifting at 0.006W degrees per day..

2006 October 23 - . 23:34 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-4B. LV Configuration: Chang Zheng 4B CZ4B-10 (92).
  • SJ-6-2A SJ-6C - . Nation: China. Agency: SISE. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: SJ-6. USAF Sat Cat: 29505 . COSPAR: 2006-046A. Apogee: 598 km (371 mi). Perigee: 594 km (369 mi). Inclination: 97.7000 deg. Period: 96.60 min. Summary: Replaced the SJ-6 Group 1 satellites A and B. Official purpose was to measure the space environment, but foreign analysts suspected a SIGINT role..
  • SJ-6-2B SJ-6D - . Nation: China. Agency: SISE. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: SJ-6. USAF Sat Cat: 29506 . COSPAR: 2006-046B. Apogee: 599 km (372 mi). Perigee: 598 km (371 mi). Inclination: 97.7000 deg. Period: 96.70 min.

2006 October 28 - . 16:20 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3B. LV Configuration: Chang Zheng 3B CZ3B (93).
  • Xinnuo 2 - . Payload: Sinosat-2. Mass: 5,100 kg (11,200 lb). Nation: China. Agency: SISE. Class: Communications. Type: Military communications satellite. Spacecraft: DFH-4. USAF Sat Cat: 29516 . COSPAR: 2006-048A. Apogee: 35,911 km (22,314 mi). Perigee: 35,675 km (22,167 mi). Inclination: 0.0600 deg. Period: 1,436.44 min. First DH-4 heavy Chinese communication satellite with communications equipment provided by Alcatel Alenia. Mission failed when solar panels and antennae failed to deploy in geosynchronous orbit. This was a blow to China's prestige, since the satellite was an important part of the 2008 Beijing Olympics coverage plans. As of 2007 Mar 10 located at 91.80E drifting at 0.093W degrees per day.

2006 December 8 - . 00:53 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-11 (94).
  • FY 2D - . Payload: Fengyun 2D. Nation: China. Agency: SISE. Class: Earth. Type: Weather satellite. Spacecraft: FY-2. Decay Date: 2006-12-09 . USAF Sat Cat: 29641 . COSPAR: 2006-053B. Apogee: 35,789 km (22,238 mi). Perigee: 35,781 km (22,233 mi). Inclination: 2.6000 deg. Period: 1,436.00 min. Fourth Wind and Cloud 2 geostationary weather satellite with an infrared radiometer as its primary instrument. The booster placed the spacecraft in a 226 x 36221 km x 24.9 deg geosynchronous transfer orbit. The FG-36 solid apogee motor aboard the satellite burned at 18:07 GMT and placed the FY-2D into an initial 35786 x 36478 km x 2.6 deg geosynchronous drift orbit.

2007 February 2 - . 16:28 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-12 (95).
  • Beidou G1 - . Payload: Beiduou 1D. Mass: 2,200 kg (4,800 lb). Nation: China. Agency: SISE. Class: Navigation. Type: Navigation satellite. Spacecraft: Beidou. USAF Sat Cat: 30323 . COSPAR: 2007-003A. Apogee: 36,248 km (22,523 mi). Perigee: 35,326 km (21,950 mi). Inclination: 6.2000 deg. Period: 1,436.10 min. Summary: Fourth Beidou satellite. It did not reach geostationary orbit until early April following deployment problems with its solar panels and reports of US detection of a debris cloud at the time of the original expected apogee firing..

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..

2007 April 12 - . 20:11 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-13 (97).
  • Beidou M1 - . Payload: Beidou M1. Mass: 2,200 kg (4,800 lb). Nation: China. Agency: CASC. Manufacturer: CAST. Class: Navigation. Type: Navigation satellite. Spacecraft: Beidou. USAF Sat Cat: 31115 . COSPAR: 2007-011A. Apogee: 21,544 km (13,386 mi). Perigee: 21,519 km (13,371 mi). Inclination: 55.3000 deg. Period: 773.40 min. Summary: The fifth Beidou satellite, but the first in the 12-hour, 55 deg inclination MEO portion of the constellation. All previous launches had been to populate the geostationary portion of the system..

2007 May 13 - . 16:01 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3B. LV Configuration: Chang Zheng 3B CZ3B (98).
  • Nigcomsat 1 - . Mass: 5,150 kg (11,350 lb). Nation: Nigeria. Agency: NCS. Class: Communications. Type: Civilian communications satellite. Spacecraft: DFH-4. USAF Sat Cat: 31395 . COSPAR: 2007-018A. Apogee: 35,789 km (22,238 mi). Perigee: 35,782 km (22,233 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Second DFH-4 communications satellite; China's first commercial payload sale, and Nigeria's first commercial communications satellite. Positioned at 42.5 deg E. Payload consisted of 4 C-band, 14 Ku-band, 8 Ka-band, and 2 L-band transponders. The antenna subsystem consisted of seven antennas.

2007 May 25 - . 07:12 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2D. LV Configuration: Chang Zheng 2D CZ2D-8 (99).
  • Yaogan 2 - . Mass: 2,700 kg (5,900 lb). Nation: China. Agency: CNSA. Manufacturer: CAST. Class: Surveillance. Type: Military surveillance radar satellite. Spacecraft: Yaogan. USAF Sat Cat: 31490 . COSPAR: 2007-019A. Apogee: 655 km (406 mi). Perigee: 631 km (392 mi). Inclination: 97.8000 deg. Period: 97.60 min. Summary: Second Chinese synthetic aperture radar military surveillance satellite..
  • Zheda Pixing 1 - . Mass: 2.00 kg (4.40 lb). Nation: China. Agency: Zhejiang. Manufacturer: SIMIT. Class: Technology. Type: Navigation technology satellite. Spacecraft: Zheda Pixing. COSPAR: 2007-019x. Summary: Experimental microelectronics research picosatellite..

2007 May 31 - . 16:08 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-14 (100).
  • Sinosat 3 - . Mass: 2,200 kg (4,800 lb). Nation: China. Agency: SinoSatCom. Manufacturer: CAST. Program: Sinosat. Class: Communications. Type: Civilian communications satellite. Spacecraft: DFH-3. USAF Sat Cat: 31577 . COSPAR: 2007-021A. Apogee: 35,793 km (22,240 mi). Perigee: 35,779 km (22,231 mi). Inclination: 0.3000 deg. Period: 1,436.10 min. Summary: Chinese C-band domestic communications satellite, launched as part of a campaign to prepare for the 2008 Olympic Games, and to compensate for failure of the first DFH-4 satellite..

2007 July 5 - . 12:08 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3B. LV Configuration: Chang Zheng 3B CZ3B (101).
  • Chinasat 6B - . Payload: Spacebus 4000C2. Mass: 4,600 kg (10,100 lb). Nation: China. Agency: ChinaSatCom. Manufacturer: Alenia. Program: Chinasat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Spacebus 4000. USAF Sat Cat: 31800 . COSPAR: 2007-031A. Apogee: 35,797 km (22,243 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.0200 deg. Period: 1,436.07 min. Summary: Direct broadcast satellite, capable of transmitting 300 television channels using 38 transponders. To be positioned at 115.5 deg E, beaming signals to China, Southeast Asia, and Oceania. Planned mission life 15 years..

2007 September 19 - . 03:26 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: CZ-4B. LV Configuration: Chang Zheng 4B CZ4B (102).
  • CBERS-2B - . Mass: 1,452 kg (3,201 lb). Nation: China; Brazil. Agency: SISE. Class: Surveillance. Type: Civilian surveillance satellite. Spacecraft: ZY. USAF Sat Cat: 32062 . COSPAR: 2007-042A. Apogee: 775 km (481 mi). Perigee: 773 km (480 mi). Inclination: 98.5000 deg. Period: 100.30 min. Third China-Brazil joint earth resources satellite. Much higher resolution optics and multispectral sensors expected to be useful for some military applications as well. The satellite raised its orbit to its operational altitude of 773 km two days after launch.

2007 October 24 - . 10:05 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. Launch Pad: LC1?. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-15 (103).
  • Chang'e 1 - . Mass: 2,300 kg (5,000 lb). Nation: China. Agency: SISE. Class: Moon. Type: Lunar probe. Spacecraft: Chang'e. USAF Sat Cat: 32273 . COSPAR: 2007-051B. Apogee: 50,182 km (31,181 mi). Perigee: 147 km (91 mi). Inclination: 30.8000 deg. Period: 929.20 min. China's first unmanned lunar/planetary probe. The initial orbit of 221 x 50,602 km x 31.0 deg was raised to a translunar trajectory by 31 October in a serious of spacecraft engine burns. The spacecraft entered a 210 km x 8600 km lunar orbit at 03:37 GMT on 5 November.

2007 November 11 - . 22:48 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: CZ-4C. LV Configuration: Chang Zheng 4C CZ4C (104).
  • Yaogan 3 - . Mass: 2,700 kg (5,900 lb). Nation: China. Agency: SISE. Class: Surveillance. Type: Civilian surveillance radar satellite. Spacecraft: Yaogan. USAF Sat Cat: 32289 . COSPAR: 2007-055A. Apogee: 629 km (390 mi). Perigee: 628 km (390 mi). Inclination: 97.8000 deg. Period: 97.30 min. Summary: The military launch used a new version of the CZ-4 booster. The CZ-4C includes a restart capability in the upper stage and a new interstage adapter between the first and second stages..

2008 April 25 - . 15:35 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3C. LV Configuration: CZ-3C s/n CZ3C1.
  • Tian Lian 1 - . Payload: DFH 76. Mass: 3,000 kg (6,600 lb). Nation: China. Agency: SISE. Class: Communications. Type: Military communications satellite. Spacecraft: DFH-4. USAF Sat Cat: 32779 . COSPAR: 2008-019A. Apogee: 35,806 km (22,248 mi). Perigee: 35,768 km (22,225 mi). Inclination: 0.4000 deg. Period: 1,436.10 min. China's first in a series of new data relay satellites, and the first launch of the CZ-3C, a variant of the Long March with two liquid strap-ons. The satellite will relay data from Chinese manned and military satellites, beginning with the Shenzhou mission, from geostationary orbit at 77 deg E. Configuration unknown, but possibly based on the DFH-4 platform.

2008 May 27 - . 03:02 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: CZ-4C.
  • FY-3A - . Nation: China. Agency: SISE. Class: Earth. Type: Weather satellite. Spacecraft: FY-3. USAF Sat Cat: 32958 . COSPAR: 2008-026A. Apogee: 828 km (514 mi). Perigee: 826 km (513 mi). Inclination: 98.8000 deg. Period: 101.40 min. Summary: Polar orbiting weather satellite. The FY-3 series will replace the older FY-1 polar system..

2008 June 9 - . 12:15 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3B.
  • Zhongxing 9 - . Nation: China. Agency: SISE. Program: Chinasat. Class: Communications. Type: Military communications satellite. Spacecraft: Spacebus 4000. USAF Sat Cat: 33051 . COSPAR: 2008-028A. Apogee: 35,804 km (22,247 mi). Perigee: 35,770 km (22,220 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: Launched to support Olympic games; 22 J-band transponders; positioned at 92.2 deg E..

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.

2008 September 25 - . 13:10 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS. LV Family: CZ. Launch Vehicle: CZ-2F. LV Configuration: CZ-2F s/n CZ2F7.
  • Shenzhou 7 - . Crew: Zhai Zhigang; Liu Buoming; Jing Haipen. Mass: 7,840 kg (17,280 lb). Nation: China. Related Persons: Zhai Zhigang; Liu Buoming; Jing Haipen. Agency: SISE. Class: Manned. Type: Manned spacecraft. Flight: Shenzhou 7. Spacecraft: Shenzhou. Duration: 2.85 days. Decay Date: 2008-09-28 . USAF Sat Cat: 33386 . COSPAR: 2008-047A. Apogee: 336 km (208 mi). Perigee: 329 km (204 mi). Inclination: 42.4000 deg. Period: 91.20 min. Third Chinese manned space mission. The crew consisted of Zhai Zhigang, backup astronaut for China's first manned space mission; and Liu Buoming and Jing Haipeng, backups for the second mission. The astronauts demonstrated the capability of the Shenzhou spacecraft to carry its full complement of three crew for the first time. Zhai, wearing a Chinese-developed Feitian space suit, emerged from the orbital module of the Shenzhou and became China's first astronaut to conduct a spacewalk. Liu, wearing a proven Russian Orlan spacesuit, remained in the depressurized orbital module, ready to assist Zhai in an emergency. A subsatellite, weighing 40 kg, was released after the EVA, and relayed back images of Shenzhou 7 from close range to a distance of several kilometers. The crew returned safely to earth in a pinpoint landing in Outer Mongolia, carried live on television. The orbital module remained in space, conducting space network experiments with the subsatellite.
  • BX-1 - . Mass: 40 kg (88 lb). Nation: China. Agency: SISE. Class: Technology. Type: Navigation technology satellite. Flight: Shenzhou 7. Spacecraft: Ban Xing. Decay Date: 2009-10-29 . USAF Sat Cat: 33392 . COSPAR: 2008-047G. Apogee: 331 km (205 mi). Perigee: 321 km (199 mi). Inclination: 42.4000 deg. Period: 91.00 min. Summary: BanXing (companion satellite) subsatellite released by Shenzhou 7. If maneuvered away and back to the Shenzhou orbital module after the mission..

2008 October 25 - . 01:15 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: CZ-4B.
  • SJ-6-03A - . Nation: China. Agency: SISE. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: SJ-6. USAF Sat Cat: 33408 . COSPAR: 2008-053A. Apogee: 603 km (374 mi). Perigee: 584 km (362 mi). Inclination: 97.7000 deg. Period: 96.50 min. Summary: Third pair in China's SJ military surveillance constellation. It has been suggested that each pair consists of two differing satellites, a smaller minisatellite built by SAST Shanghai and a larger 300-kg CAST-968 bus satellite from DFH..
  • SJ-6-03B - . Nation: China. Agency: SISE. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: SJ-6. USAF Sat Cat: 33409 . COSPAR: 2008-053B. Apogee: 605 km (375 mi). Perigee: 582 km (361 mi). Inclination: 97.7000 deg. Period: 96.50 min.

2008 October 29 - . 16:54 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3B. LV Configuration: CZ-3B s/n CZ3B11.
  • Simon Bolivar - . Mass: 5,100 kg (11,200 lb). Nation: Venezuela. Agency: SISE. Class: Communications. Type: Civilian communications satellite. Spacecraft: DFH-4. USAF Sat Cat: 33414 . COSPAR: 2008-055A. Apogee: 35,797 km (22,243 mi). Perigee: 35,777 km (22,230 mi). Inclination: 0.2000 deg. Period: 1,436.10 min. Summary: Venezuela's first satellite, a Chinese-built DFH-4 communications satellit with C-band and Ku-band transponders..

2008 November 5 - . 00:15 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2D.
  • Chuanxin-1-02 - . Nation: China. Agency: SISE. Class: Technology. Type: Navigation technology satellite. Spacecraft: CX-1. USAF Sat Cat: 33433 . COSPAR: 2008-056A. Apogee: 805 km (500 mi). Perigee: 785 km (487 mi). Inclination: 98.5000 deg. Period: 100.80 min. Summary: Microsat built by the Shanghai Institute of Microsystems and Information Technology) and the Shanghai Academy of Space Technology. The satellite was designed to collect and relay hydrological and meteorological data and data for disaster relief..
  • Shiyan Weixing 3 - . Nation: China. Agency: SISE. Class: Technology. Type: Navigation technology satellite. Spacecraft: Shiyan. USAF Sat Cat: 33434 . COSPAR: 2008-056B. Apogee: 806 km (500 mi). Perigee: 785 km (487 mi). Inclination: 98.5000 deg. Period: 100.80 min. Summary: Built by the Harbin Institute of Technology and the DFH Satellite Company for 'experiments on new technologies in atmospheric exploration'..

2008 December 1 - . 04:42 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2D. LV Configuration: CZ-2D s/n CZ2D10.
  • Yaogan Weixing 4 - . Nation: China. Agency: SISE. Class: Surveillance. Type: Military surveillance radar satellite. Spacecraft: Yaogan. USAF Sat Cat: 33446 . COSPAR: 2008-061A. Apogee: 654 km (406 mi). Perigee: 632 km (392 mi). Inclination: 97.9000 deg. Period: 97.60 min. Summary: Fourth 'Remote Sensing Satellite'; presumed military mission..

2008 December 15 - . 03:22 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: CZ-4B. LV Configuration: CZ-4B s/n CZ417.
  • Yaogan Weixing 5 - . Mass: 2,200 kg (4,800 lb). Nation: China. Agency: SISE. Class: Surveillance. Type: Military surveillance radar satellite. Spacecraft: Yaogan. USAF Sat Cat: 33456 . COSPAR: 2008-064A. Apogee: 496 km (308 mi). Perigee: 486 km (301 mi). Inclination: 97.4000 deg. Period: 94.40 min. One of the two different series of military surveillance satellites launched under the YW designation, although YW 5 was in a lower orbit similar to the ZY-2 satellites, lower than previous YW satellites. The launch vehicle was announced as a CZ-4B, but appeared to be a CZ-4B with the CZ-4C's restartable YF-40A upper stage under the larger CZ-4C nose fairing.

2008 December 23 - . 00:54 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3A.
  • FY-2E - . Nation: China. Agency: SISE. Class: Earth. Type: Weather satellite. Spacecraft: FY-2. USAF Sat Cat: 33463 . COSPAR: 2008-066A. Apogee: 35,806 km (22,248 mi). Perigee: 35,771 km (22,227 mi). Inclination: 2.6000 deg. Period: 1,436.20 min. Summary: Member of China's geosynchronous weather satellite constellation..

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 August 31 - . 09:28 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3B. LV Configuration: CZ-3B s/n CZ3B12.
  • Palapa D - . Payload: Spacebus 4000B3. Mass: 4,100 kg (9,000 lb). Nation: China. Agency: SISE. Program: Palapa. Class: Communications. Type: Communications satellite. Spacecraft: Spacebus 4000. USAF Sat Cat: 35812 . COSPAR: 2009-046A. Apogee: 35,795 km (22,241 mi). Perigee: 35,779 km (22,231 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: Early third stage cutoff left spacecraft in sub-geostationary transfer orbit of 217 km x 21,138 km at 22.4 deg inclination. It used its on-board system to reach an operational orbit, albeit with reduced life due to the propellant consumption..

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..

2009 December 9 - . 08:42 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2D. LV Configuration: CZ-2D s/n CZ2-34.
  • Yaogan Weixing 7 - . Nation: China. Agency: SISE. Spacecraft: Yaogan. USAF Sat Cat: 36110 . COSPAR: 2009-069A. Apogee: 659 km (409 mi). Perigee: 623 km (387 mi). Inclination: 97.8000 deg. Period: 97.50 min. Summary: Remote-Sensing Satellite, apparently a military optical surveillance satellite similar to YW-2 and YW-4..

2009 December 15 - . 02:31 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: CZ-4C. LV Configuration: CZ-4C s/n CZ4-18.
  • Yaogan Weixing 8 - . Mass: 1,040 kg (2,290 lb). Nation: China. Agency: SISE. Spacecraft: Yaogan. USAF Sat Cat: 36121 . COSPAR: 2009-072A. Apogee: 1,204 km (748 mi). Perigee: 1,193 km (741 mi). Inclination: 100.5000 deg. Period: 109.40 min. Summary: Sun-synchronous orbit low resolution imaging satellite, primarily for civilian Earth resource studies. Supplemental military missions may include weather forecasting..
  • Xi Wang 1 - . Mass: 50 kg (110 lb). Nation: China. Agency: SISE. Spacecraft: Oscar. USAF Sat Cat: 36122 . COSPAR: 2009-072B. Apogee: 1,205 km (748 mi). Perigee: 1,193 km (741 mi). Inclination: 100.5000 deg. Period: 109.40 min. Summary: Amateur radio satellite..

2010 January 16 - . 16:12 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3C. LV Configuration: CZ-3C s/n CZ3C3.
  • Beidou G3 - . Nation: China. Agency: SISE. Spacecraft: Beidou. USAF Sat Cat: 36287 . COSPAR: 2010-001A. Apogee: 35,972 km (22,351 mi). Perigee: 35,600 km (22,100 mi). Inclination: 1.8000 deg. Period: 1,436.10 min.

2010 March 5 - . 04:55 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-4C. LV Configuration: CZ-4C s/n CZ4-19.
  • Yaogan 9A - . Mass: 2,800 kg (6,100 lb). Nation: China. Agency: SISE. Class: Military. Type: Electronic intelligence satellite. Spacecraft: Yaogan. USAF Sat Cat: 36413 . COSPAR: 2010-009A. Apogee: 1,107 km (687 mi). Perigee: 1,075 km (667 mi). Inclination: 63.4000 deg. Period: 107.10 min.
  • Yaogan 9B - . Nation: China. Agency: SISE. Class: Military. Type: Electronic intelligence satellite. Spacecraft: Yaogan. USAF Sat Cat: 36414 . COSPAR: 2010-009B. Apogee: 1,107 km (687 mi). Perigee: 1,075 km (667 mi). Inclination: 63.4000 deg. Period: 107.10 min.
  • Yaogan 9C - . Nation: China. Agency: SISE. Class: Military. Type: Electronic intelligence satellite. Spacecraft: Yaogan. USAF Sat Cat: 36415 . COSPAR: 2010-009C. Apogee: 1,107 km (687 mi). Perigee: 1,074 km (667 mi). Inclination: 63.4000 deg. Period: 107.10 min.

2010 June 2 - . 15:53 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3C. LV Configuration: CZ-3C s/n CZ3C4.
  • Beidou G4 - . Nation: China. Agency: SISE. Class: Navigation. Type: Navigation satellite. Spacecraft: Beidou. USAF Sat Cat: 36590 . COSPAR: 2010-024A. Apogee: 35,796 km (22,242 mi). Perigee: 35,776 km (22,230 mi). Inclination: 1.8000 deg. Period: 1,436.00 min.

2010 June 15 - . 01:39 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2D. LV Configuration: CZ-2D s/n CZ2-35.
  • SJ-12 - . Nation: China. Agency: SISE. Class: Military. Type: Anti-satellite system. Spacecraft: SJ-12. USAF Sat Cat: 36596 . COSPAR: 2010-027A. Apogee: 602 km (374 mi). Perigee: 578 km (359 mi). Inclination: 97.7000 deg. Period: 96.50 min. Summary: Satellite inspector/interceptor. Carried out a close pass or even came in contact with the SJ-6/3A satellite on 19 August 2010. By 21 September was in a 580 km x 606 km x 97.8 deg orbit..

2010 July 31 - . 21:30 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3A.
  • Beidou IGS 1 - . Payload: Beidou DW5. Nation: China. Agency: SISE. Class: Navigation. Type: Navigation satellite. Spacecraft: Beidou. USAF Sat Cat: 36828 . COSPAR: 2010-036A. Apogee: 35,901 km (22,307 mi). Perigee: 35,680 km (22,170 mi). Inclination: 55.0000 deg. Period: 1,436.30 min. Summary: Fifth Beidou navigation satellite, placed in an inclined geosynchronous orbit..

2010 August 9 - . 22:49 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: CZ-4C.
  • Yaogan 10 - . Payload: Yaogan Weixing 10. Nation: China. Agency: SISE. Class: Surveillance. Type: Civilian surveillance radar satellite. Spacecraft: Yaogan. USAF Sat Cat: 36834 . COSPAR: 2010-038A. Apogee: 630 km (390 mi). Perigee: 627 km (389 mi). Inclination: 97.8000 deg. Period: 97.30 min. Summary: Radar imaging satellite..

2010 August 24 - . 07:10 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2D.
  • Tianhui-1 Weixing - . Nation: China. Agency: SISE. Class: Surveillance. Type: Surveillance satellite. USAF Sat Cat: 36985 . COSPAR: 2010-040A. Apogee: 507 km (315 mi). Perigee: 484 km (300 mi). Inclination: 97.4000 deg. Period: 94.50 min. Summary: Research, mapping and land resource survey satellite..

2010 September 4 - . 16:14 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3B.
  • Chinasat 6A - . Payload: Zhongxing 6A. Mass: 5,100 kg (11,200 lb). Nation: China. Agency: SISE. Program: Chinasat. Class: Communications. Type: Communications satellite. Spacecraft: DFH-4. USAF Sat Cat: 37150 . COSPAR: 2010-042A. Apogee: 35,795 km (22,241 mi). Perigee: 35,778 km (22,231 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Summary: C and Ku band communications transponders..

2010 September 22 - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2D.
  • Yaogan 11 - . Payload: Zheda Pixing 1A. Nation: China. Agency: SISE. Class: Surveillance. Type: Surveillance satellite. Spacecraft: Yaogan. USAF Sat Cat: 37165 . COSPAR: 2010-047A. Apogee: 669 km (415 mi). Perigee: 626 km (388 mi). Inclination: 98.0000 deg. Period: 97.70 min. Summary: Carried earth imaging camera..
  • Zheda Pixing 1B - . Nation: China. Agency: SISE. Spacecraft: Zheda Pixing. USAF Sat Cat: 37166 . COSPAR: 2010-047B. Apogee: 657 km (408 mi). Perigee: 622 km (386 mi). Inclination: 98.0000 deg. Period: 97.50 min.
  • Zheda Pixing 1C - . Nation: China. Agency: SISE. Spacecraft: Zheda Pixing. USAF Sat Cat: 37167 . COSPAR: 2010-047C. Apogee: 657 km (408 mi). Perigee: 623 km (387 mi). Inclination: 98.0000 deg. Period: 97.50 min.

2010 October 1 - . 11:00 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3C.
  • Chang'e 2 - . Payload: Chang'e 2. Nation: China. Agency: SISE. Class: Moon. Type: Lunar probe. Spacecraft: Chang'e. USAF Sat Cat: 37174 . COSPAR: 2010-050A. China's second lunar orbiter. Entered a 119 x 8599 km lunar orbit on 1 October at 03:14 GMT. By 9 October it had maneuvered to its operational 100-km circular lunar orbit. On 9 June 2011, its lunar mission complete, it was maneuvered out of lunar orbit, and arrived at the Sun-Earth L2 Lagrangian point on 25 August 2011.

2010 October 6 - . 00:49 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: CZ-4B.
  • SJ-6G - . Payload: SJ-6/4A. Mass: 1,000 kg (2,200 lb). Nation: China. Agency: SISE. Class: Surveillance. Type: Surveillance satellite. Spacecraft: SJ-6. USAF Sat Cat: 37179 . COSPAR: 2010-051A. Apogee: 606 km (376 mi). Perigee: 587 km (364 mi). Inclination: 97.7000 deg. Period: 96.60 min. Summary: Fourth pair of SJ-6 military surveillance satellites..
  • SJ-6H - . Payload: SJ-6/4B. Mass: 200 kg (440 lb). Nation: China. Agency: SISE. Class: Surveillance. Type: Surveillance satellite. Spacecraft: SJ-6. USAF Sat Cat: 37180 . COSPAR: 2010-051B. Apogee: 604 km (375 mi). Perigee: 588 km (365 mi). Inclination: 97.7000 deg. Period: 96.60 min.

2010 October 31 - . 16:26 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3C.
  • Beidou G4 - . Payload: Beidou DW6. Nation: China. Class: Navigation. Type: Navigation satellite. Spacecraft: Beidou. USAF Sat Cat: 37210 . COSPAR: 2010-057A. Apogee: 35,793 km (22,240 mi). Perigee: 35,781 km (22,233 mi). Inclination: 1.6000 deg. Period: 1,436.10 min. Summary: Navigation satellite..

2010 November 5 - . 18:37 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: CZ-4C.
  • FY-3B - . Payload: Fengyun 3 (01 B. Nation: China. Class: Earth. Type: Weather satellite. Spacecraft: FY-3. USAF Sat Cat: 37214 . COSPAR: 2010-059A. Apogee: 828 km (514 mi). Perigee: 825 km (512 mi). Inclination: 98.7000 deg. Period: 101.40 min. Summary: Second polar orbiting FY-3 weather satellite..

2010 November 24 - . 16:09 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3A.
  • Chinasat 20A - . Payload: Zhongxing 20A. Nation: China. Program: Chinasat. Class: Communications. Type: Communications satellite. Spacecraft: DFH-3. USAF Sat Cat: 37234 . COSPAR: 2010-064A. Apogee: 35,795 km (22,241 mi). Perigee: 35,778 km (22,231 mi). Inclination: 0.4000 deg. Period: 1,436.10 min.

2010 December 17 - . 20:20 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3A.
  • Beidou IGS 2 - . Payload: Beidou DW7. Nation: China. Class: Navigation. Type: Navigation satellite. Spacecraft: Beidou. USAF Sat Cat: 37256 . COSPAR: 2010-068A. Apogee: 35,857 km (22,280 mi). Perigee: 35,722 km (22,196 mi). Inclination: 55.2000 deg. Period: 1,436.20 min. Summary: Second Beidou launched to inclined synchronous orbit..

2011 April 9 - . 20:47 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3A.
  • Beidou IGS 3 - . Payload: Beidou DW8. Nation: China. Class: Navigation. Type: Navigation satellite. Spacecraft: Beidou. USAF Sat Cat: 37384 . COSPAR: 2011-013A. Apogee: 35,874 km (22,291 mi). Perigee: 35,696 km (22,180 mi). Inclination: 55.3000 deg. Period: 1,436.00 min. Summary: Beidou-2 second generation navigation satellite..

2011 June 20 - . 16:13 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3B. LV Configuration: CZ-3B(E).
  • Zhongxing-10 - . Payload: Chinasat 10. Mass: 5,000 kg (11,000 lb). Nation: China. Program: Chinasat. Class: Communications. Type: Communications satellite. Spacecraft: DFH-4. USAF Sat Cat: 37677 . COSPAR: 2011-026A. Apogee: 35,812 km (22,252 mi). Perigee: 35,764 km (22,222 mi). Inclination: 0.0000 deg. Period: 1,436.20 min. Summary: Chinese communications satellite, stationed over 103.5 deg E. AKA ChinaSat 10, Xinnuo-5, and Sinosat-5..

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 11 - . 15:41 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3C.
  • Tianlian 1-02 - . Nation: China. Class: Communications. Type: Military communications satellite. USAF Sat Cat: 37737 . COSPAR: 2011-032A. Apogee: 35,804 km (22,247 mi). Perigee: 35,769 km (22,225 mi). Inclination: 0.8000 deg. Period: 1,436.10 min. Summary: Data relay satellite to support the Shenzhou-Tiangong docking mission and later manned space station missions..

2011 July 26 - . 21:44 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3A.
  • Beidou IGS 4 - . Nation: China. Class: Navigation. Type: Navigation satellite. Spacecraft: Beidou. USAF Sat Cat: 37763 . COSPAR: 2011-038A. Apogee: 35,864 km (22,284 mi). Perigee: 35,698 km (22,181 mi). Inclination: 55.2000 deg. Period: 1,435.80 min.

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 11 - . 16:15 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3B.
  • Paksat 1R - . Mass: 5,120 kg (11,280 lb). Nation: Pakistan. Class: Communications. Type: Communications satellite. Spacecraft: DFH-4. USAF Sat Cat: 37779 . COSPAR: 2011-042A. Apogee: 35,793 km (22,240 mi). Perigee: 35,779 km (22,231 mi). Inclination: 0.0000 deg. Period: 1,436.00 min. Summary: Communications satellite to replace Paksat 1, the former Palapa C1..

2011 August 15 - . 22:57 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC2. LV Family: CZ. Launch Vehicle: CZ-4B.
  • Haiyang 2A - . Nation: China. Class: Earth. Type: Earth resources satellite. Spacecraft: HY-1. USAF Sat Cat: 37781 . COSPAR: 2011-043A. Apogee: 967 km (600 mi). Perigee: 966 km (600 mi). Inclination: 99.4000 deg. Period: 104.40 min. Summary: Oceanographic satellite with a microwave radiometer, a radar altimeter and a radar scatterometer to monitor ocean conditions..

2011 August 17 - . 07:12 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC2. LV Family: CZ. Launch Vehicle: CZ-4B.
  • EDUSAT - . Mass: 10 kg (22 lb). Nation: Italy. Class: Technology. Type: Technology satellite. USAF Sat Cat: 37788 . COSPAR: 2011-044A. Apogee: 698 km (433 mi). Perigee: 639 km (397 mi). Inclination: 98.2000 deg. Period: 98.10 min. Summary: Technology satellite built by the Universita di Roma la Sapienza..
  • Nigeriasat 2 - . Mass: 268 kg (590 lb). Nation: Nigeria. Class: Surveillance. Type: Surveillance satellite. Spacecraft: SSTL-300. USAF Sat Cat: 37789 . COSPAR: 2011-044B. Apogee: 718 km (446 mi). Perigee: 693 km (430 mi). Inclination: 98.2000 deg. Period: 98.90 min. Summary: Observation satellite with a 2.5-m resolution imager for Nigeria's National Space Research Development Agency..
  • Nigeriasat X - . Mass: 86 kg (189 lb). Nation: Nigeria. Class: Technology. Type: Technology satellite. Spacecraft: SSTL-100. USAF Sat Cat: 37790 . COSPAR: 2011-044C. Apogee: 699 km (434 mi). Perigee: 656 km (407 mi). Inclination: 98.2000 deg. Period: 98.30 min. Summary: Technology demonstration satellite built by Surrey Satellite with participation by Nigerian engineers..

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..

2011 September 17 - . 16:33 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3B.
  • Chinasat 1A - . Nation: China. Program: Chinasat. Class: Communications. Type: Communications satellite. Spacecraft: DFH-4. USAF Sat Cat: 37804 . COSPAR: 2011-047A. Apogee: 35,794 km (22,241 mi). Perigee: 35,781 km (22,233 mi). Inclination: 0.5000 deg. Period: 1,436.10 min. Summary: Military communications satellite..

2011 September 29 - . 13:16 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2F. LV Configuration: CZ-2FT1.
  • Tiangong 1 - . Nation: China. Class: Manned. Type: Manned space station. Spacecraft: Tiangong. USAF Sat Cat: 37820 . COSPAR: 2011-053A. Apogee: 339 km (210 mi). Perigee: 330 km (200 mi). Inclination: 42.8000 deg. Period: 91.20 min. Summary: First Chinese manned space laboratory. Placed initially into a 198 km x 332 km x 42.8 deg orbit. Maneuvered to a 336 km x 353 km operational orbit by 30 September in preparation for arrival of the Shenzhou 8 spacecraft that would dock with it..

2011 October 7 - . 08:21 GMT - . Launch Site: Xichang. LV Family: CZ. Launch Vehicle: CZ-3B. LV Configuration: CZ-3B(E).
  • Eutelsat W3C - . Payload: Spacebus 4000C3. Mass: 5,400 kg (11,900 lb). Nation: Europe. Program: Eutelsat. Class: Communications. Type: Communications satellite. Spacecraft: Spacebus 4000. USAF Sat Cat: 37836 . COSPAR: 2011-057A. Apogee: 35,791 km (22,239 mi). Perigee: 35,781 km (22,233 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Summary: Communications satellite..

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