RD-866

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RD-866

RD-866
Credit: Yuzhnoye

Yuzhnoye N2O4/UDMH rocket engine. RT-23 MIRV-bus. Out of Production. Engine consisted of two turbopumps with gas generators and two feeders; a single chamber main engine; and 16 liquid thrusters for attitude control and translation.

AKA: 3D65. Status: Out of Production. Date: 1980-83. Thrust: 5.20 kN (1,169 lbf). Unfuelled mass: 125 kg (276 lb). Specific impulse: 306 s. Burn time: 330 s. Height: 1.19 m (3.89 ft). Diameter: 1.98 m (6.49 ft).

The RD-866 engine powered the MIRV distribution bus. The engine provided:

delivery of fuel delivery to the steering units used for missile flight control at the end of the first stage burn and during the second and third stage engine burns
roll control during third stage burn
during dispensing of multiple independently targeted warheads, provision of attitude and translation forces in multiple burns of the main engine and peripheral thrusters
fuel delivery to the hydraulic actuators that gimbaled the main engine during warhead distribution

The multifunction engine operated under a generator scheme. Propellants were fed under a combined scheme (pressure-fed and pump delivery). A broad range of flow-rates and pressures were provided according to the engine mode. The engine consisted of a centralized propellant supply source composed of two turbopumps with gas generators and two feeders; a single chamber main engine; and 16 liquid thrusters for attitude control and translation. Overall vacuum thrust of between minus 926 KN to plus 5036 kN could be provided at a mean specific impulse of 305.5 seconds for the design dispensing profile. The thrusters could be fired in continuous or 10 Hz pulsed modes.

Summary: One main and 16 control thrusters. 5.20 kN + 16 x 116 N. Chamber pressure 40.7 / 5.56 bar. Specific impulse 305.5 / 245 sec. Burn time 330 / 1200 sec. Oxidizer to fuel ratio 2.03 / 1.85.

Chambers: 1 + 16. Engine: 125 kg (276 lb). Chamber Pressure: 40.70 bar. Thrust to Weight Ratio: 4.22. Oxidizer to Fuel Ratio: 2.03.

Family: Storable liquid. Country: Ukraine. Launch Vehicles: RT-23. Propellants: N2O4/UDMH. Stages: RT-23-3. Agency: Yuzhnoye. Bibliography: 330, 344, 348, 97.

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