History
To meet demand of international satellite launch 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 fight proven technology of Long March launch vehicles.
LM-3B Structure |
1. Payload Faring
2. Payload
3. Payload Adapter
4. Vehicle Equipment Bay
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 Main 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
|
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 frst 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 on the basis of LM-3B, 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 boosters. On May 14, 2007, the 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 dedicated for launching heavy GEO communications satellite.
| Stage |
Booster |
1st Stage |
2nd Stage |
3rd Stage |
| Stage Diameter (m) |
2.25 |
3.35 |
3.35 |
3.00 |
| Stage Length (m) |
15.326
- |
23.272
- |
9.943 |
12.375 |
| Mass of Propellants (t) |
37.746×4 |
171.775 |
49.605 |
18.193 |
| 41.5´4* |
186.6* |
| Propellant |
N2O4/UDMH |
LOX/LH2 |
| Engine |
YF-25 |
YF-21C |
YF-24E
YF-22E (Main)
YF-23C (Vernier) |
YF-75 |
| Engine Thrust (KN) |
740.4×4 |
2961.6 |
742 (Main)
11.8×4 (Vernier) |
78.5×2 |
Engine Specific Impulse
(N·Sec/kg) |
2556.2 |
2556.2 |
2922.57 (Main)
2910.5 (Vernier) |
4312 |
| Booster |
4 |
| Lift-off Mass (t) |
426/458.97* |
| Overall Length (m) |
54.838/56.326* |
| Fairing Diameter (m) |
4.00/4.20 |
| Fairing Length (m) |
9.56 |
| GTO Launch Capacity (kg) |
5100/5500* |
* LM-3B/E launch vehicle
(as of April 1, 2010)
Launch Records
| No. |
Flight No. |
Launch Date |
Payload |
Mission |
Launch Center |
Result |
| 1 |
LM-3B F01 |
15 Feb. 1996 |
Intelsat-7A |
GTO |
XSLC* |
Failure |
| 2 |
LM-3B F02 |
20 Aug. 1997 |
MABUHAYSAT |
GTO |
XSLC |
Success |
| 3 |
LM-3B F03 |
17 Oct. 1997 |
APSTAR-II R |
GTO |
XSLC |
Success |
| 4 |
LM-3B F04 |
30 May. 1998 |
CHINASTAR-1 |
GTO |
XSLC |
Success |
| 5 |
LM-3B F05 |
18 July. 1998 |
SINOSAT-1 |
GTO |
XSLC |
Success |
| 6 |
LM-3B F06 |
12 April. 2005 |
APSTAR-VI |
GTO |
XSLC |
Success |
| 7 |
LM-3B F07 |
29 Oct. 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 |
CHINASAT-6B |
GTO |
XSLC |
Success |
| 10 |
LM-3B F10 |
9 Jun. 2008 |
CHINASAT-9 |
GTO |
XSLC |
Success |
| 11 |
LM-3B/E F11 |
30 Oct. 2008 |
VENESAT-1 |
GTO |
XSLC |
Success |
| 12 |
LM-3B F12 |
31 Aug. 2009 |
PALAPA-D |
GTO |
XSLC |
Anomaly |
Note:
* Xichang Satellite Launch Center
