Solid propellant rocket stage. Loaded/empty mass 19,150/2,450 kg. Thrust 647.00 kN. Vacuum specific impulse 260 seconds. Four nozzles. Length with interstage 9.8 m. Sea level thrust 60,000 kgf. Specific impulse estimated.
Status: Retired 1969.
More... - Chronology...
Gross mass: 19,150 kg (42,210 lb).
Unfuelled mass: 2,450 kg (5,400 lb).
Height: 6.12 m (20.07 ft).
Diameter: 1.60 m (5.20 ft).
Span: 1.80 m (5.90 ft).
Thrust: 647.00 kN (145,451 lbf).
Specific impulse: 260 s.
Specific impulse sea level: 235 s.
Burn time: 65 s.
Number: 12 .
15D151 NII-125 solid rocket engine. Combined missile (RT-20P) stage 1. Out of production. Launch thrust 588 kN. Designed for first stage of combined missile and SLBM; flight tested, no production. First flight 1967. More...
Associated Launch Vehicles
RT-20P Ukrainian intercontinental ballistic missile. Following the protracted development of Shavyrin's Gnom air-augmented ICBM, it was decided to let Yangel tackle the problem of developing a 30 tonne gross mass ICBM using more conventional technology. At first a three-stage solid propellant design was considered. But it was found impossible to achieve the launch weight with such an approach. Yangel's solution was to propose the only mixed propulsion ICBM ever developed - a solid propellant first stage, and high performance ampulised storable liquid propellant second stage. The draft project for the missile was completed in December 1964 and a decree to proceed with development was issued on 24 August 1965. Shortly thereafter Shavyrin died and Gnom was cancelled, leaving Yangel's RT-20P the lead project for the mobile ICBM requirement. Designs for silo-launched and submarine-launched versions of the missile were to be developed as well. More...
Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...
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