LM-3C Launch Vehicle - Long March LM-3C launch vehicle on the pad. 18,432 bytes. 150 x 318 pixels.

Launch vehicle combining CZ-3B core with two boosters from CZ-2E. The standard fairing is 9.56 m long, 4.0 m in diameter.

Launch sequence:

Event                                     TIME (sec.)
 First Stage Ignition                          -3
 Liftoff                                        0.00
 Pitch over                                    11.0
 Booster Separation                           127.24
 First/Second Stage Separation                147.36
 Jettisoning of Fairing                       232.4
 2nd/3rd Stage Sep. & 3rd Stage Ignition      332.31
 1st Shutoff of 3rd Stage                     631.32
 2nd Ignition of 3rd Stage                   1281.23
 2nd Shutoff of Third Stage                  1459.91
 Satellite/Launcher Sep.                     1559.907

Payload: 3,800 kg. to a: Geosynchronous transfer (200 x 35,793 km @ 28 deg) trajectory. Liftoff Thrust: 453,000 kgf. Total Mass: 345,000 kg. Core Diameter: 3.4 m. Total Length: 54.8 m. Launch Price $: 75.00 million. in 1999 price dollars.

• Stage Number: 0. 2 x CZ-2E-0 Gross Mass: 41,000 kg. Empty Mass: 3,200 kg. Thrust (vac): 83,238 kgf. Isp: 291 sec. Burn time: 128 sec. Isp(sl): 261 sec. Diameter: 2.3 m. Span: 2.3 m. Length: 15.3 m. Propellants: N2O4/UDMH No Engines: 1. YF-20B

• Stage Number: 1. 1 x CZ-3A-1 Gross Mass: 179,000 kg. Empty Mass: 9,000 kg. Thrust (vac): 332,952 kgf. Isp: 289 sec. Burn time: 155 sec. Isp(sl): 259 sec. Diameter: 3.4 m. Span: 7.0 m. Length: 23.1 m. Propellants: N2O4/UDMH No Engines: 4. YF-20B

• Stage Number: 2. 1 x CZ-2C/SD-2 Gross Mass: 55,000 kg. Empty Mass: 5,000 kg. Thrust (vac): 77,700 kgf. Isp: 298 sec. Burn time: 190 sec. Isp(sl): 270 sec. Diameter: 3.4 m. Span: 3.4 m. Length: 10.0 m. Propellants: N2O4/UDMH No Engines: 1. YF-22A/23A

• Stage Number: 3. 1 x CZ-3A-3 Gross Mass: 21,000 kg. Empty Mass: 2,800 kg. Thrust (vac): 16,000 kgf. Isp: 440 sec. Burn time: 470 sec. Diameter: 3.0 m. Span: 3.0 m. Length: 12.4 m. Propellants: Lox/LH2 No Engines: 2. YF-75

• 455 - Isakowitz, Steven J,, International Reference to Space Launch Systems Third Edition, AIAA, Washington DC, 2000.