CZ-2E - 7,115 bytes. 112 x 423 pixels.

Largest Chinese launch vehicle, using four liquid rocket booster strap-ons to reach LEO payload capabilities approaching the Russian Proton, US Titan, or European Ariane rockets. The Long March 2E had a maximum payload capability of 9,500 kg. The CZ-2E was based on the mature technology of previous versions of Long March launch vehicles. 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. 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

Launches: 7. Failures: 2. Success Rate: 71.43% pct. First Launch Date: 16 July 1990. Last Launch Date: 28 December 1995. LEO Payload: 9,200 kg. to: 200 km Orbit. at: 28.0 degrees. Payload: 3,370 kg. to a: Geosynchronous transfer with solid kick stage. trajectory. Liftoff Thrust: 604,000 kgf. Total Mass: 460,000 kg. Core Diameter: 3.4 m. Total Length: 49.7 m. Launch Price $: 50.00 million. in 1999 price dollars.

• Stage Number: 0. 4 x CZ-2E-0 Gross Mass: 41,000 kg. Empty Mass: 3,200 kg. Thrust (vac): 83,238 kgf. Isp: 291 sec. Burn time: 128 sec. Isp(sl): 261 sec. Diameter: 2.3 m. Span: 2.3 m. Length: 15.3 m. Propellants: N2O4/UDMH No Engines: 1. YF-20B

• Stage Number: 1. 1 x CZ-2E-1 Gross Mass: 196,500 kg. Empty Mass: 9,500 kg. Thrust (vac): 332,952 kgf. Isp: 289 sec. Burn time: 166 sec. Isp(sl): 261 sec. Diameter: 3.4 m. Span: 6.0 m. Length: 23.7 m. Propellants: N2O4/UDMH No Engines: 4. YF-20B

• Stage Number: 2. 1 x CZ-2E-2 Gross Mass: 91,500 kg. Empty Mass: 5,500 kg. Thrust (vac): 84,739 kgf. Isp: 298 sec. Burn time: 295 sec. Isp(sl): 260 sec. Diameter: 3.4 m. Span: 3.4 m. Length: 15.5 m. Propellants: N2O4/UDMH No Engines: 1. YF-25/23

• Stage Number: 3. 1 x EPKM Gross Mass: 5,985 kg. Empty Mass: 541 kg. Thrust (vac): 12,000 kgf. Isp: 298 sec. Burn time: 135 sec. Diameter: 1.7 m. Span: 2.5 m. Length: 3.1 m. Propellants: Solid No Engines: 1. EPKM

• Badr-A Spacecraft: Badr. Payload: Badr 1 + R&D. Mass: 52 kg.

  First launch of new Chinese L/V; experimental Pakistani payload.

• HS-601 Model Spacecraft: Badr.

• Optus B1 Spacecraft: HS 601. Payload: Aussat B1. Mass: 2,760 kg.

  Stationed at 160 deg E. Commercial communications. Longitude 160 +/- 0.05 deg E. Launched fromn China.

  ---

  CZ-2E Credit: © Mark Wade. 1,845 bytes. 72 x 481 pixels.

  ---

• Aussat B2 / Optus B2 Spacecraft: HS 601. Payload: Optus B2 / Star 63F. Mass: 2,760 kg.

  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.

• Optus B3 Spacecraft: HS 601. Mass: 2,760 kg.

  Telephone; TV; mobile communications; air traffic control. Stationed at 156 deg deg E.

• Apstar 2 Spacecraft: HS 601.

  ---

  LM-2E - Launch photo of Long March LM-2E launch vehicle. 14,336 bytes. 169 x 331 pixels.

  ---

  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.

• Asiasat 2 Spacecraft: AS 7000. Mass: 3,485 kg.

  TV; 24 C-band and 9 Ku-band transponders. Stationed at 100.5 deg E.

• Echostar 1 Spacecraft: AS 7000. Mass: 3,288 kg.

  16 Ku-band transponders. Stationed at 119 deg W.

• 42 - Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991.
• 61 - Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al.