1971 September 10 - Launch Vehicle: CZ. Agency: PRC. Apogee: 1,000 km (600 mi). Research and Development Suborbital Flight

1972 August 10 - 00:32 GMT - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. LV Model: FB-1 . Feng Bao 1 701-03 FAILURE: Failure. JSSW 1 Spacecraft: JSSW. Agency: PRC.

1974 July 14 - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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(1764).

1975 December 16 - 09:19 GMT - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. LV Model: FB-1 . Feng Bao 1 701-08 FAILURE: Failure. JSSW 6 Spacecraft: JSSW. Agency: PRC.

1976 December 7 - 04:38 GMT - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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 April 15 - 16:39 GMT - Launch Vehicle: CZ. LV Model: FB-1 . Feng Bao 1 701(II)-02 DDDS test Agency: PRC. Apogee: 200 km (120 mi).

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

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

1979 July 28 - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. Agency: PRC. Apogee: 1,000 km (600 mi). Other sources say launch was from Taiyuan on 2 August.

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

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

1980 May 18 - Launch Vehicle: CZ. Test mission Agency: PRC. Apogee: 1,000 km (600 mi).

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

1981 September 19 - 21:28 GMT - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. Agency: PRC. Apogee: 1,000 km (600 mi). Other sources say launch was from Taiyuan.

1982 September 9 - 07:19 GMT - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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 September 12 - 05:44 GMT - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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 October 6 - 05:40 GMT - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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 August 5 - 07:29 GMT - Launch Vehicle: CZ. 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.

1990 October 5 - 06:14 GMT - Launch Vehicle: CZ. 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.

1992 August 9 - 08:00 GMT - Launch Vehicle: CZ. 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 October 6 - 06:20 GMT - Launch Vehicle: CZ. 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.

1993 October 8 - 08:00 GMT - Launch Vehicle: CZ. 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 July 3 - 08:00 GMT - Launch Vehicle: CZ. 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