Encyclopedia Astronautica
CZ-1C


Chinese orbital launch vehicle. Proposed launch vehicle derived from the CZ-1, with a new upper stage. Never flown.

LEO Payload: 500 kg (1,100 lb) to a 330 km orbit.

Stage Data - CZ-1C

  • Stage 1. 1 x CZ-1-1. Gross Mass: 64,100 kg (141,300 lb). Empty Mass: 4,100 kg (9,000 lb). Thrust (vac): 1,224.575 kN (275,295 lbf). Isp: 268 sec. Burn time: 130 sec. Isp(sl): 241 sec. Diameter: 2.25 m (7.38 ft). Span: 4.00 m (13.10 ft). Length: 17.84 m (58.53 ft). Propellants: Nitric acid/UDMH. No Engines: 4. Engine: YF-2A. Status: In Production.
  • Stage 2. 1 x CZ-1-2. Gross Mass: 15,000 kg (33,000 lb). Empty Mass: 2,700 kg (5,900 lb). Thrust (vac): 306.143 kN (68,824 lbf). Isp: 275 sec. Burn time: 110 sec. Isp(sl): 200 sec. Diameter: 2.25 m (7.38 ft). Span: 2.25 m (7.38 ft). Length: 5.35 m (17.55 ft). Propellants: Nitric acid/UDMH. No Engines: 1. Engine: YF-2A. Status: In Production. Comments: Masses, engine performance estimated based on successor improved stage and YF-2 engines in first stage.
  • Stage 3. 1 x CZ-1C-3. Gross Mass: 6,400 kg (14,100 lb). Empty Mass: 1,000 kg (2,200 lb). Thrust (vac): 107.000 kN (24,054 lbf). Isp: 287 sec. Burn time: 164 sec. Isp(sl): 258 sec. Diameter: 1.80 m (5.90 ft). Span: 1.80 m (5.90 ft). Length: 4.50 m (14.70 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: CZ-1C-3. Status: In production.

AKA: Long March 1C; Chang Zheng-1C.
Status: Development ended 1988.
Gross mass: 85,950 kg (189,480 lb).
Payload: 500 kg (1,100 lb).
Height: 33.00 m (108.00 ft).
Diameter: 2.25 m (7.38 ft).
Thrust: 1,101.20 kN (247,560 lbf).
Apogee: 330 km (200 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • CZ-1C-3 Chinese N2O4/UDMH rocket engine. 107.9 kN. Development ended 1988. Isp=287s. Used on CZ-1C launch vehicle. More...
  • YF-2A Beijing Wan Yuan Nitric acid/UDMH rocket engine. 306.1 kN. Out of production. Isp=268s. Used on CZ-1, CZ-1C, CZ-1D, CZ-1M. First flight 1969. More...

See also
  • CZ-1 China began development of the CZ-1 (Changzheng-1 = Long March-1) launch vehicle in the second half of 1965. The project was undertaken with the specific objective of launching China's first satellite, the DFH-1. The CZ-l's first and second stages were adapted from those of the DF-3 intermediate range ballistic missile. The third stage used a new-design solid rocket motor. More...

Associated Manufacturers and Agencies
  • CALT Chinese manufacturer of rockets, spacecraft, and rocket engines. China Academy of Launch Vehicle Technology, Beijing, China. More...

Associated Stages
  • CZ-1-2 Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 15,000/2,700 kg. Thrust 306.14 kN. Vacuum specific impulse 275 seconds. Masses, engine performance estimated based on successor improved stage and YF-2 engines in first stage. More...
  • CZ-1C-3 N2O4/UDMH propellant rocket stage. Loaded/empty mass 6,400/1,000 kg. Thrust 107.00 kN. Vacuum specific impulse 287 seconds. More...
  • CZ-YF-2 Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 64,100/4,100 kg. Thrust 1,224.58 kN. Vacuum specific impulse 268 seconds. More...

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