Xichang Credit - © Mark Wade

China's launch site for geosynchronous orbit launches. Xichang Satellite Launch Centre is situated in Xichang, Sichuan Province, south-western China. The launch pad is at 102.0 degrees East and 28.2 degrees North. The head office of the launch centre is located in Xichang City, about 65 kilometres away. Xichang Airport is 50 km away. A dedicated railway and highway lead directly to the launch site. The Technical Centre is equipped for testing and integration of the payload and launch vehicle. The Mission Command and Control Centre, located 7 kilometres south-west of the launch pad, provides flight and safety control during launch rehearsal and launch. The down range tracking stations for Xichang are located in Xichang City and Yibin City of Sichuan Province, and Guiyang City of Guizhou Province. Other facilities include the Launch Complex, the Launch Control Centre, propellant fuelling systems, communications systems for launch command, telephone and data communications for users, and support equipment for meteorological monitoring and forecasting. Most of the commercial satellite launches of Long March vehicles have been from Xichang.

• Name: Launch Complex 1. Latitude: 28.2500 N. Longitude: 102.0200 E. Launch Pads: 1. CZ-3.

• Name: Launch Complex 2. Latitude: 28.2500 N. Longitude: 102.0200 E. Launch Pads: 1. CZ-2E, CZ-3A, CZ-3B.

Xichang Credit - © Mark Wade

• 1984 January 29 12:25 - STTW-T1 Launch Vehicle: CZ-3. Third stage failed to ignite.. Chang Zheng 3 CZ3-1 (9) LC: LC1. Apogee: 6,446 km (4,005 mi). 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 - STTW-T2 Launch Vehicle: CZ-3. Chang Zheng 3 CZ3-2 (10) LC: LC1. Apogee: 35,796 km (22,242 mi). 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.

• 1986 February 1 12:37 - STTW 1 Launch Vehicle: CZ-3. Chang Zheng 3 CZ3-3 (13) LC: LC1. Apogee: 35,819 km (22,256 mi). 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.

• 1988 March 7 12:41 - Zhongxing-1 Launch Vehicle: CZ-3. Chang Zheng 3 CZ3-4 (17) LC: LC1. Apogee: 35,789 km (22,238 mi). 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 December 22 12:40 - Zhongxing-2 Launch Vehicle: CZ-3. Chang Zheng 3 CZ3-5 (20) LC: LC1. Apogee: 35,791 km (22,239 mi). 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 - Zhongxing-3 Launch Vehicle: CZ-3. Chang Zheng 3 CZ3-6 (21) LC: LC1. Apogee: 35,795 km (22,241 mi). 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 - Asiasat 1 Launch Vehicle: CZ-3. Chang Zheng 3 CZ3-7 (22) LC: LC1. Apogee: 35,789 km (22,238 mi). 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 - Badr-A Launch Vehicle: CZ-2E. Chang Zheng 2E CZ2E-1 (23) LC: LC2. Apogee: 988 km (613 mi). First launch of new Chinese launch vehicle. Experimental Pakistani payload.

• 1991 December 28 12:00 - Zhongxing-4 Launch Vehicle: CZ-3. Third stage failed to ignite. Partial Failure.. Chang Zheng 3 CZ3-8 (26) LC: LC1. Apogee: 34,041 km (21,152 mi). Third stage failure; unusable orbit. DFH-2 operational communications satellite.

• 1992 August 13 23:00 - Optus B1 Launch Vehicle: CZ-2E. Chang Zheng 2E CZ2E-2 (28) LC: LC2. Apogee: 35,800 km (22,200 mi). 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 - Aussat B2 / Optus B2 Launch Vehicle: CZ-2E. Shortcomings in the guidance system lead to the vehicle not anticipating the true effects of hoizontal wind-shear once the mountains surrounding the launch site were cleared. This caused the nose fairing to collapse 45 seconds after launch.. Chang Zheng 2E CZ2E-3 (30) LC: LC2. Apogee: 816 km (507 mi). 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 - SJ-4 Launch Vehicle: CZ-3A. Chang Zheng 3A CZ3A-1 (32) LC: LC2. Apogee: 26,837 km (16,675 mi). Particles and fields research.

• 1994 July 21 10:55 - Apstar 1 Launch Vehicle: CZ-3. Chang Zheng 3 CZ3-9 (34) LC: LC1. Apogee: 35,789 km (22,238 mi). 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 - Optus B3 Launch Vehicle: CZ-2E. Chang Zheng 2E CZ2E-4 (35) LC: LC2. Apogee: 35,855 km (22,279 mi). 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 - Zhongxing-5 Launch Vehicle: CZ-3A. Chang Zheng 3A CZ3A-2 (36) LC: LC2. Apogee: 35,957 km (22,342 mi). 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 - Apstar 2 Launch Vehicle: CZ-2E. Shortcomings in the guidance system lead to the vehicle not anticipating the true effects of hoizontal wind-shear once the mountains surrounding the launch site were cleared. This caused the nose fairing to collapse and the spacecraft to be destroyed.. Chang Zheng 2E CZ2E-5 (37) LC: LC2. 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 - Asiasat 2 Launch Vehicle: CZ-2E. Chang Zheng 2E CZ2E-6 (38) LC: LC2. Apogee: 35,798 km (22,243 mi). 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 - Echostar 1 Launch Vehicle: CZ-2E. Chang Zheng 2E CZ2E-7 (39) LC: LC2. Apogee: 35,796 km (22,242 mi). 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 - Intelsat 708 Launch Vehicle: CZ-3B. Guidance failure resulted in launch vehicle crashing 22 seconds after launch, killing or injuring 59 people.. Chang Zheng 3B CZ3B-1 (40) LC: LC2. 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 - Apstar 1A Launch Vehicle: CZ-3. Chang Zheng 3 CZ3-10 (41) LC: LC1. Apogee: 35,791 km (22,239 mi). 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 - Zhongxing 7 Launch Vehicle: CZ-3. Chang Zheng 3 CZ3-11 (42) LC: LC1. Apogee: 46,499 km (28,893 mi).

• 1997 May 11 16:17 - Zhongxing-6 Launch Vehicle: CZ-3A. Chang Zheng 3A CZ3A-3 (44) LC: LC2. Apogee: 35,797 km (22,243 mi). 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 - FY-2A Launch Vehicle: CZ-3. Chang Zheng 3 CZ3-12 (45) LC: LC1. Apogee: 35,784 km (22,235 mi). 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 - Agila 2 Launch Vehicle: CZ-3B. Chang Zheng 3B CZ3B-2 (46) LC: LC2. Apogee: 35,803 km (22,246 mi). 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 - Apstar 2R Launch Vehicle: CZ-3B. Chang Zheng 3B CZ3B-3 (48) LC: LC2. Apogee: 35,798 km (22,243 mi). 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 - Zhongwei 1 Launch Vehicle: CZ-3B. Chang Zheng 3B CZ3B-4 (52) LC: LC2. Apogee: 35,798 km (22,243 mi). 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 - Sinosat Launch Vehicle: CZ-3B. Chang Zheng 3B CZ3B-5 (53) LC: LC2. Apogee: 35,795 km (22,241 mi). 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 - Zhongxing-22 Launch Vehicle: CZ-3A. Chang Zheng 3A CZ3A-4 (60) LC: LC2. Apogee: 35,803 km (22,246 mi). 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 - Fengyun-2 Launch Vehicle: CZ-3. Chang Zheng 3 CZ3-13 (61) LC: LC1. Apogee: 35,790 km (22,230 mi). 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 October 30 - Beidou 1A Launch Vehicle: CZ-3A. Chang Zheng 3A CZ3A-5 (63) LC: LC2. Apogee: 35,803 km (22,246 mi). 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 - Beidou 1B Launch Vehicle: CZ-3A. Chang Zheng 3A CZ3A-6 (64) LC: LC2. Apogee: 35,821 km (22,258 mi). 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 - Beidou 2A Launch Vehicle: CZ-3A. Apogee: 35,836 km (22,267 mi). 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 - Zhongxing 20 Launch Vehicle: CZ-3A. Apogee: 35,811 km (22,251 mi). Military communications satellite. As of 2007 Mar 11 located at 103.00E drifting at 0.010W degrees per day.

• 2003 December 29 19:06 - Tan Ce 1 Launch Vehicle: CZ-2C. CZ-2C/SM Apogee: 78,051 km (48,498 mi). 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 - Tansuo 1 Launch Vehicle: CZ-2C. Apogee: 616 km (382 mi). 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 October 19 01:20 - FY-2C Launch Vehicle: CZ-3A. Apogee: 35,791 km (22,239 mi). Third Fengyun-2 weather satellite. The apogee motor placed the satellite into a drifting geostationary orbit. As of the date of the launch, four FY-2 satellites had been launched. FY-2 01 was destroyed in a ground fire 1994. FY-2 02 / FY-2A was placed in reserve in May 2000 86 deg E; and FY-2 03 / FY-2B was operational at 123 deg E. As of 2007 Mar 11 located at 104.44E drifting at 0.026W degrees per day.

• 2004 November 18 10:45 - Shiyan Weixing 2 Launch Vehicle: CZ-2C. Apogee: 711 km (441 mi). Remote Sensing Technology.

• 2005 April 12 12:00 - APSTAR 6 Launch Vehicle: CZ-3B. LC: LC2. Apogee: 49,629 km (30,837 mi). 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 - Zhongxing 22A Launch Vehicle: CZ-3A. Apogee: 35,817 km (22,255 mi). 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 - Xinnuo 2 Launch Vehicle: CZ-3B. Apogee: 35,911 km (22,314 mi). 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 - FY 2D Launch Vehicle: CZ-3A. Apogee: 35,789 km (22,238 mi). 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 January 11 22:28 - Chinese ASAT destroys FY-1C target satellite. Launch Vehicle: DF-21. Apogee: 850 km (520 mi). The FY-1C satellite, launched on 10 May 1999, was presumably well past the end of its operational life. It was destroyed in a test of a Chinese ASAT weapon at an altitude of 850 km, 4 degrees west of Xichang. Launch vehicle was unknown, but a version of the DF-21 IRBM would be sufficient to reach that altitude. Reportedly the flight had been preceded by one to three earlier tests that were either failures or just aimed at a point in space. The program was apparently very secret, and the Chinese foreign ministry was caught by surprise by the test and the storm of international condemnation that followed. The FY-1C was blown into over 200 pieces of debris, adding immediately by 10% to the population of space junk that threatens lower-altitude satellites.

• 2007 February 2 16:28 - Beidou 2A Launch Vehicle: CZ-3A. Apogee: 36,248 km (22,523 mi). Fourth Beidou satellite. It did not reach geostationary orbit until early April following deployment problems with its solar panels and reports of US detection of a debris cloud at the time of the original expected apogee firing.

• 2007 April 12 20:11 - Beidou 5 Launch Vehicle: CZ-3A. Apogee: 21,544 km (13,386 mi). The fifth Beidou satellite, but the first in the 12-hour, 55 deg inclination MEO portion of the constellation. All previous launches had been to populate the geostationary portion of the system.

• 2007 May 13 16:01 - Nigcomsat 1 Launch Vehicle: CZ-3B. Apogee: 35,789 km (22,238 mi). Second DFH-4 communications satellite; China's first commercial payload sale, and Nigeria's first commercial communications satellite. Positioned at 42.5 deg E. Payload consisted of 4 C-band, 14 Ku-band, 8 Ka-band, and 2 L-band transponders. The antenna subsystem consisted of seven antennas.

• 2007 May 31 16:08 - Sinosat 3 Launch Vehicle: CZ-3A. Apogee: 35,793 km (22,240 mi). Chinese C-band domestic communications satellite, launched as part of a campaign to prepare for the 2008 Olympic Games, and to compensate for failure of the first DFH-4 satellite.

• 2007 July 5 12:08 - Chinasat 6B Launch Vehicle: CZ-3B. Apogee: 49,722 km (30,895 mi). Direct broadcast satellite, capable of transmitting 300 television channels using 38 transponders. To be positioned at 115.5 deg E, beaming signals to China, Southeast Asia, and Oceania. Planned mission life 15 years.

• 2007 October 24 10:05 - Chang'e-1 Launch Vehicle: CZ-3A. Apogee: 50,182 km (31,181 mi). China's first unmanned lunar/planetary probe. The initial orbit of 221 x 50,602 km x 31.0 deg was raised to a translunar trajectory in a serious of spacecraft engine burns over the next 24 hours.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Official Site of the Topic, Information obtained from the manufacturer or operator's official web site.