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Space


CZ-2C/SD Space Launch Vehicle

In order to meet the dual launch requirement for the Motorola IRIDIUM mobile satellite telecommunication network, whose primary, CALT developed the LM-2C/SD, a LM-2C with a newly-designed upper stage, the Smart Dispenser (SD). The main differences between an LM-2C and an LM-2C/SD include a modified fairing with a diameter of 3.35m, a newly developed Smart Dispenser third stage fuel and oxidizer tanks, and a second stage larger engines with larger nozzles. The payload fairing of the LM-2C/SD consists of nose dome, forward cone section and cylindrical section. The nose dome is made of non-metallic RF-transparent material. The cylindrical section and the forward cone section are of metallic honeycomb structure. LM-2C/SD launch vehicle sends the SD into an initial elliptical parking orbit, and at initial apogee the Dispenser's SRM (Solid Rocket Motor) fires to place the combination into a circular orbit.

On April 28, 1993, CGWIC and Motorola signed a launch services contract for multiple launch of Iridium communications satellites using LM-2C/SD launch vehicles. Each LM-2C/SD has the capacity of delivering two Iridium system satellite into the designated orbit.

Iridium was the anchor customer for the CZ-2C/SD. The LM-2C/SD demonstration launch was conducted with a total success from the Taiyuan satellite Launch Center on September 1, 1997. The first three deployment launches for the Iridium program were successfully conducted on December 8, 1997, March 26, 1998 and May 2, 1998.

LM-2C/SD

Background Information
First Launch:
July 1975
Flight Rate:
2-3 per year
Launch Site:
Jiuquan
Capability:
1,650 lb Sun-synchronous
2,640 - 4,400 lb to LEO

History

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

Description

  • Two-stage vehicle (AKMs available)
  • Stage 1 consists of four YF-20 motors that burn UDMH/N2O4 providing 625,800 lb of total thrust
  • Stage 2 uses one YF-22 engine that burns UDMH/N2O4 providing 171,200 lb of thrust

Profile

Length:
40 meters
Launch Weight:
kg
Diameter:
meters
Liftoff Thrust:
kN
Payload Fairing:
5.061 meters X 3.35 meters diameter


Stage

1st

2nd

SD

Mass of Propellant (t)

143

55

125kg

Propellant

N2O4/UDMH

HTPB

Engine

YF-21 (4xYF-20)

YF22(main) YF23(Vernier)

Solid rocket motor

Engine Trust (kN)

2962

742 (Main) 47(Vernier)

10.780

Engine Specific Impulse (N.Sec/kg)

2550

2991 (Main) 2834(Vernier)

2822.4

Diameter (m)

3.35

2.70

Lift-off Mass (t)

213

Overall Length (m)

39.925

Fairing Diameter (m)

3.35




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