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CZ-2E[A] Space Launch Vehicle

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. In February 1999 the China Great Wall Company announced that the rocket would be available in 2000 and be launched from the Jiuquan Satellite Launch Center in the northwest part of China. As of 2013 this vehicle had not flown.

LM-2E[A]

Background Information First Launch: October 1999 Flight Rate: 1-3 per year Launch Site: Xichang Space Launch Center, China Capability: 12,000 kg to LEO 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 pair of YF-20B liquid engines, generating 166,450 lb of thrust each Profile Length: ft Launch Weight: lb Diameter: 11 ft Liftoff Thrust: 2,000,000 lb Payload Fairing: ft x ft