CZ-3B
CZ-3B
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Orbital launch vehicle. Year: 1996. Family: Long March. Country: China. Status: In production. Other Designations: Long March 3B. Manufacturer's Designation: Chang Zheng-3B.

The Long March 3B was the most powerful Long March launch vehicle. It could inject a 5,000 kg payload into geosynchronous transfer orbit. The CZ-3B was developed on the basis of the CZ-3A, but had enlarged propellant tanks, larger fairing, and four boosters strapped onto the core stage. The CZ-3B boosters were identical to those of the CZ-3A.

Manufacturer: CALT. Launches: 8. Failures: 1. Success Rate: 87.50%. First Launch Date: 1996-02-14. Last Launch Date: 2007-05-13. Launch data is: continuing. 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.


Stage Data - CZ-3B
  • Stage Number: 0. 4 x Stage: CZ-2E-0. Gross Mass: 41,000 kg (90,000 lb). Empty Mass: 3,200 kg (7,000 lb). Thrust (vac): 816.285 kN (183,508 lbf). Isp: 291 sec. Burn time: 128 sec. Isp(sl): 261 sec. Diameter: 2.25 m (7.38 ft). Span: 2.26 m (7.41 ft). Length: 15.33 m (50.29 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: YF-20B. Other designations: LB-40. Status: In production.
  • Stage Number: 1. 1 x Stage: CZ-3A-1. Gross Mass: 179,000 kg (394,000 lb). Empty Mass: 9,000 kg (19,800 lb). Thrust (vac): 3,265.143 kN (734,033 lbf). Isp: 289 sec. Burn time: 155 sec. Isp(sl): 259 sec. Diameter: 3.35 m (10.99 ft). Span: 7.00 m (22.90 ft). Length: 23.08 m (75.72 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: YF-20B. Other designations: L-180. Status: Development ended 1997.
  • Stage Number: 2. 1 x Stage: CZ-2C/SD-2. Gross Mass: 55,000 kg (121,000 lb). Empty Mass: 5,000 kg (11,000 lb). Thrust (vac): 761.900 kN (171,282 lbf). Isp: 298 sec. Burn time: 190 sec. Isp(sl): 270 sec. Diameter: 3.35 m (10.99 ft). Span: 3.35 m (10.99 ft). Length: 10.00 m (32.00 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: YF-22A/23A. Other designations: L-35. Status: Out of production. Stretched version of CZ-2C second stage. Empty mass estimated.
  • Stage Number: 3. 1 x Stage: CZ-3A-3. Gross Mass: 21,000 kg (46,000 lb). Empty Mass: 2,800 kg (6,100 lb). Thrust (vac): 156.000 kN (35,070 lbf). Isp: 440 sec. Burn time: 470 sec. Diameter: 3.00 m (9.80 ft). Span: 3.00 m (9.80 ft). Length: 12.38 m (40.60 ft). Propellants: Lox/LH2. No Engines: 2. Engine: YF-75. Other designations: H-18. Status: Development ended 1997.

CZ-3B Chronology

1996 February 14 - 19:01 GMT - Launch Site: Xichang. Launch Complex: LC2. Launch Pad: LC2. Launch Vehicle: CZ-3B. Model: Chang Zheng 3B. LV Configuration: Chang Zheng 3B CZ3B-1 (40). FAILURE: Guidance failure resulted in launch vehicle crashing 22 seconds after launch, killing or injuring 59 people.

  • Intelsat 708 Nation: International. Program: Intelsat. Class: Communications. Spacecraft: FS-1300. Agency: PRC. COSPAR: F960214A. First attempted launch of a new version in the Long March family. Began to experience an anomaly in attitude about 2 seconds after launch, pitching down and yawing to the right. It augured in nose down at T+22 seconds and exploded violently, utterly destroying the launcher and its payload. The Chief-Designer of the launch vehicle organised an analysis team on the same day of the accident. Interpretation and analysis of the telemetered data indicated that the crash was caused by a change in the inertial reference. The explosion killed six and injured 57. Two of the killed were senior engineers with CASC.References: 4.
1997 August 19 - 17:50 GMT - Launch Site: Xichang. Launch Complex: LC2. Launch Pad: LC2. Launch Vehicle: CZ-3B. Model: Chang Zheng 3B. LV Configuration: Chang Zheng 3B CZ3B-2 (46).
  • Agila 2 Nation: Philippines. Payload: Mabuhay. Class: Communications. Spacecraft: FS-1300. Agency: MPSC. Manufacturer: Space Systems/Loral, Palo Alto. Perigee: 35,771 km (22,227 mi). Apogee: 35,803 km (22,246 mi). Inclination: 0.00 deg. Period: 1,436.20 min. COSPAR: 1997-042A. USAF Sat Cat: 24901. 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. References: 4.
1997 October 16 - 19:13 GMT - Launch Site: Xichang. Launch Complex: LC2. Launch Pad: LC2. Launch Vehicle: CZ-3B. Model: Chang Zheng 3B. LV Configuration: Chang Zheng 3B CZ3B-3 (48).
  • Apstar 2R Nation: China. Program: Apstar. Class: Communications. Spacecraft: FS-1300. Agency: APT. Manufacturer: Space Systems/Loral, Palo Alto. Perigee: 35,774 km (22,228 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 1997-062A. USAF Sat Cat: 25010. 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. References: 4.
1998 May 30 - 10:00 GMT - Launch Site: Xichang. Launch Complex: LC2. Launch Pad: LC2. Launch Vehicle: CZ-3B. Model: Chang Zheng 3B. LV Configuration: Chang Zheng 3B CZ3B-4 (52).
  • Zhongwei 1 Nation: China. Program: Chinastar. Class: Communications. Spacecraft: AS 2100. Agency: China Or. Manufacturer: Lockheed Martin, Sunnyvale (formerly Lockheed). Perigee: 35,777 km (22,230 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.10 deg. Period: 1,436.10 min. COSPAR: 1998-033A. USAF Sat Cat: 25354. Also known as Chinastar 1; comsat to serve China, India, Korea and Southeast Asia with 18 C-band and 20 Ku-band transponders. Operated by the China Orient Telecommunications Satellite Company, part of the Chinese telecommunications ministry. Zhongwei 1 and the CZ-3B's final liquid hydrogen upper stage were placed in an initial supersynchronous 216 x 85,035 km x 24.4 deg transfer orbit. Geostationary at 87.6 degrees E. Positioned in geosynchronous orbit at 87 deg E in 1998-1999 As of 6 September 2001 located at 87.49 deg E drifting at 0.013 deg W per day. As of 2007 Mar 11 located at 87.64E drifting at 0.010W degrees per day.
1998 July 18 - 09:20 GMT - Launch Site: Xichang. Launch Complex: LC2. Launch Pad: LC2. Launch Vehicle: CZ-3B. Model: Chang Zheng 3B. LV Configuration: Chang Zheng 3B CZ3B-5 (53).
  • Sinosat Nation: China. Program: Sinosat. Mass: 2,820 kg (6,210 lb). Class: Communications. Spacecraft: Spacebus 3000 . Agency: Eurasspa. Manufacturer: Alcatel, Cannes, France (was Aerospatiale). Perigee: 35,779 km (22,231 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.10 deg. Period: 1,436.10 min. COSPAR: 1998-044A. USAF Sat Cat: 25404. 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.
2005 April 12 - 12:00 GMT - Launch Site: Xichang. Launch Complex: LC2. Launch Pad: LC2. Launch Vehicle: CZ-3B.
  • APSTAR 6 Nation: China. Payload: Apstar 5B / Spacebus 4000C2. Mass: 4,680 kg (10,310 lb). Class: Communications. 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. COSPAR: 2005-012A. USAF Sat Cat: 28638. 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 October 28 - 16:20 GMT - Launch Site: Xichang. Launch Vehicle: CZ-3B.
  • Xinnuo 2 Nation: China. Payload: Sinosat-2. Class: Communications. 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. COSPAR: 2006-048A. USAF Sat Cat: 29516. 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.
2007 May 13 - 16:01 GMT - Launch Site: Xichang. Launch Vehicle: CZ-3B.
  • Nigcomsat 1 Nation: Nigeria. Mass: 5,150 kg (11,350 lb). Class: Communications. Spacecraft: DFH-4. Agency: Nigerian Communications Satellite Ltd. Perigee: 35,782 km (22,233 mi). Apogee: 35,789 km (22,238 mi). Inclination: 0.10 deg. Period: 1,436.10 min. COSPAR: 2007-018A. USAF Sat Cat: 31395. 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 July 5 - 12:08 GMT - Launch Site: Xichang. Launch Vehicle: CZ-3B.
  • Chinasat 6B Nation: China. Payload: Spacebus 4000C2. Mass: 4,600 kg (10,100 lb). Class: Communications. Spacecraft: Spacebus 4000. Agency: ChinaSatCom. Manufacturer: Thales Alenia Space. Perigee: 233 km (144 mi). Apogee: 49,722 km (30,895 mi). Inclination: 24.20 deg. Period: 920.90 min. COSPAR: 2007-031A. USAF Sat Cat: 31800. 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.

Bibliography and Further Reading
  • 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.
  • Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition). ISBN: 1563473534. Superseded by the later editions. More at amazon.com...
  • Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al. ISBN: 0710618107. The most comprehensive source of information for current space projects. Too expensive for human beings and most libraries. More at amazon.com...
 
 
 
 
 
 
 
 
 

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