Proj 921 Spacecraft Proj 921 Spacecraft
Chinese Project 921 Spacecraft. Provisional drawing based on description and drawing of earlier design. Four solar panels, Soyuz-shaped re-entry vehicle, cylindrical forward orbital module, androgynous docking system.
LOx/Kerosene propellant rocket stage. Engine chamber pressure 13 to 15 MPa.
Status: Design 1992. Thrust: 5,406.14 kN (1,215,349 lbf). Gross mass: 306,000 kg (674,000 lb). Unfuelled mass: 20,000 kg (44,000 lb). Specific impulse: 330 s. Specific impulse sea level: 293 s. Burn time: 170 s. Height: 29.00 m (95.00 ft). Diameter: 4.50 m (14.70 ft). Span: 7.50 m (24.60 ft).
No Engines: 4.
Country:
China.
Launch Vehicles:
Chang Cheng 1,
Project 921.
Propellants:
Lox/Kerosene.
