RD-8
Engine · Ukraine
Original archive entry. The text, images and links below are kept as they were written.
Credit: © Dietrich Haeseler
Yuzhnoye LOx/Kerosene rocket engine. Zenit stage 2 attitude control engine. In Production. Four-chamber pump-fed single-run engine operated in a staged combustion scheme with afterburning of the generator gas. Development began in 1976.
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.
Subtopics
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.
Related
- Country
- Ukraine
- Launch Vehicles
- Zenit-2
- Propellants
- Lox/Kerosene
- Agency
- Yuzhnoye