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15D151
NII-125 solid rocket engine. Designed for first stage of combined missile and SLBM; flight tested, no production. First flight 1967. Solid propellant rocket stage. Four nozzles. Length with interstage 9.8 m. Sea level thrust 60,000 kgf. Specific impulse estimated.

Status: Out of production. Date: 1964-69. Number: 12 . Thrust: 647.00 kN (145,451 lbf). Gross mass: 19,150 kg (42,210 lb). Unfuelled mass: 2,450 kg (5,400 lb). Specific impulse: 260 s. Specific impulse sea level: 235 s. Burn time: 65 s. Height: 6.12 m (20.07 ft). Diameter: 1.60 m (5.20 ft). Span: 1.80 m (5.90 ft).

Chambers: 4. Thrust (sl): 588.000 kN (132,187 lbf). Thrust (sl): 60,000 kgf.

Country: Ukraine. Launch Vehicles: RT-20P. Propellants: Solid. Stages: 15D151. Agency: NII-125. Bibliography: 475, 476.



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