Encyclopedia Astronautica
15D94


Solid rocket stage. 180.40 kN (40,556 lbf) thrust. Mass 4,640 kg (10,229 lb).

Status: Retired 1974.
Gross mass: 4,640 kg (10,220 lb).
Unfuelled mass: 1,040 kg (2,290 lb).
Height: 4.60 m (15.00 ft).
Diameter: 0.98 m (3.21 ft).
Thrust: 180.40 kN (40,556 lbf).
Burn time: 49 s.
Number: 4 .

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Associated Countries
Associated Engines
  • 15D94 TsKB-7 solid rocket engine. 180.4 kN. RT-2P Stage 3. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/ammonium butyl propellant. Chamber pressure 48 kgf/cm2. More...

Associated Launch Vehicles
  • RT-15 Russian intermediate range ballistic missile. The RT-15 IRBM used the second and third stages if the RT-2 ICBM. After protracted development in 1961-1970 with a range of alternative self-propelled mobile launchers, limited numbers ('few' to 19) of two types of launchers were deployed in 1970. The various transporters tested created confusion in the West (with designations SS-14 Scapegoat and Scamp being applied). More...
  • 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...

Associated Propellants
  • 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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