1990 July 16 - 00:40 GMT - Launch Vehicle: CZ. 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.

1992 August 13 - 23:00 GMT - Launch Vehicle: CZ. 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 December 21 - 11:21 GMT - Launch Vehicle: CZ. 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.

1994 February 8 - 08:34 GMT - Launch Vehicle: CZ. 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 August 27 - 23:10 GMT - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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.

1997 May 11 - 16:17 GMT - Launch Vehicle: CZ. 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 August 19 - 17:50 GMT - Launch Vehicle: CZ. 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 October 16 - 19:13 GMT - Launch Vehicle: CZ. 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.

1998 May 30 - 10:00 GMT - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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.

2000 January 25 - 16:45 GMT - Launch Vehicle: CZ. 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 October 30 - Launch Vehicle: CZ. 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 - Launch Vehicle: CZ. 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.

2003 May 24 - Launch Vehicle: CZ. 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 November 14 - 16:01 GMT - Launch Vehicle: CZ. 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.

2004 October 19 - 01:20 GMT - Launch Vehicle: CZ. LV Model: CZ-3A . Chang Zheng 3A CZ3A-9 (81) FY-2C Mass: 1,380 kg (3,040 lb). Spacecraft: FY-2. Perigee: 35,786 km (22,236 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.70 deg. Period: 1,436.20 min. Third Fengyun-2 weather satellite. The apogee motor placed the satellite into a drifting geostationary orbit. As of the date of the launch, four FY-2 satellites had been launched. FY-2 01 was destroyed in a ground fire 1994. FY-2 02 / FY-2A was placed in reserve in May 2000 86 deg E; and FY-2 03 / FY-2B was operational at 123 deg E. As of 2007 Mar 11 located at 104.44E drifting at 0.026W degrees per day.

2005 April 12 - 12:00 GMT - Launch Vehicle: CZ. LV Model: CZ-3B . Chang Zheng 3B CZ3B (84) APSTAR 6 Mass: 4,680 kg (10,310 lb). Spacecraft: Spacebus 4000. Agency: APT Satellite. Perigee: 256 km (159 mi). Apogee: 49,629 km (30,837 mi). Inclination: 26.00 deg. Period: 919.40 min. Delayed from November, December 4, 2004. Ku and C band transponders. As of 2007 Mar 11 located at 133.99E drifting at 0.013W degrees per day.

2006 September 12 - 16:02 GMT - Launch Vehicle: CZ. LV Model: CZ-3A . Chang Zheng 3A CZ3A-10 (91) Zhongxing 22A Mass: 2,300 kg (5,000 lb). Spacecraft: FH-1. Agency: CTBSC. Perigee: 35,757 km (22,218 mi). Apogee: 35,817 km (22,255 mi). Inclination: 0.40 deg. Period: 1,000.00 min. Military communications satellite, launched to replace Zhongxing 22 in geosynchronous orbit at 98.0 E. As of 2007 Mar 10 located at 98.10E drifting at 0.006W degrees per day.

2006 October 28 - 16:20 GMT - Launch Vehicle: CZ. LV Model: CZ-3B . Chang Zheng 3B CZ3B (93) Xinnuo 2 Spacecraft: DFH-4. Perigee: 35,675 km (22,167 mi). Apogee: 35,911 km (22,314 mi). Inclination: 0.0600 deg. Period: 1,436.44 min. First DH-4 heavy Chinese communication satellite with communications equipment provided by Alcatel Alenia. Mission failed when solar panels and antennae failed to deploy in geosynchronous orbit. This was a blow to China's prestige, since the satellite was an important part of the 2008 Beijing Olympics coverage plans. As of 2007 Mar 10 located at 91.80E drifting at 0.093W degrees per day.

2006 December 8 - 00:53 GMT - Launch Vehicle: CZ. LV Model: CZ-3A . Chang Zheng 3A CZ3A-11 (94) FY 2D Spacecraft: FY-2. Perigee: 35,781 km (22,233 mi). Apogee: 35,789 km (22,238 mi). Inclination: 2.60 deg. Period: 1,436.00 min. Fourth Wind and Cloud 2 geostationary weather satellite with an infrared radiometer as its primary instrument. The booster placed the spacecraft in a 226 x 36221 km x 24.9 deg geosynchronous transfer orbit. The FG-36 solid apogee motor aboard the satellite burned at 18:07 GMT and placed the FY-2D into an initial 35786 x 36478 km x 2.6 deg geosynchronous drift orbit.

2007 February 2 - 16:28 GMT - Launch Vehicle: CZ. LV Model: CZ-3A . Chang Zheng 3A CZ3A-12 (95) Beidou 2A Mass: 2,200 kg (4,800 lb). Spacecraft: Beidou. Perigee: 35,326 km (21,950 mi). Apogee: 36,248 km (22,523 mi). Inclination: 6.20 deg. Period: 1,436.10 min. Fourth Beidou satellite. It did not reach geostationary orbit until early April following deployment problems with its solar panels and reports of US detection of a debris cloud at the time of the original expected apogee firing.