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RD-8 LIQUID PROPELLANT ROCKET ENGINE
 


Enterprise:Yuzhnoye State Design Office

Type of Production:Engines and units LV


Photo:


Description:

    Intended for flight control of the second stage of "Zenit-2", "Zenit-3SL" launch vehicles via all stabilization channels.
    FUNCTIONAL SPECIFICS
    An autonomous four-chamber single-operation engine with fuel pump supply, using the generator gas afterburning scheme. The engine is delivered to the customer after firing control/processing test, without its subsequent reassembly.

    Thrust in vacuum. kN (kgf)78.5 (8,000)
    Specific thrust pulse in vacuum, kN sec/kg (kgf sec/kg)3.42 (342)
    Engine weight, kg380
    Absolute pressure in combustion chamber, kPa (kgf/cm2)7,800 (78)
    Absolute pressure at the chamber nozzle edge, kPa (kgf/cm2)5 (0.05)
    Fuel components:
    oxidantliquid oxygen
    fuelkerosene
    Chamber deviation angle, ang. deg 33
    Operation time, sec1,100
    Operational life, sec, not less than4,000
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