Fourth Academy solid rocket engine. 181 kN. CZ-1 launch vehicle. Out of production. Isp=254s. First upper stage, zero-G, vacuum-start solid rocket motor developed in China. Inserted China's first satellite into orbit on 24 April 1970.
Development issues confronted included ignition at high alititude, effects of spinning on combustion, motor burn rate, insulaton erosion, and alumina slag. Total impulse 4500 kN-s over 38 seconds. Nozzle diameter 728 mm.
Application: CZ-1 launch vehicle.
Propellant Formulation: Polysulfide.
Status: Out of production.
More... - Chronology...
Gross mass: 2,050 kg (4,510 lb).
Unfuelled mass: 246 kg (542 lb).
Height: 3.95 m (12.95 ft).
Diameter: 0.77 m (2.51 ft).
Thrust: 181.00 kN (40,690 lbf).
Specific impulse: 254 s.
Burn time: 38 s.
First Launch: 1966-1971.
Number: 4 .
Associated Launch Vehicles
CZ-1 Chinese orbital launch vehicle. 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
Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...
Huang Jianding and Ye Dingyou, "The Development of Space Solid Rocket Motors in China", Acta Astronautica, Vol 40, No. 2-8, pp. 607-612, 1997..
GF-02 Solid propellant rocket stage. Loaded/empty mass 2,050/246 kg. Thrust 180.99 kN. Vacuum specific impulse 254 seconds. More...
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