15D151
Engine · Ukraine
Original archive entry. The text, images and links below are kept as they were written.
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.
Chambers: 4. Thrust (sl): 588.000 kN (132,187 lbf). Thrust (sl): 60,000 kgf.