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Space


CZ-1D Space Launch Vehicle

To satisfy the need for launching small satellites into LEO, the PRC developed the CZ-1D launch vehicle. The CZ-1D design consists of a 2-stage vehicle with the first stage burning UDMH and nitric acid whereas the second stage utilizes UDMH and nitrogen tetroxide. The LM-1D is a 3-stage rocket derived from the 1970 LM-1. It is actually a 2-stage DF-4 surmounted by a solid-fuel stage containing 0.625 t of fuel. Although slightly smaller than the LM-1, its performance is better. The payload capacity of the CZ-1D is 900 kg to LEO and 300 kg to a sun-synchronous orbit (References 159-161, 191-192).

LM-1D

Background Information
First Launch:
1991
Flight Rate:
2-3 per year
Launch Site:
Jiuquan Space Launch Center, China
Capability:
900 kg to LEO

History

  • Chinese rocket program started in the late 1950s
  • Evolved from Chinese surface-to-surface series IRBMs
  • CZ-1D is enhanced version of the CZ-1

Description

    Three-stage liquid fueled vehicle (including PAM-D upper stage)
  • Stage 1 consists of one YF-2A motor with four thrust chambers motors burning UDMH/N2O4
  • Stage 2 uses one YF-3 motor with two thrust chambers motors burning UDMH/N2O4

Profile

Length:
28.2 meters
Launch Weight:
79,400 kg
Diameter:
2.25 meters
Liftoff Thrust:
1,093 kiloNewtons
Payload Fairing:
4.82 meters x 2.05 meters




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