Notional LOx/Kerosene rocket engine. Study 1963. Engines used in recoverable stage of ballistic shape; separation at 3,420 m/s at 93,900 m altitude; splashdown using retrorockets under 7 parachutes 1340 km downrange.
Status: Study 1963. Thrust: 31,010.00 kN (6,971,320 lbf). Specific impulse: 330 s. Specific impulse sea level: 310 s. Burn time: 203 s.