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LM- 2C/CTS Launch Vehicle
* History
Based on the flight proven technology of LM-1 and LM-2, the development of LM-2C launch vehicle was started in 1970. After its successful test flight in 1975, LM-2 was renamed to LM-2C. Later it became the main force to launch China's recoverable satellites. With 14 successes out of 14 launches for LEO missions, this launch vehicle was selected by Motorola, Inc in April of 1993 to provide multiple launches for the Iridium communications satellites. According to the Iridium launch mission requirement, some necessary modifications were made. It included two upgraded stages based on LM-2C and a smart dispenser (SD) developed with flight proven technology and hardware. The renamed launch vehicle --- LM-2C/SD, as of December 31,1999, has achieved six successful launch missions for Motorola, sending 12 Iridium communications satellites into pre-defined orbit. As of April 30, 2005, the LM-2C has conducted 26 launches with 100% successful rate. After some improvements, the LM-2C/SD was renamed LM-2C/CTS.
* Technical Data
LM-2C/CTS is a launch vehicle with two liquid propellant stages plus a smart dispenser as its third stage developed on the basis of LM-2 and LM-2C. It is specially dedicated for launching different spacecraft for LEO missions.
LM-2C's launch capability for LEO mission is 3366 kg. LM-2C/CTS's capability for Iridium mission is 1456 kg. The fairing static envelope is 3 meters. To accommodate mobile communications satellite market, the LM-2C/CTS, with the successful Iridium program experiences, is capable of launching multiple satellites into different LEO.
|
1stStage |
2ndStage |
CTS* |
Stage Diameter (m) |
3.35 |
3.35 |
2.7 |
Stage Length (m) |
25.720 |
7.757 |
1.5 |
Mass of propellant (kg) |
162706 |
54667 |
125/50 |
Propellant |
UDMH /N2O4 |
HTPB/Hydrazine |
Engine |
DaYF6-2 |
DaYF20-1(Main)
YF21-1 (Vernier) |
Solid Motor / RCS (Reaction Control System) |
Thrust (KN) |
2961.6 |
741.4 (Main)
11.8x4 (Vernier) |
10.78(solid motor) |
Engine Specific Impulse
(NĄ¤Sec / kg) |
2556.5
(on ground) |
2922.37 (Main)
2834.11 (Vernier)
(in vacuum) |
2804
(solid motor) |
Lift-off Mass (t) |
233 |
Overall Length (m) |
42 |
Fairing Diameter (m) |
3.35 |
LEO or SSO Launch Capability (kg)
(h=900km, SSO) |
1456 |
*CTS is a three-axis stabilized upper stage compatible with two-stage LM-2C. CTS consists of spacecraft adapter and orbital maneuver system. LM-2C/CTS can deliver the spacecraft into the LEO (h>500km)or SSO.
Launch Record
No. |
Launch Vehicle |
Launch Date |
Payload |
Mission |
LaunchCenter |
Result |
| 01 |
LM-2C F01 |
26 Nov. 1975 |
FHW |
LEO |
JSLC |
Success |
| 02 |
LM-2C F02 |
7 Dec. 1976 |
FHW |
LEO |
JSLC |
Success |
| 03 |
LM-2C F03 |
26 Jan. 1978 |
FHW |
LEO |
JSLC |
Success |
| 04 |
LM-2C F04 |
9 Sept. 1982 |
FHW |
LEO |
JSLC |
Success |
| 05 |
LM-2C F05 |
19 Aug. 1983 |
FHW |
LEO |
JSLC |
Success |
| 06 |
LM-2C F06 |
12 Sept. 1984 |
FHW |
LEO |
JSLC |
Success |
| 07 |
LM-2C F07 |
21 Oct. 1985 |
FHW |
LEO |
JSLC |
Success |
| 08 |
LM-2C F08 |
6 Oct.1986 |
FHW |
LE0 |
JSLC |
Success |
| 09 |
LM-2C F09 |
5 Aug.1987 |
FHW/Piggyback |
LE0 |
JSLC |
Success |
| 10 |
LM-2C F10 |
9 Sept.1987 |
FHW |
LE0 |
JSLC |
Success |
| 11 |
LM-2C F11 |
5 Aug.1988 |
FHW/Piggyback |
LE0 |
JSLC |
Success |
| 12 |
LM-2C F12 |
5 Oct.1990 |
FHW |
LE0 |
JSLC |
Success |
| 13 |
LM-2C F13 |
6 Oct.1992 |
Freja/FHW-2*** |
LE0 |
JSLC |
Success |
| 14 |
LM-2C F14 |
8 Oct. 1993 |
FHW |
LE0 |
JSLC |
Success |
| 15 |
LM-2C/SD F15 |
1 Sept. 1997 |
Motorola**** |
LE0 |
TSLC***** |
Success |
| 16 |
LM-2C/SD F16 |
8 Dec.1997 |
Motorola |
LE0 |
JSLC |
Success |
| 17 |
LM-2C/SD F17 |
26 Mar. 1998 |
Motorola |
LE0 |
JSLC |
Success |
| 18 |
LM-2C/SD F18 |
2 May 1998 |
Motorola |
LE0 |
JSLC |
Success |
| 19 |
LM-2C/SD F19 |
20 Aug.1998 |
Motorola |
LE0 |
JSLC |
Success |
| 20 |
LM-2C/SD F20 |
19 Dec.1998 |
Motorola |
LE0 |
JSLC |
Success |
| 21 |
LM-2C/SD F21 |
12 June 1999 |
Motorola |
LE0 |
JSLC |
Success |
| 22 |
LM-2C/SM F22 |
30 Dec.2003 |
TC-1 |
LEO |
XSLC |
Success |
23 |
LM-2C/CTS F23 |
18 April 2004 |
Experiment Satllite-1/ Nano Satellite-1 |
SSO |
XSLC |
Success |
24 |
LM-2C/SM F24 |
25 July 2004 |
TC-2 |
LEO |
TSLC |
Success |
25 |
LM-2CF25 |
29 Aug. 2004 |
FHW |
LEO |
JSLC |
Success |
26 |
LM-2CF26 |
18Nov. 2004 |
Experiment Satellite-2 |
LEO |
XSLC |
Success |
Note:
* China's recoverable satellite
** Jiuquan Satellite Launch Center
*** FHW with a piggybacked Swedish scientific satellite -- Freja
**** Test flight with 2 mockup satellites for Iridium mission
***** Taiyuan Satellite Launch Center
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