UNITED24 - Make a charitable donation in support of Ukraine!

Space


CZ-2D Space Launch Vehicle

The Long March 2D is a two-stage launch vehicle with storable propellant, suitable for launching a variety of LEO satellites. Developed and manufactured by the Shanghai Academy of Spaceflight Technology, the LM-2D has a typical payload capability of 3,500kg for a 200km×200km LEO. The CZ-2D is essentially a two stage version of the CZ-4 with a LEO payload capacity in excess of three metric tons. Its 1st stage is identical to that of the LM-4 and the second stage is essentially the same as that of the LM-4, except for the recently improved vehicle equipment bay.

The third CZ-2 variant, the CZ-2D, appeared with little forewarning on 9 August 1992 in conjunction with the maiden flight of the FSW-2 spacecraft. On August 9, 1992, the maiden flight of the LM-2D successfully sent one of China's new generation of recoverable satellites into orbit. On July 3, 1994, the LM-2D successfully launched another FSW-2 recoverable satellite from the Jiuquan Satellite Launch Center and on October 20, 1996, the LM-2D made its third flight, orbiting a recoverable satellite with a total success.

LM-2D

Background Information
First Launch:
August 1992
Flight Rate:
2-3 per year
Launch Site:
Xichang Space Launch Center, China
Capability:
2,750 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

  • Three-stage liquid fueled vehicle (including PAM-D upper stage)
  • Stage 1 consists of four YF-20 motors burning UDMH/N2O4 providing a total thrust of 626,000 lb
  • Stage 2 uses one YF-22 engine and four YF-23 verniers burning UDMH/N2O4 for a total thrust of 171,300 lb
  • Stage 3 is a McDonnell Douglas PAM-D upper stage providing 66,700 lb of thrust

Profile

Length:
131 ft
Launch Weight:
421,000 lb
Diameter:
11 ft
Liftoff Thrust:
626,000 lb
Payload Fairing:
31.0 ft x 11.0 ft

Stage

1st

2nd

Mass of Propellant (t)

181

38

Propellant

N2O4/UDMH

Engine

YF-21B

DaFY-20

Engine Trust (kN)

2962

742 (Main) 46.1(Vernier)

Engine Specific Impulse (N.Sec/kg)

2550

2910 (Main) 2762 (Vernier)

Diameter (m)

3.35

Lift-off Mass (t)

233

Overall Length (m)

37.728(for Type-A Fairing) 41.303(for Type-B Fairing)

Fairing Diameter (m)

2.90(Type-A) 3.35(Type-B)




NEWSLETTER
Join the GlobalSecurity.org mailing list



 
Page last modified: 21-07-2011 00:50:06 ZULU