Credit: © Dietrich Haeseler
AKA: 11D513. Status: In Production. Date: 1976-85. Thrust: 78.40 kN (17,625 lbf). Unfuelled mass: 380 kg (830 lb). Specific impulse: 342 s. Burn time: 1,100 s. Height: 1.67 m (5.47 ft). Diameter: 4.00 m (13.10 ft).
The RD-8 was designed from the beginning for high reliability (no less than 0.995%) long service life (more than 4000 seconds); and for installation in the upper stage after a factory firing test without the need for post -test refurbishment. A safe shutdown was commanded upon depletion of any propellant component. The propellants were ignited in the gas generator and chambers by use of a starting fuel. The control units were fed with helium through electropneumatic valves. The engine could stay ready on the pad, filled with propellants, for 24 hours before a launch would need to be scrubbed and the engine purged and recycled. The engine design of the engine allowed for multiple bench firing tests.
Chambers: 4. Engine: 380 kg (830 lb). Chamber Pressure: 76.50 bar. Thrust to Weight Ratio: 21.03. Oxidizer to Fuel Ratio: 2.4.
|RD-802 Yuzhnoye LOx/Kerosene rocket engine. Upper stages. Design concept 2007. Derivative of the RD-8 Zenit-2 second stage vernier thrust engine combustion chamber for use in launch vehicle upper stages.|
|RD-809 Yuzhnoye LOx/Kerosene rocket engine. Upper stages. 2007 design concept for a four-chamber restartable main engine for launch vehicle upper stages.|