LM-3A

The current page: Home -> Space Transportation

LM-3A

LM-3A is a 3-stage launch vehicle developed on the basis of LM-3 and LM- 2C. Its third stage is powered by cryogenic propellants --- liquid hydrogen and liquid oxygen. It is mainly usec for launching spacecraft with GTO mission. Its launch capability for GTO mission is 2,600 kg. The fairing static envelope is 3m in diameter.

Technical Data

Stage 1st Stage 2nd Stage 3rd Stage
Lift-off Mass (t) 241
Stage Propellant Mass (t) 171.775 30.752 18.193
Propellant N2O4/UDMH LOX/LH2
Engine YF-21C YF-24E
YF-22E (Main)
YF-23C (Vernier)
YF-75
Engine Thrust (KN) 2961.6 742 (Main)
11.8x4 (Vernier)
78.5x2
Engine Specific Impulse
(N.Sec/kg)
2556.5 2922.57 (Main)
2910.5 (Vernier)
4312
Booster 0
Overall Length (m) 52.52
Fairing Diameter (m) 3.35
Fairing Length (m) 8.887
GTO Launch Capability (kg) 2600
LM-3A
(as of April 1, 2010)

LM-3A Launch Record

No. Flight No. Launch Date Satellite Orbit Launch Center Result
1 F01 8 Feb. 1994 SJ-4/DP2* GTO XSLC** Success
2 F02 30 Nov. 1994 DFH-3*** GTO XSLC Success
3 F03 12 May 1997 DFH-3 GTO XSLC Success
4 F04 26 Jan. 2000 ChinaSat-22 GTO XSLC Success
5 F05 31 Oct. 2000 BD 1-01 GTO XSLC Success
6 F06 21 Dec. 2000 BD 1-02 GTO XSLC Successl
7 F07 25 May 2003 BD 1-03 GTO XSLC Success
8 F08 15 Nov. 2003 ChinaSat-20 GTO XSLC Success
9 F09 19 Oct. 2004 FY-2C GTO XSLC Success
10 F10 13 Sept. 2006 ChinaSat-22A GTO XSLC Success
11 F11 8 Dec. 2006 FY-2D GTO XSLC Success
12 F12 3 Feb. 2007 BD 1-04 GTO XSLC Success
13 F13 14 April 2007 Compass-M1 GTO XSLC Success
14 F14 1 June 2007 SinoSat-3 GTO XSLC Success
15 F15 24 Oct. 2007 Chang'e-1 GTO XSLC Success
16 F16 23 Dec. 2008 FY 2-06 GTO XSLC Success
Note * Chinese Scientific Payload       *** Chinese Third Generation Communications Satellite
** Xichang Satellite Launch Center