Encyclopedia Astronautica
CZ-2E



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CZ-2E
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CZ-2E
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CZ-2E
Credit: © Mark Wade
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LM-2E
Launch photo of Long March LM-2E launch vehicle.
Chinese orbital launch vehicle. 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

LEO Payload: 9,200 kg (20,200 lb) to a 200 km orbit at 28.00 degrees. Payload: 3,370 kg (7,420 lb) to a GTO with solid kick stage.. Failures: 2. First Fail Date: 1992-12-21. Last Fail Date: 1995-01-25. Launch Price $: 50.000 million in 1999 dollars.

Stage Data - CZ-2E

  • Stage 0. 4 x 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 1. 1 x 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 2. 1 x 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 3. 1 x 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: In Production. Comments: 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.

AKA: Long March 2E; Chang Zheng 2E; Chang Zheng-2E.
Status: Retired 1995.
Gross mass: 460,000 kg (1,010,000 lb).
Payload: 9,200 kg (20,200 lb).
Height: 49.70 m (163.00 ft).
Diameter: 3.35 m (10.99 ft).
Thrust: 5,920.00 kN (1,330,860 lbf).
Apogee: 200 km (120 mi).
First Launch: 1990.07.16.
Last Launch: 1995.12.28.
Number: 7 .

More... - Chronology...


Associated Countries
Associated Spacecraft
  • HS 601 American communications satellite bus. First launch 1990.01.09. 3-axis unified ARC 22 N and one Marquardt 490 N bipropellant thrusters, Sun and Barnes Earth sensors and two 61 Nms 2-axis gimbaled momentum bias wheels. More...
  • Badr Pakistani communications technology satellite. 3 launches, 1990.07.16 (Badr-A) to 2008.07.07 (Badr B). Pakistani experimental series with a variety of payloads. More...
  • AS 7000 American communications satellite. 13 launches, 1993.12.16 (Telstar 401) to 1998.06.18 (Intelsat 805). 3-axis stabilized. Two large solar panels with 1-axis articulation. More...

Associated Engines
  • Perigee Orbit Transfer Motor Fourth Academy solid rocket engine. 222.840 kN. In Production. Isp=280s. Basic perigee kick motor for CZ-2E launch vehicle. Featured glass fibre-wound case, HTPB propellant, 3-D finocyl propellant grain, and carbon/carbon throat insert. First flight 1990. More...
  • YF-20B Beijing Wan Yuan N2O4/UDMH rocket engine. 816.3 kN. In production. Isp=289s. Boosted CZ-2C, CZ-2D, CZ-2E, CZ-2E(A), CZ-3A, CZ-3B, CZ-3C, CZ-4A. First flight 1988. More...
  • YF-25/23 Beijing Wan Yuan N2O4/UDMH rocket engine. 831 kN. In production. Cluster of YF-25 and 4 x YF-23 verniers. Isp=295s. First stage engine for CZ-2D, CZ-2E, CZ-2E(A), CZ-3A, CZ-3B, CZ-3C, CZ-4A. First flight 1988. More...

See also
  • CZ China's first ICBM, the DF-5, first flew in 1971. It was a two-stage storable-propellant rocket in the same class as the American Titan, the Russian R-36, or the European Ariane. The DF-5 spawned a long series of Long March ("Chang Zheng") CZ-2, CZ-3, and CZ-4 launch vehicles. These used cryogenic engines for upper stages and liquid-propellant strap-on motors to create a family of 12 Long-March rocket configurations capable of placing up to 9,200 kg into orbit. In 2000 China began development of a new generation of expendable launch vehicles using non-toxic, high-performance propellants with supposedly lower operating costs. However these encountered development delays, and it seemed the reliable Long March series of rockets would continue in operational use for nearly fifty years before being replaced. More...

Associated Manufacturers and Agencies
  • CALT Chinese manufacturer of rockets, spacecraft, and rocket engines. China Academy of Launch Vehicle Technology, Beijing, China. More...

Associated Programs
  • Asiasat AsiaSat is a wholly owned subsidiary of Asia Satellite Telecommunications Holdings Ltd., a company listed on both the Hong Kong (SEHK: 1135HK) and New York (NYSE: SAT) stock exchanges. AsiaSat's two major shareholders are China International Trust and Investment Corporation (CITIC) and Société Européene des Satellites (SES), the operator of EuropeÌs premier ASTRA satellite system. More...

Associated Launch Sites
  • Xichang 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 kilometers away. Xichang Airport is 50 km away. A dedicated railway and highway lead directly to the launch site. More...

Associated Stages
  • CZ-2E-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 196,500/9,500 kg. Thrust 3,265.14 kN. Vacuum specific impulse 289 seconds. More...
  • CZ-2E-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 91,500/5,500 kg. Thrust 831.01 kN. Vacuum specific impulse 298 seconds. More...
  • EPKM Solid propellant rocket stage. Loaded/empty mass 5,985/541 kg. Thrust 117.00 kN. Vacuum specific impulse 298 seconds. 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. More...
  • LB-40 N2O4/UDMH propellant rocket stage. Loaded/empty mass 41,000/3,200 kg. Thrust 816.29 kN. Vacuum specific impulse 291 seconds. More...

CZ-2E Chronology


1990 July 16 - . 00:40 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-2E. LV Configuration: Chang Zheng 2E CZ2E-1 (23).
  • Badr-A - . Payload: Badr 1 + R&D. Mass: 52 kg (114 lb). Nation: Pakistan. Agency: Suparco. Class: Technology. Type: Communications technology satellite. Spacecraft: Badr. Decay Date: 1990-12-08 . USAF Sat Cat: 20685 . COSPAR: 1990-059A. Apogee: 988 km (613 mi). Perigee: 208 km (129 mi). Inclination: 28.5000 deg. Period: 96.70 min. Summary: First launch of new Chinese launch vehicle. Experimental Pakistani payload..
  • HS-601 Model - . Nation: China. Agency: PRC. COSPAR: 1990-059xx. Summary: First launch of new Chinese launch vehicle..

1992 August 13 - . 23:00 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-2E. LV Configuration: Chang Zheng 2E CZ2E-2 (28).
  • Optus B1 - . Payload: Aussat B1. Mass: 2,760 kg (6,080 lb). Nation: Australia. Agency: Optus. Program: Aussat. Class: Communications. Type: Military communications satellite. Spacecraft: HS 601. USAF Sat Cat: 22087 . COSPAR: 1992-054A. Apogee: 35,800 km (22,200 mi). Perigee: 35,774 km (22,228 mi). Inclination: 0.0000 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 Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-2E. LV Configuration: 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.. Failed Stage: G.
  • Aussat B2 / Optus B2 - . Payload: Optus B2 / Star 63F. Mass: 2,760 kg (6,080 lb). Nation: Australia. Agency: Hughes. Program: Aussat. Class: Communications. Type: Military communications satellite. Spacecraft: HS 601. Decay Date: 1995-06-29 . USAF Sat Cat: 22278 . COSPAR: 1992-090A. Apogee: 816 km (507 mi). Perigee: 206 km (128 mi). Inclination: 28.1000 deg. Period: 94.90 min. Summary: 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 August 27 - . 23:10 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-2E. LV Configuration: Chang Zheng 2E CZ2E-4 (35).
  • Optus B3 - . Mass: 2,760 kg (6,080 lb). Nation: Australia. Agency: Optus. Program: Aussat. Class: Communications. Type: Military communications satellite. Spacecraft: HS 601. USAF Sat Cat: 23227 . COSPAR: 1994-055A. Apogee: 35,855 km (22,279 mi). Perigee: 35,718 km (22,194 mi). Inclination: 0.0000 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.

1995 January 25 - . 22:40 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-2E. LV Configuration: 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.. Failed Stage: G.
  • Apstar 2 - . Nation: China. Agency: PRC. Program: Apstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. Decay Date: 1995-01-25 . COSPAR: F950125A. 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 Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-2E. LV Configuration: Chang Zheng 2E CZ2E-6 (38).
  • Asiasat 2 - . Mass: 3,485 kg (7,683 lb). Nation: China. Agency: Asiasat. Manufacturer: Lockheed. Program: Asiasat. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 7000. USAF Sat Cat: 23723 . COSPAR: 1995-064A. Apogee: 35,798 km (22,243 mi). Perigee: 35,777 km (22,230 mi). Inclination: 0.4000 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 Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-2E. LV Configuration: Chang Zheng 2E CZ2E-7 (39).
  • Echostar 1 - . Mass: 3,288 kg (7,248 lb). Nation: USA. Agency: TCI. Manufacturer: Lockheed. Program: Echostar. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 7000. USAF Sat Cat: 23754 . COSPAR: 1995-073A. Apogee: 35,796 km (22,242 mi). Perigee: 35,777 km (22,230 mi). Inclination: 0.0000 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.

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