CZ Credit - (c) Mark Wade

Orbital launch vehicle. Country: China. Status: Active.

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.

Manufacturer: CALT. Launches: 122. Failures: 10. Success Rate: 91.80%. First Launch Date: 1971-09-10. Last Launch Date: 2007-11-11. Launch data is: continuing. Version:

DF-5.

DF-5

Intercontinental ballistic missile. IOC: 1981. Status: Active. Department of Defence Designation: CSS-4.

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.

The missile was designed from the beginning to include China's first full inertial navigation guidance package. On January 4, 1966, Tsien proposed development of a countermeasures package for the DF-5 to evade American anti-ballistic missile systems. This was to included electronic jammers and spoofers and balloon decoys. American investigators would claim, beginning in the 1990's, that the CZ-5 incorporated Titan 2 missile technology. Flight tests began in 1971 but the missile did not enter service until 1981, following a series of two recoverable-warhead tests.

Launches: 9. First Launch Date: 1971-09-10. Last Launch Date: 1981-12-07. Apogee: 1,000 km (600 mi). Liftoff Thrust: 2,500.000 kN (562,000 lbf). Total Mass: 181,000 kg (399,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 32.61 m (106.98 ft). Span: 3.35 m (10.99 ft). Standard warhead mass: 3,000 kg (6,600 lb). Maximum range: 12,020 km (7,460 mi). Number Standard Warheads: 1. Standard warhead yield: 3,300 KT. Standard warhead CEP: 0.44 km (0.27 mi). Boost Propulsion: Storable liquid rocket, N2O4/UDMH. Guidance: Inertial. Total Number Built: 4.

• Stage1: 1 x FB-1-1. Gross Mass: 150,400 kg (331,500 lb). Empty Mass: 10,000 kg (22,000 lb). Motor: 4 x YF-20A. Thrust (vac): 3,000.000 kN (674,400 lbf). Isp: 289 sec. Burn time: 128 sec. Length: 20.10 m (65.90 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x FB-1-2. Gross Mass: 38,300 kg (84,400 lb). Empty Mass: 3,500 kg (7,700 lb). Motor: 1 x YF-22/23. Thrust (vac): 761.900 kN (171,282 lbf). Isp: 295 sec. Burn time: 127 sec. Length: 7.40 m (24.20 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

Apogee: 1,000 km (600 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 181,000 kg (399,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 32.61 m (106.98 ft). Span: 3.35 m (10.99 ft). Standard warhead mass: 3,190 kg (7,030 lb). Maximum range: 13,030 km (8,090 mi). Number Standard Warheads: 1. Standard warhead yield: 3,300 KT. Standard warhead CEP: 0.44 km (0.27 mi). Boost Propulsion: Storable liquid rocket, N2O4/UDMH. Guidance: Inertial. Total Number Built: 4. Version:

FB-1.

FB-1 Launch

Status: Retired 1981. Other Designations: Storm 1. Manufacturer's Designation: Feng-Bao-1.

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.

The 'Gang of Four' was formed by Mao Zedong's wife Jiang Qing, a Shanghai Propaganda Department official, a literary critic, and a Shanghai security guard. They rose to power during turbulent period of the Cultural Revolution (1966-1976) and dominated Chinese politics during that time. Development of the FB-1 (Feng Bao-1 = Storm-1), the first Chinese heavy-lift launch vehicle, began under their auspices in the autumn of 1969. A development team was formed with the Shanghai No. 2 Bureau of Mechanic-Electrical Industry as the leader. General system design was started in December the same year.

After Mao's death in September 1976, the Gang of Four was arrested and orbital flights of the FB-1 and JSSW came to a halt. In 1980 the Gang of Four were tried in court and given lengthy prison sentences. The final FB-1 made its last flight a year later with a payload of assorted scientific satellites. The FB-1 had slightly lower performance than the CZ-2 and no useful results from the series of JSSW satellites launched have been reported. However the Shanghai facility remained in use, being assigned development of the CZ-4 variants of the triumphant CZ-2 design.

Launches: 11. Failures: 4. First Launch Date: 1972-08-10. Last Launch Date: 1981-09-19. LEO Payload: 2,500 kg (5,500 lb). to: 200 km Orbit. Apogee: 1,000 km (600 mi). Associated Spacecraft: JSSW, SJ. Liftoff Thrust: 2,679.000 kN (602,263 lbf). Total Mass: 191,700 kg (422,600 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 33.00 m (108.00 ft). Flyaway Unit Cost $: 6.000 million. in: 1985 unit dollars.

• Stage1: 1 x FB-1-1. Gross Mass: 150,400 kg (331,500 lb). Empty Mass: 10,000 kg (22,000 lb). Motor: 4 x YF-20A. Thrust (vac): 3,000.000 kN (674,400 lbf). Isp: 289 sec. Burn time: 128 sec. Length: 20.10 m (65.90 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x FB-1-2. Gross Mass: 38,300 kg (84,400 lb). Empty Mass: 3,500 kg (7,700 lb). Motor: 1 x YF-22/23. Thrust (vac): 761.900 kN (171,282 lbf). Isp: 295 sec. Burn time: 127 sec. Length: 7.40 m (24.20 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

Launches: 1. Failures: 1. First Launch Date: 1974-11-05. Last Launch Date: 1974-11-05. LEO Payload: 2,000 kg (4,400 lb). to: 200 km Orbit. at: 52.00 degrees. Apogee: 500 km (310 mi). Associated Spacecraft: FSW, Shuguang 1. Liftoff Thrust: 2,690.000 kN (604,730 lbf). Total Mass: 190,000 kg (410,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 32.00 m (104.00 ft). Launch Price $: 20.000 million. in: 1994 price dollars.

• Stage1: 1 x FB-1-1. Gross Mass: 150,400 kg (331,500 lb). Empty Mass: 10,000 kg (22,000 lb). Motor: 4 x YF-20A. Thrust (vac): 3,000.000 kN (674,400 lbf). Isp: 289 sec. Burn time: 128 sec. Length: 20.10 m (65.90 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x FB-1-2. Gross Mass: 38,300 kg (84,400 lb). Empty Mass: 3,500 kg (7,700 lb). Motor: 1 x YF-22/23. Thrust (vac): 761.900 kN (171,282 lbf). Isp: 295 sec. Burn time: 127 sec. Length: 7.40 m (24.20 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

Launches: 22. First Launch Date: 1975-11-26. Last Launch Date: 2007-04-11. LEO Payload: 2,500 kg (5,500 lb). to: 200 km Orbit. at: 52.00 degrees. Payload: 2,200 kg (4,800 lb). to a: 200 km, 90 deg inclination orbital trajectory. Apogee: 500 km (310 mi). Associated Spacecraft: Double Star, Freja, FSW, KOMPSAT-2. Liftoff Thrust: 2,960.000 kN (665,430 lbf). Total Mass: 192,000 kg (423,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 35.15 m (115.32 ft). Launch Price $: 25.000 million. in: 1999 price dollars.

• Stage1: 1 x CZ-2C-1. Gross Mass: 153,000 kg (337,000 lb). Empty Mass: 10,000 kg (22,000 lb). Motor: 4 x YF-20A. Thrust (vac): 3,295.000 kN (740,745 lbf). Isp: 291 sec. Burn time: 122 sec. Length: 20.52 m (67.32 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x CZ-2C-2. Gross Mass: 39,000 kg (85,000 lb). Empty Mass: 4,000 kg (8,800 lb). Motor: 1 x YF-22A/23A. Thrust (vac): 761.900 kN (171,282 lbf). Isp: 295 sec. Burn time: 130 sec. Length: 7.50 m (24.60 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

Launches: 7. First Launch Date: 1997-09-01. Last Launch Date: 1999-06-11. LEO Payload: 2,800 kg (6,100 lb). Payload: 1,400 kg (3,000 lb). to a: 780 km, 86 deg inclination orbital trajectory. Apogee: 1,000 km (600 mi). Associated Spacecraft: LM 700. Liftoff Thrust: 2,960.000 kN (665,430 lbf). Total Mass: 213,000 kg (469,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 40.40 m (132.50 ft). Launch Price $: 25.000 million. in: 1999 price dollars.

• Stage1: 1 x CZ-2C-1. Gross Mass: 153,000 kg (337,000 lb). Empty Mass: 10,000 kg (22,000 lb). Motor: 4 x YF-20A. Thrust (vac): 3,295.000 kN (740,745 lbf). Isp: 291 sec. Burn time: 122 sec. Length: 20.52 m (67.32 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x CZ-2C/SD-2. Gross Mass: 55,000 kg (121,000 lb). Empty Mass: 5,000 kg (11,000 lb). Motor: 1 x YF-22A/23A. Thrust (vac): 761.900 kN (171,282 lbf). Isp: 298 sec. Burn time: 190 sec. Length: 10.00 m (32.00 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

Launches: 8. First Launch Date: 1992-08-09. Last Launch Date: 2007-05-25. LEO Payload: 3,500 kg (7,700 lb). to: 200 km Orbit. at: 28.00 degrees. Apogee: 500 km (310 mi). Associated Spacecraft: FSW. Liftoff Thrust: 2,926.200 kN (657,836 lbf). Total Mass: 232,250 kg (512,020 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 35.07 m (115.05 ft). Launch Price $: 15.000 million. in: 1999 price dollars.

• Stage1: 1 x CZ-4A-1. Gross Mass: 192,700 kg (424,800 lb). Empty Mass: 9,500 kg (20,900 lb). Motor: 4 x YF-20B. Thrust (vac): 3,265.143 kN (734,033 lbf). Isp: 289 sec. Burn time: 170 sec. Length: 24.66 m (80.90 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x CZ-4A-2. Gross Mass: 39,550 kg (87,190 lb). Empty Mass: 4,000 kg (8,800 lb). Motor: 1 x YF-25/23. Thrust (vac): 831.005 kN (186,817 lbf). Isp: 295 sec. Burn time: 135 sec. Length: 10.41 m (34.15 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

 Event                                   TIME (sec.)
 Liftoff                                  0.0
 Pitch over                              11.0
 Booster engine shutoff                 125.8
 Booster separation                     127.3
 First Stage Engine Shutoff             158.9
 First/Second Stage Separation          160.4
 Jettisoning of Fairing                 200.4
 Second Stage Main Engine Shutoff       459.9
 Vernier Engine Shutoff (LEO injection) 572.9
 Start of re-orientation                582.9
 End of re-orientation                  582.9+Tr
 Ignition of spin-up rockets            582.9+Tr+10.0
 End of spin-up                         582.9+Tr+10.5 
 Payload separation                     582.9+Tr+10.7
 Ignition of tumbling rocket            582.9+Tr+14

Launches: 7. Failures: 2. First Launch Date: 1990-07-16. Last Launch Date: 1995-12-28. LEO Payload: 9,200 kg (20,200 lb). to: 200 km Orbit. at: 28.00 degrees. Payload: 3,370 kg (7,420 lb). to a: Geosynchronous transfer with solid kick stage. trajectory. Apogee: 500 km (310 mi). Associated Spacecraft: AS 7000, Badr, HS 601. Liftoff Thrust: 5,920.000 kN (1,330,860 lbf). Total Mass: 460,000 kg (1,010,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 49.70 m (163.00 ft). Launch Price $: 50.000 million. in: 1999 price dollars.

• Stage0: 4 x LB-40. Gross Mass: 41,000 kg (90,000 lb). Empty Mass: 3,200 kg (7,000 lb). Motor: 1 x YF-20B. Thrust (vac): 816.285 kN (183,508 lbf). Isp: 291 sec. Burn time: 128 sec. Length: 15.33 m (50.29 ft). Diameter: 2.25 m (7.38 ft). Propellants: N2O4/UDMH.

• Stage1: 1 x CZ-2E-1. Gross Mass: 196,500 kg (433,200 lb). Empty Mass: 9,500 kg (20,900 lb). Motor: 4 x YF-20B. Thrust (vac): 3,265.143 kN (734,033 lbf). Isp: 289 sec. Burn time: 166 sec. Length: 23.70 m (77.70 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x CZ-2E-2. Gross Mass: 91,500 kg (201,700 lb). Empty Mass: 5,500 kg (12,100 lb). Motor: 1 x YF-25/23. Thrust (vac): 831.005 kN (186,817 lbf). Isp: 298 sec. Burn time: 295 sec. Length: 15.52 m (50.91 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage3: 1 x EPKM. Gross Mass: 5,985 kg (13,194 lb). Empty Mass: 541 kg (1,192 lb). Motor: 1 x EPKM. Thrust (vac): 117.000 kN (26,302 lbf). Isp: 298 sec. Burn time: 135 sec. Length: 3.10 m (10.10 ft). Diameter: 1.70 m (5.50 ft). Propellants: Solid.

LEO Payload: 14,100 kg (31,000 lb). to: 200 km Orbit. at: 48.00 degrees. Associated Spacecraft: Chinese Space Laboratory. Liftoff Thrust: 8,910.000 kN (2,003,040 lbf). Total Mass: 695,000 kg (1,532,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 53.60 m (175.80 ft). Launch Price $: 55.000 million. in: 1999 price dollars.

• Stage0: 4 x CZ-2E(A)-0. Gross Mass: 80,000 kg (176,000 lb). Empty Mass: 8,000 kg (17,600 lb). Motor: 2 x YF-20B. Thrust (vac): 1,632.800 kN (367,068 lbf). Isp: 291 sec. Burn time: 125 sec. Length: 27.00 m (88.00 ft). Diameter: 2.25 m (7.38 ft). Propellants: N2O4/UDMH.

• Stage1: 1 x CZ-2E-1. Gross Mass: 196,500 kg (433,200 lb). Empty Mass: 9,500 kg (20,900 lb). Motor: 4 x YF-20B. Thrust (vac): 3,265.143 kN (734,033 lbf). Isp: 289 sec. Burn time: 166 sec. Length: 23.70 m (77.70 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x CZ-2E-2. Gross Mass: 91,500 kg (201,700 lb). Empty Mass: 5,500 kg (12,100 lb). Motor: 1 x YF-25/23. Thrust (vac): 831.005 kN (186,817 lbf). Isp: 298 sec. Burn time: 295 sec. Length: 15.52 m (50.91 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

LEO Payload: 7,800 kg (17,100 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 6,000.000 kN (1,348,800 lbf). Total Mass: 500,000 kg (1,100,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 33.00 m (108.00 ft). Version:

CZ-2F.

CZ-2F on pad

Status: Active. Other Designations: Long March 2F. Manufacturer's Designation: Chang Zheng-2F. Popular Name: Shenjian. Alternate Designation: Divine Arrow.

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.

Launches: 6. First Launch Date: 1999-11-19. Last Launch Date: 2005-10-12. LEO Payload: 8,400 kg (18,500 lb). to: 185 km Orbit. at: 57.00 degrees. Payload: 3,500 kg (7,700 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 500 km (310 mi). Associated Spacecraft: Shenzhou. Liftoff Thrust: 5,920.000 kN (1,330,860 lbf). Total Mass: 464,000 kg (1,022,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 62.00 m (203.00 ft).

• Stage0: 4 x LB-40. Gross Mass: 41,000 kg (90,000 lb). Empty Mass: 3,200 kg (7,000 lb). Motor: 1 x YF-20B. Thrust (vac): 816.285 kN (183,508 lbf). Isp: 291 sec. Burn time: 128 sec. Length: 15.33 m (50.29 ft). Diameter: 2.25 m (7.38 ft). Propellants: N2O4/UDMH.

• Stage1: 1 x CZ-2E-1. Gross Mass: 196,500 kg (433,200 lb). Empty Mass: 9,500 kg (20,900 lb). Motor: 4 x YF-20B. Thrust (vac): 3,265.143 kN (734,033 lbf). Isp: 289 sec. Burn time: 166 sec. Length: 23.70 m (77.70 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x CZ-2E-2. Gross Mass: 91,500 kg (201,700 lb). Empty Mass: 5,500 kg (12,100 lb). Motor: 1 x YF-25/23. Thrust (vac): 831.005 kN (186,817 lbf). Isp: 298 sec. Burn time: 295 sec. Length: 15.52 m (50.91 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

Launches: 13. Failures: 2. First Launch Date: 1984-01-29. Last Launch Date: 2000-06-25. LEO Payload: 4,800 kg (10,500 lb). to: 200 km Orbit. at: 28.50 degrees. Payload: 1,400 kg (3,000 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: DFH-2, FY-2, HS 376. Liftoff Thrust: 2,960.000 kN (665,430 lbf). Total Mass: 204,000 kg (449,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 43.25 m (141.89 ft). Launch Price $: 40.000 million. in: 1999 price dollars.

• Stage1: 1 x CZ-3-1. Gross Mass: 151,000 kg (332,000 lb). Empty Mass: 9,000 kg (19,800 lb). Motor: 4 x YF-20A. Thrust (vac): 3,000.000 kN (674,400 lbf). Isp: 289 sec. Burn time: 132 sec. Length: 20.22 m (66.33 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x CZ-3-2. Gross Mass: 39,000 kg (85,000 lb). Empty Mass: 4,000 kg (8,800 lb). Motor: 1 x YF-22A/23A. Thrust (vac): 761.900 kN (171,282 lbf). Isp: 295 sec. Burn time: 130 sec. Length: 9.71 m (31.85 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage3: 1 x CZ-YF-73. Gross Mass: 10,500 kg (23,100 lb). Empty Mass: 2,000 kg (4,400 lb). Motor: 4 x YF-73. Thrust (vac): 44.100 kN (9,914 lbf). Isp: 425 sec. Burn time: 800 sec. Length: 7.48 m (24.54 ft). Diameter: 2.25 m (7.38 ft). Propellants: Lox/LH2.

Launches: 15. First Launch Date: 1994-02-08. Last Launch Date: 2007-10-24. LEO Payload: 7,200 kg (15,800 lb). to: 200 km Orbit. at: 28.50 degrees. Payload: 2,600 kg (5,700 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: Beidou, DFH-3, FH-1, SJ. Liftoff Thrust: 2,960.000 kN (665,430 lbf). Total Mass: 241,000 kg (531,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 52.50 m (172.20 ft). Launch Price $: 55.000 million. in: 1999 price dollars.

• Stage1: 1 x CZ-3A-1. Gross Mass: 179,000 kg (394,000 lb). Empty Mass: 9,000 kg (19,800 lb). Motor: 4 x YF-20B. Thrust (vac): 3,265.143 kN (734,033 lbf). Isp: 289 sec. Burn time: 155 sec. Length: 23.08 m (75.72 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x CZ-3A-2. Gross Mass: 33,600 kg (74,000 lb). Empty Mass: 4,000 kg (8,800 lb). Motor: 1 x YF-25/23. Thrust (vac): 831.005 kN (186,817 lbf). Isp: 297 sec. Burn time: 110 sec. Length: 11.53 m (37.82 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage3: 1 x CZ H-18. Gross Mass: 21,000 kg (46,000 lb). Empty Mass: 2,800 kg (6,100 lb). Motor: 2 x YF-75. Thrust (vac): 156.000 kN (35,070 lbf). Isp: 440 sec. Burn time: 470 sec. Length: 12.38 m (40.60 ft). Diameter: 3.00 m (9.80 ft). Propellants: Lox/LH2.

Launches: 9. Failures: 1. First Launch Date: 1996-02-14. Last Launch Date: 2007-07-05. LEO Payload: 11,200 kg (24,600 lb). to: 200 km Orbit. at: 28.50 degrees. Payload: 5,100 kg (11,200 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: AS 2100, FS-1300, Spacebus 3000 . Liftoff Thrust: 2,980.000 kN (669,930 lbf). Total Mass: 425,800 kg (938,700 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 54.80 m (179.70 ft). Launch Price $: 70.000 million. in: 1999 price dollars.

• Stage0: 4 x LB-40. Gross Mass: 41,000 kg (90,000 lb). Empty Mass: 3,200 kg (7,000 lb). Motor: 1 x YF-20B. Thrust (vac): 816.285 kN (183,508 lbf). Isp: 291 sec. Burn time: 128 sec. Length: 15.33 m (50.29 ft). Diameter: 2.25 m (7.38 ft). Propellants: N2O4/UDMH.

• Stage1: 1 x CZ-3A-1. Gross Mass: 179,000 kg (394,000 lb). Empty Mass: 9,000 kg (19,800 lb). Motor: 4 x YF-20B. Thrust (vac): 3,265.143 kN (734,033 lbf). Isp: 289 sec. Burn time: 155 sec. Length: 23.08 m (75.72 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x CZ-2C/SD-2. Gross Mass: 55,000 kg (121,000 lb). Empty Mass: 5,000 kg (11,000 lb). Motor: 1 x YF-22A/23A. Thrust (vac): 761.900 kN (171,282 lbf). Isp: 298 sec. Burn time: 190 sec. Length: 10.00 m (32.00 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage3: 1 x CZ H-18. Gross Mass: 21,000 kg (46,000 lb). Empty Mass: 2,800 kg (6,100 lb). Motor: 2 x YF-75. Thrust (vac): 156.000 kN (35,070 lbf). Isp: 440 sec. Burn time: 470 sec. Length: 12.38 m (40.60 ft). Diameter: 3.00 m (9.80 ft). Propellants: Lox/LH2.

LEO Payload: 13,000 kg (28,000 lb). to: 200 km Orbit. at: 28.50 degrees. Payload: 6,000 kg (13,200 lb). to a: Geosynchronous transfer trajectory. Liftoff Thrust: 8,910.000 kN (2,003,040 lbf). Total Mass: 580,000 kg (1,270,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 62.00 m (203.00 ft). Version:

CZ-3C.

LM-3C Launch Vehicle

Status: Development ended 1997. Other Designations: Long March 3C. Manufacturer's Designation: Chang Zheng-3C.

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.

Launch sequence:

Event                                     TIME (sec.)
 First Stage Ignition                          -3
 Liftoff                                        0.00
 Pitch over                                    11.0
 Booster Separation                           127.24
 First/Second Stage Separation                147.36
 Jettisoning of Fairing                       232.4
 2nd/3rd Stage Sep. & 3rd Stage Ignition      332.31
 1st Shutoff of 3rd Stage                     631.32
 2nd Ignition of 3rd Stage                   1281.23
 2nd Shutoff of Third Stage                  1459.91
 Satellite/Launcher Sep.                     1559.907

Payload: 3,800 kg (8,300 lb). to a: Geosynchronous transfer (200 x 35,793 km @ 28 deg) trajectory. Liftoff Thrust: 4,440.000 kN (998,150 lbf). Total Mass: 345,000 kg (760,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 54.80 m (179.70 ft). Launch Price $: 75.000 million. in: 1999 price dollars.

• Stage0: 2 x LB-40. Gross Mass: 41,000 kg (90,000 lb). Empty Mass: 3,200 kg (7,000 lb). Motor: 1 x YF-20B. Thrust (vac): 816.285 kN (183,508 lbf). Isp: 291 sec. Burn time: 128 sec. Length: 15.33 m (50.29 ft). Diameter: 2.25 m (7.38 ft). Propellants: N2O4/UDMH.

• Stage1: 1 x CZ-3A-1. Gross Mass: 179,000 kg (394,000 lb). Empty Mass: 9,000 kg (19,800 lb). Motor: 4 x YF-20B. Thrust (vac): 3,265.143 kN (734,033 lbf). Isp: 289 sec. Burn time: 155 sec. Length: 23.08 m (75.72 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x CZ-2C/SD-2. Gross Mass: 55,000 kg (121,000 lb). Empty Mass: 5,000 kg (11,000 lb). Motor: 1 x YF-22A/23A. Thrust (vac): 761.900 kN (171,282 lbf). Isp: 298 sec. Burn time: 190 sec. Length: 10.00 m (32.00 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage3: 1 x CZ H-18. Gross Mass: 21,000 kg (46,000 lb). Empty Mass: 2,800 kg (6,100 lb). Motor: 2 x YF-75. Thrust (vac): 156.000 kN (35,070 lbf). Isp: 440 sec. Burn time: 470 sec. Length: 12.38 m (40.60 ft). Diameter: 3.00 m (9.80 ft). Propellants: Lox/LH2.

Launches: 2. First Launch Date: 1988-09-06. Last Launch Date: 1990-09-03. LEO Payload: 4,680 kg (10,310 lb). to: 200 km Orbit. Payload: 1,100 kg (2,400 lb). to a: Geosynchronous transfer trajectory. Apogee: 1,000 km (600 mi). Associated Spacecraft: FY-1, SJ. Liftoff Thrust: 2,960.000 kN (665,430 lbf). Total Mass: 249,000 kg (548,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 41.90 m (137.40 ft). Launch Price $: 30.000 million. in: 1994 price dollars. Flyaway Unit Cost $: 9.500 million. in: 1985 unit dollars.

• Stage1: 1 x CZ-4A-1. Gross Mass: 192,700 kg (424,800 lb). Empty Mass: 9,500 kg (20,900 lb). Motor: 4 x YF-20B. Thrust (vac): 3,265.143 kN (734,033 lbf). Isp: 289 sec. Burn time: 170 sec. Length: 24.66 m (80.90 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x CZ-4A-2. Gross Mass: 39,550 kg (87,190 lb). Empty Mass: 4,000 kg (8,800 lb). Motor: 1 x YF-25/23. Thrust (vac): 831.005 kN (186,817 lbf). Isp: 295 sec. Burn time: 135 sec. Length: 10.41 m (34.15 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage3: 1 x CZ-4A-3. Gross Mass: 15,150 kg (33,400 lb). Empty Mass: 1,000 kg (2,200 lb). Motor: 2 x YF-40. Thrust (vac): 100.810 kN (22,663 lbf). Isp: 303 sec. Burn time: 400 sec. Length: 1.92 m (6.29 ft). Diameter: 2.90 m (9.50 ft). Propellants: N2O4/UDMH.

Launches: 11. First Launch Date: 1999-05-10. Last Launch Date: 2007-09-19. LEO Payload: 2,800 kg (6,100 lb). Payload: 2,800 kg (6,100 lb). to a: Sun synchronous, 900 km orbital trajectory. Apogee: 1,000 km (600 mi). Associated Spacecraft: FY-1, HY-1, SACI, SJ, ZY. Liftoff Thrust: 2,960.000 kN (665,430 lbf). Total Mass: 249,200 kg (549,300 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 45.80 m (150.20 ft). Launch Price $: 35.000 million. in: 1999 price dollars.

• Stage1: 1 x CZ-4A-1. Gross Mass: 192,700 kg (424,800 lb). Empty Mass: 9,500 kg (20,900 lb). Motor: 4 x YF-20B. Thrust (vac): 3,265.143 kN (734,033 lbf). Isp: 289 sec. Burn time: 170 sec. Length: 24.66 m (80.90 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage2: 1 x CZ-4B-2. Gross Mass: 39,600 kg (87,300 lb). Empty Mass: 4,000 kg (8,800 lb). Motor: 1 x YF-22B. Thrust (vac): 742.000 kN (166,808 lbf). Burn time: 127 sec. Length: 10.40 m (34.10 ft). Diameter: 3.35 m (10.99 ft). Propellants: N2O4/UDMH.

• Stage3: 1 x CZ-4B-3. Gross Mass: 15,200 kg (33,500 lb). Empty Mass: 1,000 kg (2,200 lb). Motor: 1 x YF-40. Thrust (vac): 98.100 kN (22,054 lbf). Burn time: 303 sec. Length: 1.90 m (6.20 ft). Diameter: 2.90 m (9.50 ft). Propellants: N2O4/UDMH.

Launches: 1. First Launch Date: 2007-11-11. Last Launch Date: 2007-11-11. LEO Payload: 2,800 kg (6,100 lb). Payload: 2,800 kg (6,100 lb). to a: Sun synchronous, 900 km orbital trajectory. Associated Spacecraft: Yaogan. Liftoff Thrust: 2,960.000 kN (665,430 lbf). Total Mass: 250,000 kg (550,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 45.80 m (150.20 ft). Launch Price $: 35.000 million. in: 1999 price dollars.

1964 September 12 - Chinese missiles redesignated and new development plan adopted. 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 - Jiuquan LA2B. Agency: PRC. Apogee: 1,000 km (600 mi). Research and Development Suborbital Flight

1972 August 10 - 00:32 GMT - Jiuquan LA2B. LV Model: FB-1 . Feng Bao 1 701-02 Shiyan Peizhong Agency: PRC. Apogee: 200 km (120 mi). Research and Development Suborbital Flight

1973 September 18 - Jiuquan LA2B. LV Model: FB-1 . Feng Bao 1 701-03 FAILURE: Failure. JSSW 1 Spacecraft: JSSW. Agency: PRC.

1974 July 14 - Jiuquan LA2B. LV Model: FB-1 . Feng Bao 1 701-04 FAILURE: Vehicle lost attitude stability and destroyed by range safety. JSSW 2 Spacecraft: JSSW. Agency: PRC.

1974 November 5 - Jiuquan LA2B. LV Model: CZ-2A . Chang Zheng 2A CZ2A-1 (3) FAILURE: Cable carrying pitch rate gyro signal disconnected. FSW-0 Spacecraft: FSW. Agency: PRC.

1975 July 26 - 13:28 GMT - Jiuquan LA2B. LV Model: FB-1 . Feng Bao 1 701-05 JSSW 3 Mass: 1,107 kg (2,440 lb). Spacecraft: JSSW. Agency: MAI. Perigee: 190 km (110 mi). Apogee: 455 km (282 mi). Inclination: 69.00 deg. Period: 90.90 min. Photo surveillance; radio transmission.

1975 November 26 - 03:29 GMT - Jiuquan LA2B. LV Model: CZ-2C . Chang Zheng 2C CZ2C-1 (4) FSW-0 No. 1 Mass: 2,500 kg (5,500 lb). Spacecraft: FSW. Agency: MAI. Perigee: 183 km (113 mi). Apogee: 483 km (300 mi). Inclination: 63.00 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: FSW-0 No. 1.

1975 December 16 - 09:19 GMT - Jiuquan LA2B. LV Model: FB-1 . Feng Bao 1 701-06 JSSW 4 Mass: 1,110 kg (2,440 lb). Spacecraft: JSSW. Agency: MAI. Perigee: 186 km (115 mi). Apogee: 387 km (240 mi). Inclination: 69.00 deg. Period: 90.30 min. Photo surveillance; radio transmission.

1976 August 30 - 11:53 GMT - Jiuquan LA2B. LV Model: FB-1 . Feng Bao 1 701-07 JSSW 5 Mass: 1,108 kg (2,442 lb). Spacecraft: JSSW. Agency: MAI. Perigee: 195 km (121 mi). Apogee: 2,145 km (1,332 mi). Inclination: 69.20 deg. Period: 108.80 min.

1976 November 10 - Jiuquan LA2B. LV Model: FB-1 . Feng Bao 1 701-08 FAILURE: Failure. JSSW 6 Spacecraft: JSSW. Agency: PRC.

1976 December 7 - 04:38 GMT - Jiuquan LA2B. LV Model: CZ-2C . Chang Zheng 2C CZ2C-2 (5) FSW-0 No. 2 Mass: 2,500 kg (5,500 lb). Spacecraft: FSW. Agency: MAI. Perigee: 172 km (106 mi). Apogee: 489 km (303 mi). Inclination: 59.40 deg. Period: 91.10 min. 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 - Jiuquan LA2B. LV Model: FB-1 . Feng Bao 1 701(II)-01 DDDS test Agency: PRC. Apogee: 200 km (120 mi).

1978 January 26 - 04:58 GMT - Jiuquan LA2B. LV Model: CZ-2C . Chang Zheng 2C CZ2C-3 (6) FSW-0 No. 3 Mass: 2,500 kg (5,500 lb). Spacecraft: FSW. Agency: MAI. Perigee: 186 km (115 mi). Apogee: 507 km (315 mi). Inclination: 57.00 deg. Period: 91.40 min. Photo surveillance; film capsule; capsule returned January 30. Second fully successful FSW mission.

1978 February - First public announcement of a Chinese manned program Spacecraft: Chinese Manned Capsule 1978. 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 - Jiuquan LA2B. LV Model: FB-1 . Feng Bao 1 701(II)-02 DDDS test Agency: PRC. Apogee: 200 km (120 mi).

1979 January 7 - Jiuquan LA2B. Agency: PRC. Apogee: 1,000 km (600 mi). Other sources say launch was from Taiyuan.

1979 July 15 - Jiuquan LA2B. Agency: PRC. Apogee: 1,000 km (600 mi). Other sources say launch was from Taiyuan.

1979 July 28 - Jiuquan LA2B. LV Model: FB-1 . Feng Bao 1 XCZ-1-02 FAILURE: Second stage failure. SJ-1 Mass: 221 kg (487 lb). Spacecraft: SJ. Agency: PRC. The SJ-1 was similar in appearance to the American Telstar and conducted communications technology tests.

1979 August 21 - Jiuquan LA2B. Agency: PRC. Apogee: 1,000 km (600 mi). Other sources say launch was from Taiyuan on 2 August.

1979 September 4 - Jiuquan LA2B. Agency: PRC. Apogee: 1,000 km (600 mi). Other sources say launch was from Taiyuan.

1979 November 26 - Jiuquan LA2B. Agency: PRC. Apogee: 1,000 km (600 mi). Other sources say launch was from Taiyuan on 15 October.

1980 January - Chinese astronauts in training 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 - Taiyuan -. Last DF-5 partial range test. Other sources do not list this test.

1980 May 18 - Jiuquan LA2B. Test mission Agency: PRC. Apogee: 1,000 km (600 mi).

1980 May 21 - 02:00 GMT - Jiuquan LA2B. Test mission Agency: PRC. Apogee: 1,000 km (600 mi).

1981 September 19 - 21:28 GMT - Jiuquan LA2B. LV Model: FB-1 . Feng Bao 1 XCZ-1-02 SJ-2A Mass: 257 kg (566 lb). Spacecraft: SJ. Agency: MAI. Perigee: 232 km (144 mi). Apogee: 1,598 km (992 mi). Inclination: 59.50 deg. Period: 103.30 min.

1981 December 7 - Jiuquan LA2B. Agency: PRC. Apogee: 1,000 km (600 mi). Other sources say launch was from Taiyuan.

1982 September 9 - 07:19 GMT - Jiuquan LA2B. LV Model: CZ-2C . Chang Zheng 2C CZ2C-4 (7) FSW-0 No. 4 Mass: 2,500 kg (5,500 lb). Spacecraft: FSW. Agency: MAI. Perigee: 172 km (106 mi). Apogee: 392 km (243 mi). Inclination: 63.00 deg. Period: 90.20 min. Photo surveillance; film capsule recovered 14 September.

1983 August 19 - 06:00 GMT - Jiuquan LA2B. LV Model: CZ-2C . Chang Zheng 2C CZ2C-5 (8) FSW-0 No. 5 Mass: 2,500 kg (5,500 lb). Spacecraft: FSW. Agency: MAI. Perigee: 170 km (100 mi). Apogee: 493 km (306 mi). Inclination: 63.30 deg. Period: 91.20 min. Photo surveillance; film capsule recovered 24 August.

1984 January 29 - 12:25 GMT - Xichang LC1. LV Model: CZ-3 . Chang Zheng 3 CZ3-1 (9) FAILURE: Third stage failed to ignite. STTW-T1 Mass: 900 kg (1,980 lb). Spacecraft: DFH-2. Agency: MAI. Perigee: 484 km (300 mi). Apogee: 6,446 km (4,005 mi). Inclination: 36.10 deg. Period: 162.00 min. 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 - Xichang LC1. LV Model: CZ-3 . Chang Zheng 3 CZ3-2 (10) STTW-T2 Mass: 900 kg (1,980 lb). Spacecraft: DFH-2. Agency: MAI. Perigee: 35,733 km (22,203 mi). Apogee: 35,796 km (22,242 mi). Inclination: 6.10 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 - Jiuquan LA2B. LV Model: CZ-2C . Chang Zheng 2C CZ2C-6 (11) FSW-0 No. 6 Mass: 2,500 kg (5,500 lb). Spacecraft: FSW. Agency: MAI. Perigee: 172 km (106 mi). Apogee: 398 km (247 mi). Inclination: 67.90 deg. Period: 90.20 min. Photo surveillance; film capsule recovered 17 September.

1985 October 21 - 05:04 GMT - Jiuquan LA2B. LV Model: CZ-2C . Chang Zheng 2C CZ2C-7 (12) FSW-0 No. 7 Mass: 2,500 kg (5,500 lb). Spacecraft: FSW. Agency: MAI. Perigee: 171 km (106 mi). Apogee: 393 km (244 mi). Inclination: 63.00 deg. Period: 90.20 min. Fanhui Shi Weixing photo surveillance satellite; film capsule recovered 26 October.

1986 February 1 - 12:37 GMT - Xichang LC1. LV Model: CZ-3 . Chang Zheng 3 CZ3-3 (13) STTW 1 Mass: 1,024 kg (2,257 lb). Spacecraft: DFH-2. Agency: MAI. Perigee: 35,774 km (22,228 mi). Apogee: 35,819 km (22,256 mi). Inclination: 9.80 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 - Jiuquan LA2B. LV Model: CZ-2C . Chang Zheng 2C CZ2C-8 (14) FSW-0 No. 8 Mass: 2,500 kg (5,500 lb). Spacecraft: FSW. Agency: MAI. Perigee: 169 km (105 mi). Apogee: 337 km (209 mi). Inclination: 57.00 deg. Period: 89.60 min. Fanhui Shi Weixing recoverable satellite; capsule re-entered October 11 after five day mission.

1987 August 5 - 06:39 GMT - Jiuquan LA2B. LV Model: CZ-2C . Chang Zheng 2C CZ2C-9 (15) FSW-0 No. 9 Mass: 2,500 kg (5,500 lb). Spacecraft: FSW. Agency: MAI. Perigee: 169 km (105 mi). Apogee: 366 km (227 mi). Inclination: 63.00 deg. Period: 89.90 min. Fanhui Shi Weixing recoverable satellite; carried microgravity experiments; return capsule recovered August 10 after five days in space.

1987 September 9 - 07:15 GMT - Jiuquan LA2B. LV Model: CZ-2C . Chang Zheng 2C CZ2C-10 (16) FSW-1 No. 1 Mass: 2,100 kg (4,600 lb). Spacecraft: FSW. Agency: MAI. Perigee: 181 km (112 mi). Apogee: 222 km (137 mi). Inclination: 63.00 deg. Period: 88.50 min. Fanhui Shi Weixing recoverable satellite; return capsule recovered September 17 after eight days in space.

1988 March 7 - 12:41 GMT - Xichang LC1. LV Model: CZ-3 . Chang Zheng 3 CZ3-4 (17) Zhongxing-1 Mass: 1,024 kg (2,257 lb). Spacecraft: DFH-2. Agency: Chinasat. Perigee: 35,786 km (22,236 mi). Apogee: 35,789 km (22,238 mi). Inclination: 0.50 deg. Period: 1,436.20 min. 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 - Jiuquan LA2B. LV Model: CZ-2C . Chang Zheng 2C CZ2C-11 (18) FSW-1 No. 2 Mass: 2,100 kg (4,600 lb). Spacecraft: FSW. Agency: MAI. Perigee: 204 km (126 mi). Apogee: 311 km (193 mi). Inclination: 63.00 deg. Period: 89.70 min. German crystal growth experiment in recoverable capsule. Results marred by hard landing.

1988 September 6 - 20:30 GMT - Taiyuan LC1. LV Model: CZ-4A . Chang Zheng 4 CZ4-1 (19) FY-1A Mass: 750 kg (1,650 lb). Spacecraft: FY-1. Agency: MAI. Perigee: 875 km (543 mi). Apogee: 895 km (556 mi). Inclination: 98.80 deg. Period: 102.70 min. 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 - Xichang LC1. LV Model: CZ-3 . Chang Zheng 3 CZ3-5 (20) Zhongxing-2 Mass: 1,024 kg (2,257 lb). Spacecraft: DFH-2. Agency: Chinasat. Perigee: 35,787 km (22,236 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.10 deg. Period: 1,436.20 min. 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 - Xichang LC1. LV Model: CZ-3 . Chang Zheng 3 CZ3-6 (21) Zhongxing-3 Mass: 1,024 kg (2,257 lb). Spacecraft: DFH-2. Agency: Chinasat. Perigee: 35,783 km (22,234 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.00 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 - Xichang LC1. LV Model: CZ-3 . Chang Zheng 3 CZ3-7 (22) Asiasat 1 Mass: 1,442 kg (3,179 lb). Spacecraft: HS 376. Agency: Asiasat. Perigee: 35,786 km (22,236 mi). Apogee: 35,789 km (22,238 mi). Inclination: 2.70 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 - Xichang LC2. LV Model: CZ-2E . Chang Zheng 2E CZ2E-1 (23) Badr-A Mass: 52 kg (114 lb). Spacecraft: Badr. Agency: Suparco. Perigee: 208 km (129 mi). Apogee: 988 km (613 mi). Inclination: 28.50 deg. Period: 96.70 min. First launch of new Chinese launch vehicle. Experimental Pakistani payload.

1990 September 3 - 00:53 GMT - Taiyuan LC1. LV Model: CZ-4A . Chang Zheng 4 CZ4-2 (24) FY-1B Mass: 881 kg (1,942 lb). Spacecraft: FY-1. Agency: MAI. Perigee: 875 km (543 mi). Apogee: 897 km (557 mi). Inclination: 98.80 deg. Period: 102.70 min. Experimental weather satellite. Operated for over a year.

1990 October 5 - 06:14 GMT - Jiuquan LA2B. LV Model: CZ-2C . Chang Zheng 2C CZ2C-12 (25) FSW-1 No. 3 Mass: 2,100 kg (4,600 lb). Spacecraft: FSW. Agency: MAI. Perigee: 208 km (129 mi). Apogee: 312 km (193 mi). Inclination: 57.00 deg. Period: 89.70 min. Fanhui Shi Weixing recoverable satellite; carried biological research experiments.

1991 December 28 - 12:00 GMT - Xichang LC1. LV Model: CZ-3 . Chang Zheng 3 CZ3-8 (26) FAILURE: Third stage failed to ignite. Partial Failure. Zhongxing-4 Mass: 1,025 kg (2,259 lb). Spacecraft: DFH-2. Agency: Chinasat. Perigee: 2,023 km (1,257 mi). Apogee: 34,041 km (21,152 mi). Inclination: 32.30 deg. Period: 632.60 min. Third stage failure; unusable orbit. DFH-2 operational communications satellite.

1992 August 9 - 08:00 GMT - Jiuquan LA2B. LV Model: CZ-2D . Chang Zheng 2D CZ2D-1 (27) FSW-2 No. 1 Mass: 2,500 kg (5,500 lb). Spacecraft: FSW. Agency: MAI. Perigee: 171 km (106 mi). Apogee: 332 km (206 mi). Inclination: 63.10 deg. Period: 89.50 min. Fanhui Shi Weixing recoverable imaging satellite; carried microgravity experiments; capsule returned August 25 after 15 days in orbit.

1992 August 13 - 23:00 GMT - Xichang LC2. LV Model: CZ-2E . Chang Zheng 2E CZ2E-2 (28) Optus B1 Mass: 2,760 kg (6,080 lb). Spacecraft: HS 601. Agency: Optus. Perigee: 35,774 km (22,228 mi). Apogee: 35,800 km (22,200 mi). Inclination: 0.00 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 - Jiuquan LA2B. LV Model: CZ-2C . Chang Zheng 2C CZ2C-13 (29) Freja Mass: 259 kg (570 lb). Spacecraft: Freja. Agency: SSC. Perigee: 590 km (360 mi). Apogee: 1,763 km (1,095 mi). Inclination: 63.00 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.

1992 December 21 - 11:21 GMT - Xichang LC2. LV Model: CZ-2E . 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. Aussat B2 / Optus B2 Mass: 2,760 kg (6,080 lb). Spacecraft: HS 601. Agency: Hughes. Perigee: 206 km (128 mi). Apogee: 816 km (507 mi). Inclination: 28.10 deg. Period: 94.90 min. 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 - Jiuquan LA2B. LV Model: CZ-2C . Chang Zheng 2C CZ2C-14 (31) FSW-1 No. 5 Mass: 2,099 kg (4,627 lb). Spacecraft: FSW. Agency: CASC. Perigee: 181 km (112 mi). Apogee: 2,860 km (1,770 mi). Inclination: 56.60 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 - Xichang LC2. LV Model: CZ-3A . Chang Zheng 3A CZ3A-1 (32) SJ-4 Mass: 400 kg (880 lb). Spacecraft: SJ. Agency: CASC. Perigee: 195 km (121 mi). Apogee: 26,837 km (16,675 mi). Inclination: 28.70 deg. Period: 465.40 min. Particles and fields research.

1994 July 3 - 08:00 GMT - Jiuquan LA2B. LV Model: CZ-2D . Chang Zheng 2D CZ2D-2 (33) FSW-2 No. 2 Mass: 2,600 kg (5,700 lb). Spacecraft: FSW. Agency: CASC. Perigee: 207 km (128 mi). Apogee: 350 km (210 mi). Inclination: 62.90 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 - Xichang LC1. LV Model: CZ-3 . Chang Zheng 3 CZ3-9 (34) Apstar 1 Mass: 1,383 kg (3,048 lb). Spacecraft: HS 376. Agency: APT. Perigee: 35,785 km (22,235 mi). Apogee: 35,789 km (22,238 mi). Inclination: 0.00 deg. Period: 1,436.12 min. 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 - Xichang LC2. LV Model: CZ-2E . Chang Zheng 2E CZ2E-4 (35) Optus B3 Mass: 2,760 kg (6,080 lb). Spacecraft: HS 601. Agency: Optus. Perigee: 35,718 km (22,194 mi). Apogee: 35,855 km (22,279 mi). Inclination: 0.00 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 - Xichang LC2. LV Model: CZ-3A . Chang Zheng 3A CZ3A-2 (36) Zhongxing-5 Mass: 2,230 kg (4,910 lb). Spacecraft: DFH-3. Agency: Chinasat. Perigee: 35,225 km (21,887 mi). Apogee: 35,957 km (22,342 mi). Inclination: 0.15 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 - Xichang LC2. LV Model: CZ-2E . 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. Apstar 2 Spacecraft: HS 601. Agency: PRC. 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 - Xichang LC2. LV Model: CZ-2E . Chang Zheng 2E CZ2E-6 (38) Asiasat 2 Mass: 3,485 kg (7,683 lb). Spacecraft: AS 7000. Agency: Asiasat. Perigee: 35,777 km (22,230 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.40 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 - Xichang LC2. LV Model: CZ-2E . Chang Zheng 2E CZ2E-7 (39) Echostar 1 Mass: 3,288 kg (7,248 lb). Spacecraft: AS 7000. Agency: TCI. Perigee: 35,777 km (22,230 mi). Apogee: 35,796 km (22,242 mi). Inclination: 0.00 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 - Xichang LC2. LV Model: CZ-3B . Chang Zheng 3B CZ3B-1 (40) FAILURE: Guidance failure resulted in launch vehicle crashing 22 seconds after launch, killing or injuring 59 people. Intelsat 708 Spacecraft: FS-1300. Agency: PRC. 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 - Xichang LC1. LV Model: CZ-3 . Chang Zheng 3 CZ3-10 (41) Apstar 1A Mass: 2,800 kg (6,100 lb). Spacecraft: HS 376. Agency: APT. Perigee: 35,785 km (22,235 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.00 deg. Period: 1,436.10 min. 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 - Xichang LC1. LV Model: CZ-3 . Chang Zheng 3 CZ3-11 (42) Zhongxing 7 Spacecraft: HS 376. Agency: Chinasat. Perigee: 21,674 km (13,467 mi). Apogee: 46,499 km (28,893 mi). Inclination: 26.30 deg. Period: 1,350.20 min.

1996 October 20 - 07:20 GMT - Jiuquan LA2B. LV Model: CZ-2D . Chang Zheng 2D CZ2D-3 (43) FSW-2 No. 3 Mass: 2,600 kg (5,700 lb). Spacecraft: FSW. Agency: CASC. Perigee: 121 km (75 mi). Apogee: 133 km (82 mi). Inclination: 63.00 deg. Period: 87.00 min. Final launch in the FSW series. Landed in China on November 4 after 15 days in orbit.

1997 May 11 - 16:17 GMT - Xichang LC2. LV Model: CZ-3A . Chang Zheng 3A CZ3A-3 (44) Zhongxing-6 Mass: 2,200 kg (4,800 lb). Spacecraft: DFH-3. Agency: Chinasat. Perigee: 35,776 km (22,230 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.00 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 - Xichang LC1. LV Model: CZ-3 . Chang Zheng 3 CZ3-12 (45) FY-2A Spacecraft: FY-2. Agency: CASC. Perigee: 35,783 km (22,234 mi). Apogee: 35,784 km (22,235 mi). Inclination: 0.80 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 - Xichang LC2. LV Model: CZ-3B . Chang Zheng 3B CZ3B-2 (46) Agila 2 Spacecraft: FS-1300. Agency: MPSC. Perigee: 35,771 km (22,227 mi). Apogee: 35,803 km (22,246 mi). Inclination: 0.00 deg. Period: 1,436.20 min. 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 - Taiyuan LC1. LV Model: CZ-2C/SD . Chang Zheng 2C-III/SD CZ2C-15 (47) Iridium Mass: 689 kg (1,518 lb). Spacecraft: LM 700. Agency: CASC. Perigee: 620 km (380 mi). Apogee: 633 km (393 mi). Inclination: 86.34 deg. Period: 97.25 min. Plane 5. Ascending node 271.9 degrees. Dummy satellite.

1997 October 16 - 19:13 GMT - Xichang LC2. LV Model: CZ-3B . Chang Zheng 3B CZ3B-3 (48) Apstar 2R Spacecraft: FS-1300. Agency: APT. Perigee: 35,774 km (22,228 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min. 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 - Taiyuan LC1. LV Model: CZ-2C/SD . Chang Zheng 2C-III/SD CZ2C-16 (49) Iridium 42 Mass: 689 kg (1,518 lb). Spacecraft: LM 700. Agency: Iridium. Perigee: 776 km (482 mi). Apogee: 780 km (480 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 6. Ascending node 325.8 degrees.

1998 March 25 - 17:01 GMT - Taiyuan LC1. LV Model: CZ-2C/SD . Chang Zheng 2C-III/SD CZ2C-17 (50) Iridium 51 Mass: 689 kg (1,518 lb). Spacecraft: LM 700. Agency: Iridium. Perigee: 751 km (466 mi). Apogee: 756 km (469 mi). Inclination: 86.45 deg. Period: 99.90 min. Plane 4. Ascending node 262.5 degrees. Not in service.

1998 May 2 - 09:16 GMT - Taiyuan LC1. LV Model: CZ-2C/SD . Chang Zheng 2C-III/SD CZ2C-18 (51) Iridium 69 Mass: 689 kg (1,518 lb). Spacecraft: LM 700. Agency: Iridium. Perigee: 777 km (482 mi). Apogee: 783 km (486 mi). Inclination: 86.40 deg. Period: 100.46 min. Plane 2. Ascending node 199.4 degrees. Not in service.

1998 May 30 - 10:00 GMT - Xichang LC2. LV Model: CZ-3B . Chang Zheng 3B CZ3B-4 (52) Zhongwei 1 Spacecraft: AS 2100. Agency: China Or. Perigee: 35,777 km (22,230 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.10 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 - Xichang LC2. LV Model: CZ-3B . Chang Zheng 3B CZ3B-5 (53) Sinosat Mass: 2,820 kg (6,210 lb). Spacecraft: Spacebus 3000 . Agency: Eurasspa. Perigee: 35,779 km (22,231 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.10 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 - Taiyuan LC1. LV Model: CZ-2C/SD . Chang Zheng 2C-III/SD CZ2C-19 (54) Iridium 3 Mass: 689 kg (1,518 lb). Spacecraft: LM 700. Agency: Iridium. Perigee: 776 km (482 mi). Apogee: 779 km (484 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 199.4 degrees.

1998 December 19 - 11:39 GMT - Taiyuan LC1. LV Model: CZ-2C/SD . Chang Zheng 2C-III/SD CZ2C-20 (55) Iridium 11 Mass: 689 kg (1,518 lb). Spacecraft: LM 700. Agency: Iridium. Perigee: 776 km (482 mi). Apogee: 780 km (480 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 197 degrees. Parking orbit.

1999 March 11 - Chinese Man-Rated Launch Vehicle Test Predicted Spacecraft: Shenzhou. 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 - Manned Program Delayed Spacecraft: Shenzhou. 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 - Taiyuan LC1. LV Model: CZ-4B . Chang Zheng 4B CZ4B-1 (56) FY-1C Spacecraft: FY-1. Agency: CASC. Perigee: 847 km (526 mi). Apogee: 869 km (539 mi). Inclination: 98.80 deg. 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.

1999 June 9 - CZ-2F Photograph Appears on the Internet 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 - Taiyuan LC1. LV Model: CZ-2C/SD . Chang Zheng 2C-III/SD CZ2C-21 (57) Iridium 14A Spacecraft: LM 700. Agency: Iridium. Perigee: 708 km (439 mi). Apogee: 711 km (441 mi). Inclination: 86.50 deg. Period: 99.00 min.

1999 August 15 - China Upgrades Launch Facilities 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 - Taiyuan LC1. LV Model: CZ-4B . Chang Zheng 4B CZ4B-2 (58) ZY-1 Mass: 1,540 kg (3,390 lb). Spacecraft: ZY. Agency: CAST/INP. Perigee: 773 km (480 mi). Apogee: 774 km (480 mi). Inclination: 98.60 deg. 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.

1999 November 19 - 22:30 GMT - Jiuquan SLS. LV Model: CZ-2F . Chang Zheng 2F CZ2F-1 (59) Shenzhou Mass: 7,600 kg (16,700 lb). Spacecraft: Shenzhou. Agency: CASC. Perigee: 196 km (122 mi). Apogee: 324 km (202 mi). Inclination: 42.60 deg. 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: Shenzhou.

2000 January 25 - 16:45 GMT - Xichang LC2. LV Model: CZ-3A . Chang Zheng 3A CZ3A-4 (60) Zhongxing-22 Mass: 2,300 kg (5,000 lb). Spacecraft: FH-1. Agency: CAST. Perigee: 35,771 km (22,227 mi). Apogee: 35,803 km (22,246 mi). Inclination: 0.00 deg. 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 - Xichang LC1. LV Model: CZ-3 . Chang Zheng 3 CZ3-13 (61) Fengyun-2 Mass: 1,250 kg (2,750 lb). Spacecraft: FY-2. Agency: CASC. Perigee: 35,786 km (22,236 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.80 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 - Taiyuan LC1. LV Model: CZ-4B . Chang Zheng 4B CZ4B-3 (62) ZY-2 Spacecraft: ZY. Agency: CAST. Perigee: 489 km (304 mi). Apogee: 501 km (311 mi). Inclination: 97.41 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 - China Reveals New Launcher Detail 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 - Xichang LC2. LV Model: CZ-3A . Chang Zheng 3A CZ3A-5 (63) Beidou 1A Mass: 2,200 kg (4,800 lb). Spacecraft: Beidou. Agency: CNSA. Perigee: 35,772 km (22,227 mi). Apogee: 35,803 km (22,246 mi). Inclination: 0.10 deg. 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 - Xichang LC2. LV Model: CZ-3A . Chang Zheng 3A CZ3A-6 (64) Beidou 1B Mass: 2,200 kg (4,800 lb). Spacecraft: Beidou. Agency: CNSA. Perigee: 35,753 km (22,215 mi). Apogee: 35,821 km (22,258 mi). Inclination: 0.00 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 - Jiuquan SLS. LV Model: CZ-2F . Chang Zheng 2F CZ2F-2 (65) Shenzhou 2 Mass: 7,400 kg (16,300 lb). Spacecraft: Shenzhou. Agency: CASC. Perigee: 330 km (200 mi). Apogee: 346 km (214 mi). Inclination: 42.60 deg. 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 - Jiuquan SLS. LV Model: CZ-2F . Chang Zheng 2F CZ2F-3 (66) Shenzhou 3 Mass: 7,800 kg (17,100 lb). Spacecraft: Shenzhou. Agency: China Aerospace Corp. (China). Perigee: 374 km (232 mi). Apogee: 379 km (235 mi). Inclination: 42.40 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 - Taiyuan LC1. LV Model: CZ-4B . Chang Zheng 4B CZ4B-4 (67) Hai Yang 1 Mass: 360 kg (790 lb). Spacecraft: HY-1. Agency: CASC. Perigee: 793 km (492 mi). Apogee: 799 km (496 mi). Inclination: 98.80 deg. 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.

2002 October 27 - 03:17 GMT - Taiyuan LC1. LV Model: CZ-4B . Chang Zheng 4B CZ4B-5 (68) ZY-2 Spacecraft: ZY. Agency: Chinese Academy of Space Technology. Perigee: 470 km (290 mi). Apogee: 483 km (300 mi). Inclination: 97.40 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 - Jiuquan SLS. LV Model: CZ-2F . Chang Zheng 2F CZ2F-4 (69) Shenzhou 4 Mass: 7,794 kg (17,182 lb). Spacecraft: Shenzhou. Agency: China Aerospace Corp. (China). Perigee: 331 km (205 mi). Apogee: 337 km (209 mi). Inclination: 42.40 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 - Xichang LC2. LV Model: CZ-3A . Chang Zheng 3A CZ3A-7 (70) Beidou 2A Mass: 2,200 kg (4,800 lb). Spacecraft: Beidou. Perigee: 35,760 km (22,220 mi). Apogee: 35,836 km (22,267 mi). Inclination: 0.30 deg. Period: 1,436.70 min. 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 - Jiuquan SLS. LV Model: CZ-2F . Chang Zheng 2F CZ2F-5 (71) Shenzhou 5 Mass: 7,840 kg (17,280 lb). Spacecraft: Shenzhou. Agency: PLAAF. Perigee: 332 km (206 mi). Apogee: 336 km (208 mi). Inclination: 42.42 deg. Period: 91.20 min. Crew: Yang Liwei. Flight: Shenzhou 5. 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 - Taiyuan LC1. LV Model: CZ-4B . Chang Zheng 4B CZ4B-6 (72) ZY-1-2 (CBERS-2) Mass: 1,500 kg (3,300 lb). Spacecraft: ZY. Agency: China Aerospace Corp. (China), INPE (Brazil). Perigee: 731 km (454 mi). Apogee: 750 km (460 mi). Inclination: 98.50 deg. Period: 99.60 min. Delayed from late 2001, September 3 2002, March 14 and September 2003. Second China-Brazil Earth Resources Satellite (CBERS 2).

2003 November 2 - 07:20 GMT - Jiuquan SLS-2. LV Model: CZ-2D . Chang Zheng 2D CZ2D-4 (73) FSW-3 No. 1 Mass: 3,000 kg (6,600 lb). Spacecraft: FSW. Agency: Shangai Academy of Space Technology. Perigee: 141 km (87 mi). Apogee: 165 km (102 mi). Inclination: 63.00 deg. Period: 87.50 min. Expected to have been long-awaited 'seeds in space' mission but official announcements spoke only of photography.

2003 November 14 - 16:01 GMT - Xichang LC2. LV Model: CZ-3A . Chang Zheng 3A CZ3A-8 (74) Zhongxing 20 Mass: 2,300 kg (5,000 lb). Spacecraft: DFH-3. Perigee: 35,762 km (22,221 mi). Apogee: 35,811 km (22,251 mi). Inclination: 0.00 deg. Period: 1,436.10 min. 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 - Xichang LC1. LV Model: CZ-2C . Chang Zheng 2C CZ2C-22 (75) Tan Ce 1 Mass: 350 kg (770 lb). Spacecraft: Double Star. Perigee: 555 km (344 mi). Apogee: 78,051 km (48,498 mi). Inclination: 28.50 deg. 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 - Xichang LC1. LV Model: CZ-2C . Chang Zheng 2C CZ2C-23 (76) Tansuo 1 Mass: 204 kg (449 lb). Spacecraft: Shiyan. Agency: University of Harbin. Perigee: 598 km (371 mi). Apogee: 616 km (382 mi). Inclination: 97.70 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.

2004 July 25 - 07:05 GMT - Taiyuan LC1. LV Model: CZ-2C . Chang Zheng 2C CZ2C-24 (77) Tan Ce 2 Mass: 660 kg (1,450 lb). Spacecraft: Double Star. Perigee: 655 km (406 mi). Apogee: 38,574 km (23,968 mi). Inclination: 90.00 deg. Period: 695.10 min. Delayed from June, July 20

2004 August 29 - 07:50 GMT - Jiuquan SLS. LV Model: CZ-2C . Chang Zheng 2C CZ2C-25 (78) FSW-3 No. 2 Mass: 2,100 kg (4,600 lb). Spacecraft: FSW. Perigee: 168 km (104 mi). Apogee: 547 km (339 mi). Inclination: 63.00 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 - Taiyuan LC1. LV Model: CZ-4B . Chang Zheng 4B CZ4B-7 (79) SJ-6A Spacecraft: SJ-6. Perigee: 578 km (359 mi). Apogee: 593 km (368 mi). Inclination: 97.70 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 Corporati