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Based on fight proven technology of LM-1 and LM-2, the development of LM- 2C launch vehicle was started in 1970. After its successful fight in 1975, LM-2 was renamed to LM-2C.

With 14 successes out of 14 launches for LEO missions, this launch vehicle was selected by Motorola, Inc. in April 1993 to provide multiple launches for Iridium communications satellites. According to the Iridium launch mission requirement, some necessary modifications were made. Then this launch vehicle was renamed as LM-2C/SD. Twelve (12) Iridium satellites were successfully launched by LM-2C/SD.

Technical Data
Stage 1st Stage 2nd Stage Upper Stage
Stage Diameter (m) 3.35 3.35 2.7
Stage Length (m) 25.720 7.757 1.5
Propellant mass (kg) 162,706 54,667 125/50
Propellant UDMH /N2O4 HTPB/Hydrazine
Engine YF-21C YF-24E
YF-22E (Main)
YF23C (Vernier)
Solid Motor / RCS (Reaction Control System)
Thrust (KN) 2961.6 741.4 (Main)
11.8x4 (Vernier)
10.78 (solid motor)
Engine Specific Impulse
(N��Sec / kg)
(on ground)
2922.37 (Main)
2834.11 (Vernier)
(in vacuum)
(solid motor)
Lift-off Mass (t) 233
Overall Length (m) 42
Fairing Diameter (m) 3.35
Launch Capability (kg) LM-2C LEO 3850 (200km/63°)
SSO 1400 (600km)
LM-2C/SM GTO 1250 (28°)
LM-2C/SMA SSO 1900 (600km)

1. Fairing
2. Payload
3. Payload Adapter
4. Vehicle Equipment Bay
5. Second Stage Oxidizer Tank
6. Inter-tank Section
7. Second Stage Fuel Tank
8. Second Stage Vernier Engines
9. Second Stage main Engine
10. Inter-stage Structure
11. First Stage Oxidizer Tank
12. Inter-tank Section
13. First Stage Fuel Tank
14. Backward Transition Section
15. Tail Section
16. Stabilizer
17. First Stage Engines