Launch Vehicle
 
     
 

To meet demand of international GEO communications satellite market, especially for high power and heavy communications satellites, the development of LM-3B launch vehicle was started in 1986 on the basis of the flight proven technology of Long March launch vehicles.

The configurations of the LM-3B launch vehicle have been qualified and flight proven by its eleven successful flights since 1997. The compatibility between LM-3B and major satellite platforms,including Space Systes/Loral's FS1300, Lockheed Martin's A2100, Thales Alenia Space's Spacebus 3000&4000, DHF 4 ,has been verified by the GTO launch services to dozens of international clients.

Technical Data

LM-3B is the most powerful launch vehicle in Long March fleet based on LM-3A as its core stage with four liquid boosters strapped on the first stage. The development of LM-3B has been made upon good heritage of mature and flight proven technology of Long March family of launch vehicles. Its GTO capacity is 5,100kg.

In recent years, the LM-3B/E (Enhanced Version) launch vehicle is developed, increasing the GTO capacity up to 5,500kg. LM-3B/E has nearly the same configurations with LM-3B except its enlarged core stage and booster. On 14 May, 2007, the maiden flight of LM-3B/E was performed successfully, accurately sending the NigcomSat-1 into pre-determined orbit.

With the GTO launch capability of 5,500kg, LM-3B/E is suitable for launching heavy GEO communications satellite.

1.Payload Faring
2.Payload
3.Payload Adapter
4.VehicleEquipmentBay
5.LH2 Tank
6.LOX Tank
7.Inter-stage Section
8.Third Stage Engine
9.Oxidizer Tank
10.Inter-tank Section
11.Fuel Tank
12.Second Stage Vernier Engine
13.Second Stage Engine
14.Inter-stage Truss
15.Oxidizer Tank
16.Fuel Tank
17.First Stage Engine
18.Strap-on Booster Cone
19.Strap-on Booster Oxidizer Tank
20.Strap-on Booster Fuel Tank
21.Stabilizer
22.Strap-on Booster Engine

Stage

Booster

1stStage

2ndStage

3rdStage

Stage Diameter (m)

2.25

3.35

3.35

3.00

Stage Length (m)

15.326/16.094*

23.272/24.76*

12.92

12.375

Mass of Propellants (t)

37.7x4

171.8

49.4

18.2

41.1x4*

186.2

Propellant

N2O4/UDMH

LOX/LH2

Engine

YF-25

YF-21C

YF-24E

YF-75

Engine Thrust (KN)

740.4x4

2961.6

742 (Main)

78.5x2

 

 

 

47.1 (Vernier)

Engine Specific Impulse (N Sec/kg)

2556.2

2556.5

2922.57(Main)

4312

2910.5(Vernier)

Booster

 

 

4

 

Lift-off Mass (t)

 

 

425.8/456

 

Overall Length (m)

 

 

54.838/56.326*

 

Fairing Diameter (m)

 

 

4.00/4.20

 

Fairing Length (m)

 

 

9.56/9.777

 

GTO LaunchCapacity (kg)

 

5100/5500*

 

 

*LM-3B/E launch vehicle

 

 

 

 

Launch Record

No.

Flight

No.

Launch Date

Payload

Mission

Launch Site

Result

1

LM-3B

F01

15 Feb.1996

INTELSAT-7A

GTO

XSLC*

Success

2

LM-3B

F02

20 Aug. 1997

MABUHAYSAT

GTO

XSLC

Success

3

LM-3B

F03

17 Oct. 1997

APSTAR-ⅡR

GTO

XSLC

Success

4

LM-3B

F04

30 May. 1998

CHINASTAR-1

GTO

XSLC

Success

5

LM-3B

F05

18July.1998

SINOSAT-1

GTO

XSLC

Success

6

LM-3B

F06

12 April. 2005

APSTAR-VI

GTO

XSLC

Success

7

LM-3B

F07

29Oct.2006

SINOSAT-2

GTO

XSLC

Success

8

LM-3B/E

F08

14 May. 2007

NIGCOMSAT-1

GTO

XSLC

Success

9

LM-3B

F09

5 Jul.2007

NIGCOMSAT-6B

GTO

XSLC

Success

10

LM-3B

F10

9 Jun. 2008

CHINASAT-9

GTO

XSLC

Success

11

LM-3B/E

F11

9 June.2008

VENESAT-1

GTO

XSLC

Success

12

LM-3B

 

31 Aug. 2009

PALAPA-D

GTO

XSLC

Success

13

LM-3B/E

 

5 Sep. 2010

SINOSAT-6

GTO

XSLC

Success

Note:
* XichangSatelliteLaunchCenter
** LM-3B/Papala-D mission experienced underperformance

 
 
 
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