CZ-2E Media Gallery

The CZ-2E added four liquid rocket booster strap-ons to the basic CZ-2 core to achieve a low earth orbit payload capability approaching the Russian Proton, US Titan, or European Ariane rockets. The Long March 2E had a maximum payload capability of 9,500 kg to low earth orbit.

The CZ-2E was based on the mature technology of previous versions of the Long March launch vehicles. Wang Uongzhi was the Chief Designer for the vehicle. With a solid Perigee Kick Motor (EPKM, built by Hexi Company, China), the CZ-2E could put 3,500 kg into a geosynchronous transfer orbit. In May 2001 it was announced that another upper stage, the ETS was being developed for the CZ-2E. This would be an adaptation of the CTS of the CZ-2C, consisting of a Spacecraft Adapter and an Orbital Maneuver System.

Launch event sequence:

 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

Manufacturer: CALT. Launches: 7. Failures: 2. Success Rate: 71.43%. First Launch Date: 1990-07-16. Last Launch Date: 1995-12-28. Launch data is: continuing. 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.

• 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-2E-1. Gross Mass: 196,500 kg (433,200 lb). Empty Mass: 9,500 kg (20,900 lb). Thrust (vac): 3,265.143 kN (734,033 lbf). Isp: 289 sec. Burn time: 166 sec. Isp(sl): 261 sec. Diameter: 3.35 m (10.99 ft). Span: 6.00 m (19.60 ft). Length: 23.70 m (77.70 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: YF-20B. Other designations: L-180. Status: In production.

• Stage Number: 2. 1 x Stage: CZ-2E-2. Gross Mass: 91,500 kg (201,700 lb). Empty Mass: 5,500 kg (12,100 lb). Thrust (vac): 831.005 kN (186,817 lbf). Isp: 298 sec. Burn time: 295 sec. Isp(sl): 260 sec. Diameter: 3.35 m (10.99 ft). Span: 3.35 m (10.99 ft). Length: 15.52 m (50.91 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: YF-25/23. Other designations: L-90. Status: In production.

• Stage Number: 3. 1 x Stage: EPKM. Gross Mass: 5,985 kg (13,194 lb). Empty Mass: 541 kg (1,192 lb). Thrust (vac): 117.000 kN (26,302 lbf). Isp: 298 sec. Burn time: 135 sec. Diameter: 1.70 m (5.50 ft). Span: 2.50 m (8.20 ft). Length: 3.10 m (10.10 ft). Propellants: Solid. No Engines: 1. Engine: EPKM. Status: Out of production. Perigee kick motor for putting CZ-2E payloads into geosynchronous transfer orbit. Thrust, burn time estimated. Specific impulse calculated based on motor payload/delta v performance and masses.

1990 July 16 - 00:40 GMT - Launch Site: Xichang. Launch Complex: LC2. Launch Pad: LC2. Launch Vehicle: CZ-2E. Model: Chang Zheng 2E. LV Configuration: Chang Zheng 2E CZ2E-1 (23).

• Badr-A Nation: Pakistan. Payload: Badr 1 + R&D. Mass: 52 kg (114 lb). Class: Technology. Type: Comsat. Spacecraft: Badr. Agency: Suparco. Perigee: 208 km (129 mi). Apogee: 988 km (613 mi). Inclination: 28.50 deg. Period: 96.70 min. COSPAR: 1990-059A. USAF Sat Cat: 20685. Decay Date: 1990-12-08. First launch of new Chinese launch vehicle. Experimental Pakistani payload. References: 1, 2, 5, 6.

• HS-601 Model Nation: China. Agency: PRC. COSPAR: 1990-059xx. First launch of new Chinese launch vehicle. References: 279.

• Optus B1 Nation: Australia. Program: Aussat. Payload: Aussat B1. Mass: 2,760 kg (6,080 lb). Class: Communications. 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. COSPAR: 1992-054A. USAF Sat Cat: 22087. 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.References: 1, 2, 5, 6.

• Aussat B2 / Optus B2 Nation: Australia. Program: Aussat. Payload: Optus B2 / Star 63F. Mass: 2,760 kg (6,080 lb). Class: Communications. Spacecraft: HS 601. Agency: Hughes. Perigee: 206 km (128 mi). Apogee: 816 km (507 mi). Inclination: 28.10 deg. Period: 94.90 min. COSPAR: 1992-090A. USAF Sat Cat: 22278. Decay Date: 1995-06-29. 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. References: 1, 2, 5, 6.

• Optus B3 Nation: Australia. Program: Aussat. Mass: 2,760 kg (6,080 lb). Class: Communications. 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. COSPAR: 1994-055A. USAF Sat Cat: 23227. 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.References: 2, 5, 6.

• Apstar 2 Nation: China. Program: Apstar. Class: Communications. Spacecraft: HS 601. Agency: PRC. COSPAR: F950125A. Decay Date: 1995-01-25. 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.References: 5.

• Asiasat 2 Nation: China. Program: Asiasat. Mass: 3,485 kg (7,683 lb). Class: Communications. Spacecraft: AS 7000. Agency: Asiasat. Manufacturer: Lockheed Martin. Perigee: 35,777 km (22,230 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.40 deg. Period: 1,436.20 min. COSPAR: 1995-064A. USAF Sat Cat: 23723. 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.References: 2, 5, 6.

• Echostar 1 Nation: USA. Program: Echostar. Mass: 3,288 kg (7,248 lb). Class: Communications. Spacecraft: AS 7000. Agency: TCI. Manufacturer: Lockheed Martin. Perigee: 35,777 km (22,230 mi). Apogee: 35,796 km (22,242 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 1995-073A. USAF Sat Cat: 23754. 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.References: 2, 5, 6.

• 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...