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CZ-2F Space Launch Vehicles

In 1992, with the approval of the Central Committee of the Chinese Communist Party, China began the development of piloted space-travel technology. The CZ-2F represents a modest extension of the existing CZ-2E with a 2-stage core vehicle and four strap-on stages, all employing UDMH and nitrogen tetroxide. The CZ-2F was designed to support the Chinese piloted spaceflight effort, with an initial launch in Novmbers 1999.

In June 1999 images purporting to be those of a version of China's Long March booster capable of launching a piloted spacecraft were made public. While some "enhancement" may have taken place, there is evidently considerable basis in truth of these images of the Long March 2F.

LM-2F (China)

[preliminary data, based on LM-2E]
Background Information
First Launch:
November 1999
Flight Rate:
1-3 per year
Launch Site:
Xichang Space Launch Center, China
Capability:
19,400 lb to LEO; 7,430 lb to GTO

History

  • Chinese rocket program started in the late 1950s
  • Evolved from Chinese surface-to-surface series IRBMs
  • LM-2E is enhanced version of the LM-2

Description

  • Two-stage vehicle with four strap-on boosters
  • Stage 1 consists of four YF-20B motors that burn UDMH/N2O4, providing 665,800 lb of total thrust
  • Stage 2 uses one YF-22B engine and four YF-23B verniers burning UDMH/N2O4, generating a total thrust of 177,200 lb
  • Each strap-on booster uses a single YF-20B liquid engine, generating 166,450 lb of thrust each

Profile

Length:
49.7 meters
Launch Weight:
460,000 kg
Diameter:
3.35 meters
Liftoff Thrust:
1,331,600 lb
Payload Fairing:
39.2 ft x 13.8 ft

Sources and Resources

"The Aerospace Industry of China" China Pictorial #3, 2000

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