Solid rocket stage. 980.00 kN (220,313 lbf) thrust. Mass 34,550 kg (76,170 lb).
Status: Retired 1974.
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Gross mass: 34,550 kg (76,160 lb).
Unfuelled mass: 3,750 kg (8,260 lb).
Height: 9.20 m (30.10 ft).
Diameter: 1.84 m (6.03 ft).
Thrust: 980.00 kN (220,310 lbf).
Burn time: 75 s.
Number: 4 .
15D23P TsKB-7 solid rocket engine. 980 kN. RT-2P Stage 1. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/ammonium butyl propellant. Chamber pressure 56 kgf/cm2. More...
Associated Launch Vehicles
RT-2P Russian intercontinental ballistic missile. Development of the improved RT-2P version of the basic missile was authorised by decree 1004-365 of 18 December 1968. The overriding concern was imminent deployment by the Americans of the Safeguard anti-ballistic missile system, and the need for the missile to have the necessary countermeasures to defeat those defences. More...
RT-2M Russian intercontinental ballistic missile. The RT-2M was a modernised RT-2, developed under Savodskiy at Korolev's bureau beginning in the late 1960's in parallel with the RT-2P and using alternate new engines. This increased both range and payload compared to the RT-20. However the RT-2P was selected for further development. More...
Associated Manufacturers and Agencies
Arsenal Russian manufacturer of rockets, spacecraft, and rocket engines. Arsenal Design Bureau, Saint Petersburg, Russia. 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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