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.
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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
|
|
|
|
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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 |
