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Weapons of Mass Destruction (WMD)


RT-2UTTH - Topol-M
SS-27


Specifications
Compoundthree-stage intercontinental ballistic missile with sequential stage separation, universal for two types of basing
DIA SS-27, SS-X-29, SS-25B
NATO  
Bilateral RS-12M2
Service RT-2PM2, RT-2PM-OS
OKB/Industry 15Zh??
Design Bureau (MIT)Moscow Institute of Thermal Technology
Approved 2/ /1993
Years of R&D 1993 - 1997
Engineering and Testing 1994 1997
First Flight Test 12/20/94
IOC 1997
Deployment Date 12/27/1997
Warranty period of operation15 years
Reached service life(as of January 1, 2009)
11 years (for silo variant of RK basing),
3 years (for mobile soil variant of RK basing)
Type of Warhead
  • Yars = monoblock with a nuclear warhead and a set of means to overcome missile defense
  • Yars-M = multiple nuclear warheads and means to overcome missile defense
    • Warheads Yars = 1 (+ ~ 20 false targets)
  • Yars-M = 3 or 4 (+ false targets)
    • Yield (Mt)
  • Yars = 0.55 Mt
  • Yars-M = 150-300 or 300–500 kt kt
    • Payload (kg) 1,000 - 1,200 - Western sources
    ~1200 kg Russian sources
    Total length (m) 21.0 - 22.7 - Western sources
    22.5 m Russian sources
    Total length w/o warhead (m) 17.9
    Missile Diameter (m) 1.86 - 1.95 - Western sources
    1.8 m Russian sources
    Launch Weight (t) 47.2 - 47.21 - Western sources
    46.5 t Russian sources
    Fuel Weight (t)  
    Range (km) 10,000 -10,500 Western sources
    11000 km Russian sources
    CEP (m) (Russian Sources)  
    CEP (m) (Western Sources) 350+


    Number of Stages 3
    Canister length (m) 21,2 - 23.0
    Canister length w/o
    front meters (m)    		 19.44
    Canister diameter (m) 2.0
    Booster guidance system Inertial, autonomous


      1st stage 2nd stage 3rd stage 4th. BUS
    Length (m) 8.04?      
    Body diameter (m) 1.86 - 1.95 1.61 1.58  
    Fueled weight (t) 28.6      
    Dry weight (t)        
    Design Bureau for the Solid Motors MIT, NPO Soyuz MIT, NPO Soyuz MIT, NPO Soyuz  
    Engine Designation        
    Propellants Solid Propellant Solid Propellant Solid Propellant  
    Burning time (s)        
    Solid Motor Thrust Sea Level/Vacuum (Tonnes)        
    Specific Impulse (m/s)        


    Basing Mode Silo/Ground mobile
    Hardness  
    Launching Technique  
    Deployed boosters  
    Test Boosters  
    Warheads Deployed  
    Deployment Sites  
    Training Launchers  
    Space Booster Variant No

    APU with ICBM RT-2PM2

    Full mass120 t
    TPK length~22 m
    TPK diameter~2.0 m
    Propulsion power800 HP
    engine typeV-shaped 12-cylinder turbocharged diesel YaMZ-847
    Chassis typeeight-axle wheeled chassis with hydromechanical transmission
    Wheel formula16x16
    Fuel range500 km
    Movement speed:
    on paved roads40 km/h
    on dirt roads30 km/h
    through the explored area15 km/h
    Warranty period of operation15 years



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