RD-8
11D513
Credit - © Dietrich Haeseler
Manufacturer Name: RD-8. Government Designation: 11D513. Designer: Yangel. Developed in: 1976-85. Application: Zenit stage 2 attitude control engine. Propellants: Lox/Kerosene. Thrust(vac): 78.400 kN (17,625 lbf). Isp: 342 sec. Burn time: 1,100 sec. Mass Engine: 380 kg (830 lb). Diameter: 4.00 m (13.10 ft). Length: 1.67 m (5.47 ft). Chambers: 4. Chamber Pressure: 76.50 bar. Oxidizer to Fuel Ratio: 2.40. Thrust to Weight Ratio: 21.03. Country: Ukraine. Status: In Production.

The RD-8 four-chamber pump-fed single-run engine operated in a staged combustion scheme with afterburning of the generator gas. Development began in 1976, and it 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.


Bibliography and Further Reading
  • Novosti kosmonavtiki, Issue 11, 1997 via Dietrich Haeseler.
  • Shnyakin, V N, Shidkostnye Raketye Dvigateli - Opisanie i Osnovnye Tekhnicheskie Dannye, GKB Yuzhnoe "Yangel", Dnepropetrovsk 1996 via Dietrich Haeseler.
 
 
 
 
 
 
 
 
 

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