Search
 

 

LM - 2D Launch Vehicle

* History

LM-2D is a 2-stage liquid propellant launch vehicle developed on the basis of the 1st and 2nd stage of LM-4, especially dedicated for launching different spacecraft for LEO missions.

Its launch capability for LEO mission is 3,700 kg. There are two kinds of fairing available for LM-2D --Type A and B. The static envelope diameter of Type A is 2,900 mm, for Type B is 3,350 mm. As of today, three China's recoverable satellites have been successfully launched by LM-2D.

Technical Data:

  1stStage 2ndStage 3rdStage
Diameter(m) 3.35 3.35  
Mass of propellant(t) 182.07 35.408  
Propellant N2O4/UDMH  
Engine DaYF-21B YF-22B (Main)  
Engine Thrust (KN) 2250 742 (Main)
46.1 (Vernier)		  
Engine Specific Impulse
(NĄ¤Sec / kg)		 2961.6 2910 (Main)
2672 (Vernier)		  
Lift-off Mass(t) 232.7
Overall Length (m) 37.73
Fairing Diameter (m) 2.90/3.35

Launch Record:

As of December 2004
No. Launch Vehicle Launch Date Payload Mission Launch Center Result
01 LM-2D F01 Sept.08, 1992 FHW Satellite* LEO JSLC** Success
02 LM-2D F02 Mar.07, 1994 FHW Satellite LEO JSLC Success
03 LM-2D F03 Jan.20, 1996 FHW Satellite LEO JSLC Success

04

LM-2DF04

Nov.03, 2003

FHW

LEO

JSLC

Success

05

LM-2DF05

Sept.27, 2004

FHW

LEO

JSLC

Success

Note:
* China's recoverable satellites
** Jiuquan Satellite Launch Center

 

LM- 2C/CTS Launch Vehicle LM- 2D Launch Vehicle LM- 2E Launch Vehicle
LM- 3A Launch Vehicle LM- 3B Launch Vehicle LM- 4 Launch Vehicle