References

LM-2C USER'S MANUAL - CALT PROPRIETARY - Issue 1999
LM-2C Launch Vehicle @ CALT
Space Launch Vehicles Secretary of the Air Force Acquisition - Space Programs Directorate
Adapted from: Europe and Asia in Space 1993-1994, Nicholas Johnson and David Rodvold [Kaman Sciences / Air Force Phillips Laboratory]
158. LM-2C Launch Vehicle, specification sheet distributed by China Great Wall Industry Corp., 1992.
159. Zhao Bing, "A System Analysis of the Launch Vehicle Technology in China", Paper 92-824, 43rd Congress of the International Astronautical Federation, August-September 1992.
160. China In Space, China Great Wall Industry Corp., 1988.
161. Space in China. Launch Services and Space Technology, China Great Wall Industry Corp., 1989.
162. Xu Jian, Progress in Carrier Rocket Technology", Beijing Review, 3-9 September 1990, pp. 27-30.
163. G. Pike, "Chinese Launch Services, A User's Guide", Space Policy, May 1991, pp.103-115.
164. Long March Launch System, Ministry of Astronautics, 1985.
165. P. S. Clark, Chinese Launch Vehicles - Chang Zheng 2", Jane's Intelligence Review, May 1992, pp.231-234.
166. P. S. Clark, "Chinese Launch Vehicles - The Rest of the Story", Jane's Intelligence Review, October 1990, pp. 469-473.

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:

Diameter:

meters

Liftoff Thrust:

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

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