 | LM-3C Launch Vehicle
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Orbital launch vehicle. Year: 1997. Family: Long March. Country: China. Status: Development ended 1997. Other Designations: Long March 3C. Manufacturer's Designation: Chang Zheng-3C. Launch vehicle combining CZ-3B core with two boosters from CZ-2E. The standard fairing was 9.56 m long, 4.0 m in diameter. On August 23, 2001, the CZ-3C launcher passed its critical design review. CZ-3C development had begun in 1995 but was suspended in 1996-2000 due to the 1996 CZ-3B failure. 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
Manufacturer: CALT. Payload: 3,800 kg (8,300 lb). to a: Geosynchronous transfer (200 x 35,793 km @ 28 deg) trajectory. Liftoff Thrust: 4,440.000 kN (998,150 lbf). Total Mass: 345,000 kg (760,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 54.80 m (179.70 ft). Launch Price $: 75.000 million. in: 1999 price dollars.
Stage Data - CZ-3C - Stage Number: 0. 2 x Stage: CZ-2E-0. Gross Mass: 41,000 kg (90,000 lb). Empty Mass: 3,200 kg (7,000 lb). Thrust (vac): 816.285 kN (183,508 lbf). Isp: 291 sec. Burn time: 128 sec. Isp(sl): 261 sec. Diameter: 2.25 m (7.38 ft). Span: 2.26 m (7.41 ft). Length: 15.33 m (50.29 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: YF-20B. Other designations: LB-40. Status: In production.
- Stage Number: 1. 1 x Stage: CZ-3A-1. Gross Mass: 179,000 kg (394,000 lb). Empty Mass: 9,000 kg (19,800 lb). Thrust (vac): 3,265.143 kN (734,033 lbf). Isp: 289 sec. Burn time: 155 sec. Isp(sl): 259 sec. Diameter: 3.35 m (10.99 ft). Span: 7.00 m (22.90 ft). Length: 23.08 m (75.72 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: YF-20B. Other designations: L-180. Status: Development ended 1997.
- Stage Number: 2. 1 x Stage: CZ-2C/SD-2. Gross Mass: 55,000 kg (121,000 lb). Empty Mass: 5,000 kg (11,000 lb). Thrust (vac): 761.900 kN (171,282 lbf). Isp: 298 sec. Burn time: 190 sec. Isp(sl): 270 sec. Diameter: 3.35 m (10.99 ft). Span: 3.35 m (10.99 ft). Length: 10.00 m (32.00 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: YF-22A/23A. Other designations: L-35. Status: Out of production. Stretched version of CZ-2C second stage. Empty mass estimated.
- Stage Number: 3. 1 x Stage: CZ-3A-3. Gross Mass: 21,000 kg (46,000 lb). Empty Mass: 2,800 kg (6,100 lb). Thrust (vac): 156.000 kN (35,070 lbf). Isp: 440 sec. Burn time: 470 sec. Diameter: 3.00 m (9.80 ft). Span: 3.00 m (9.80 ft). Length: 12.38 m (40.60 ft). Propellants: Lox/LH2. No Engines: 2. Engine: YF-75. Other designations: H-18. Status: Development ended 1997.
Bibliography and Further Reading - Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004. ISBN: 156347591X. The best reference on launch vehicles ever produced. More at amazon.com...
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