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CZ-2E[A] Space Launch Vehicles

The CZ-2E[A] represents an extension of the existing CZ-2E with stretched strap-on boosters and an enlarge payload shroud. The booster consists of a 2-stage core vehicle with four lengthened strap-on stages, all employing UDMH and nitrogen tetroxide. The strap-on stages each use two YF-20B engines, versus the single YF-20B engine used on the CZ-2E. Four YF20B engines are combined to make the YF-21B which powers the first stage of the core vehicle, which is largely unchanged from the CZ-2E first stage. The CZ-2E[A] second stage is also based on its CZ-2C counterpart with an uprated main engine (YF-22B) and larger propellant tanks carrying more than twice the load of the CZ-2C second stages. The CZ-2E[A] has a 12 metric ton LEO capacity.

The large low Earth orbit payload of this launch vehicle indicates that it is probably intended to support the Chinese piloted spaceflight effort, possibly to launch a small space station.

LM-2E[A] (China)

Background Information
First Launch:
October 1999
Flight Rate:
1-3 per year
Launch Site:
Xichang Space Launch Center, China
12,000 kg to LEO


  • 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


  • 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 pair of YF-20B liquid engines, generating 166,450 lb of thrust each


Launch Weight:
11 ft
Liftoff Thrust:
2,000,000 lb
Payload Fairing:
ft x ft

Sources and Resources

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Updated Thursday, November 18, 1999 8:41:53 AM