Find a Security Clearance Job!

Space


CZ-2C/CTS Long March Space Launch Vehicles

10-9-09

CZ-2C/CTS

Another variant of the Chinese CZ-2C launch vehicle was revealed in May 2001 when it was announced that the Double Star and KOMPSAT-2 satellites would be launched by a CZ-2C with a CTS upper stage. This was apparently a further development of the CZ-2C/SD that was adapter to the top of the second stage cone shaped adapter mounting. The CTS third stage was a three-axis stabilized upper stage consisting of a spacecraft adapter, a structural ring with cross struts payload supports with instrumentation platform areas and an Orbital Maneuver System. The primary propulsion system solid motor of the CTS dispenser stage makes it capable of putting 1,400 kg of payload into a 900 km sun-synchronous orbit. The first launch of this booster configuration took place on December 29, 2003 and was followed with its second flight on July 25, 2004 . No further launches of this booster configuration have been identified unless PRC Chinese authorities have changed the launch vehicles designation. Both demonstrated a 100% success rate. One was launched from the Xichang (XSLC) and the other was launched from the Taiyuan (TSLC) Satellite Launch Centers infrastructure. The CZ-2C is derived from the CSS-4 ballistic missile and consists of two stages.

For Further information on the Chinese launch vehicle CZ-2C/SD see: http://www.globalsecurity.org/space/world/china/cz-2csd.htm

 

LM-2C/CTS

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

1 st

2 nd

SD/CTS dispenser stage

Mass of Propellant (t)

143

55

125kg

Propellant

N 2O 4/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

 

 



NEWSLETTER
Join the GlobalSecurity.org mailing list