Some important Soviet solid fuel missiles

Norbert Brügge. Germany

Update: 02.08.2010

LRBM

RT-1  (8K95)  & RT-1M (8K95M)


   


RT-1 rear


    

      
RT-1M launch

 

The RT-1 and RT-1M (RT = RocketSolid in Russian) were the first large Soviet solid propellant ballistic missiles. It was developed and tested in 1959-1963. but no production was undertaken due to its poor performance.

 

 RT-1   stage 1 stage 2 stage 3
Diameter m 1.60 (4x) 1.50 (4x) 1.50 (4x)
Mass tons      
Propellant tons      
Engine design. (nozzles)   ? (4) ? (4)  ? (4)
Thrust (s.l.) kN 980.7 - -
Thrust (vac) kN  ? 500.1 245.2
Isp (s.l.) Ns/kg 2000 - -
Isp (vac) Ns/kg ? 2187 ?
Burn time sec 30 30 42
 
RT-1M   stage 1 stage 2 stage 3
Diameter m 1.60 (4x) 1.50 (4x) 1.40 (1)
Mass tons      
Propellant tons      
Engine design. (nozzles)    ? (4)  ? (4) ? (4)
Thrust (s.l.) kN   - -
Thrust (vac) kN      
Isp (s.l.) Ns/kg   - -
Isp (vac) Ns/kg      
Burn time sec      




RT-1M

 

LRBM

RT-2  & RT-2P   (8K98 & 8K98P)



RT-2P missile



RT-2P second + third stages


RT-2P first stage


              
RT-2 second stage engines                                                                                              
  

 
RT-2  

stage 1

stage 2

stage 3
Diameter m 1.84 1.48 0.98
Masse tons 34.50 9.60 3.50
Propellant tons 30.67 ~8.30 ~2.70
Engine design. (nozzles)   15D23 (4) 15D24 (4) 15D94 (4)
Thrust (s.l.) kN 812 - -
Thrust (vac) kN ? 431.5 215.7
Isp (s.l.) Ns/kg ? - -
Isp (vac) Ns/kg ? ? ?
Burn time sec 75 60 30

 

RT-2P  

stage 1

stage 2

stage 3
Diameter m 1.84 1.49 1.06
Masse tons 34.55 11.28 4.64
Propellant tons 30.80 9.78 3.60
Engine design. (nozzles)   15D23P (4) 15D24P (4) ? (4)
Thrust (s.l.) kN 980.7 - -
Thrust (vac) kN ? 437.4 176.5
Isp (s.l.) Ns/kg ? - -
Isp (vac) Ns/kg ? ? ?
Burn time sec 75.4 60.6 49



RT-2P

 

IRBM

RT-15  (8K96)
RT-15  

stage 1

stage 2
Diameter m 1.48 0.98
Masse tons 9.60 3.50
Propellant tons ~8.30 ~2.74
Engine design. (nozzles)   15D24 (4) 15D94 (4)
Thrust (s.l.) kN ? -
Thrust (vac) kN 431.5 215.7
Isp (s.l.) Ns/kg ? ?
Isp (vac) Ns/kg ? ?
Burn time sec 60 30



 

IRBM

RT-20P (8K99)
RT-20P  

stage 1

stage 2
Diameter m 1.60 1.60
Masse tons 19.15 9.80
Propellant   solid UDMH/N2O4
tons 16.70 8.90
Engine design. (nozzles)   15D151 (4)  RD-857 (1)
Thrust (s.l.) kN 600 -
Thrust (vac) kN 647 147
Isp (s.l.) Ns/kg  ? -
Isp (vac) Ns/kg 2550 3236
Burn time sec 65 215



 

LRBM

RT-21 (Temp-2S)
RT-21  

stage 1

stage 2

stage 3
Diameter m 1.79 1.47 1.34 ?
Masse tons 26.7 8.63  
Propellant tons      
Engine design. (nozzles)   ? (1)  ? (1)  ? (1)
Thrust (s.l.) kN    - -
Thrust (vac) kN  -    
Isp (s.l.) Ns/kg    -  -
Isp (vac) Ns/kg  -    

Burn time

sec

 

 

 

 

 

 

?

 

 

 

 

 

IRBM

RSD-10 (Pioner)

     

RSD-10   stage 1 stage 2
Diameter m 1.79 1.47
Masse tons 26.70 8.63
Propellant tons ? ?
Engine design. (nozzles)   ? (1) ? (1)
Thrust (s.l.) kN ? -
Thrust (vac) kN ? ?
Isp (s.l.) Ns/kg ? -
Isp (vac) Ns/kg ? ?
Burn time sec 63  


                           

 

LRBM

RT-2PM1 (Topol)



        


    
First stage and third stage
RT-2PM  

stage 1

stage 2

stage 3
Diameter m 1.79 1.55 1.34
Masse tons      
Propellant tons      
Engine design. (nozzles)   ?  ?  ?
Thrust (s.l.) kN      
Thrust (vac) kN      
Isp (s.l.) Ns/kg      
Isp (vac) Ns/kg      
Burn time sec      


                                                          Second stage

 

LRBM

RT-2PM1 (Topol-M)


  

RT-2PM1  

stage 1

stage 2

stage 3
Diameter m 1.79    
Masse tons      
Propellant tons      
Engine design. (nozzles)   ?  ?  ?
Thrust (s.l.) kN      
Thrust (vac) kN      
Isp (s.l.) Ns/kg      
Isp (vac) Ns/kg      
Burn time sec      

 

LRBM

RT-23 & RT-23U


RT-23U



RT-23U launch



RT-23U first stage motor 15D305


    
RT-23 first stage motor 15D206
 RT-23   stage 1 stage 2 stage 3
Diameter m 2.40 2.40  2.40
Masse tons      
Propellant tons      
Engine design. (nozzles)   15D206 ?

 ?
Thrust (s.l.) kN 2,157 -  -
Thrust (vac) kN 2,354 ?  ?
Isp (s.l.) Ns/kg      
Isp (vac) Ns/kg      
Burn time sec      
Total Impulse (vac) MN*sec      
 
 RT-23U   stage 1 stage 2 stage 3
Diameter m 2.40 2.40 2.40
Masse tons      
Propellant tons      
Engine design. (nozzles)   15D305  15D339

?
Thrust (s.l.) kN 2,746 -  -
Thrust (vac) kN 3,040 1,471 ?
Isp (s.l.) Ns/kg      
Isp (vac) Ns/kg      
Burn time sec      
Total Impulse (vac) MN*sec      



RT-23U second stage motor 15D339

RT-23U third stage motor
 

SLBM

R-30 (Bulava)

                  
Test launch                                                                                                     

 

SLBM

R-31
R-31   stage 1 stage 2
Diameter m 1.54 1.54
Masse tons 17.50 6.90
Propellant tons    
Engine design. (nozzles)   ? (1) ? (1)
Thrust (s.l.) kN ? -
Thrust (vac) kN 580 233.3
Isp (s.l.) Ns/kg ? -
Isp (vac) Ns/kg ? ?
Burn time sec 84 74
 

 

 

 

 

 

SLBM

 R-39


  

R-39  

stage 1

stage 2

stage 3
Diameter m      
Masse tons      
Propellant tons      
Engine design. (nozzles)   ?  ?  ?
Thrust (s.l.) kN      
Thrust (vac) kN      
Isp (s.l.) Ns/kg      
Isp (vac) Ns/kg      
Burn time sec      

 

Tactical Missile

9M76 (TR-1. Temp-S)


9M76 (Temp-S)  

stage 1

stage 2
Diameter m 1.01 1.01
Masse tons    
Propellant tons    
Engine design. (nozzles)   ? (4) ? (4)
Thrust (s.l.) kN 167  
Thrust (vac) kN  -  -
Isp (s.l.) Ns/kg    
Isp (vac) Ns/kg  - -
Burn time sec    

 

Tactical Missile

9M79 & 9M79M (Totchka)


           
 


9M79   motor
Length m  
Diameter m  
Masse tons 0.926
Propellant tons 0.790
Engine design. (nozzles)   ?
Thrust (s.l.) kN 96.0
Thrust (vac) kN -
Isp (s.l.) Ns/kg 2314
Isp (vac) Ns/kg -
Burn time sec 19

 

Tactical Missile

9M714 (Oka)


    

9M79   motor
Length m  
Diameter m  
Masse tons  
Propellant tons  
Engine design. (nozzles)   ? (4)
Thrust (s.l.) kN  
Thrust (vac) kN -
Isp (s.l.) Ns/kg  
Isp (vac) Ns/kg -
Burn time sec  

 

Tactical Missile

9M723 (Iskander)


 

9M79   motor
Length m  
Diameter m 0.90
Masse tons  
Propellant tons  
Engine design. (nozzles)   ?
Thrust (s.l.) kN  
Thrust (vac) kN -
Isp (s.l.) Ns/kg  
Isp (vac) Ns/kg -
Burn time sec  

 

Tactical Missile (FROG)

9M21  (Luna & Luna-M)



Type Luna



Type Luna-M



Propulsion system: Launch engines-ring and main engine
9M21 (Luna)  

stage 1

stage 2
Diameter m 0.54 0.54
Masse tons    
Propellant tons    
Engine design. (nozzles)   3Ch18 ?
Thrust (s.l.) kN    
Thrust (vac) kN - -
Isp (s.l.) Ns/kg    
Isp (vac) Ns/kg - -
Burn time sec    

 

 

SAM (S-25)

ShB32



 

SAM/ABM (S-50)

V-400 (Dalh)



 

SAM (S-75)

V-750 (Volchov. Dvina. Desna)



V-750 (Dvina)


V-750 (Volchov)


  

 

SAM (S-75M)

V-755 (Volchov-M1)





V-755 (Volchov)

 

SAM (S-75M)

V-759 (5Ya23 Volchov-M2)


 

SAM (S-125)

V-600 & V-601 (Neva. Petchora)



 

SAM (S-200)

V-860 & V-880 (Angara. Vega. Dubna)


   


 

ABM

V-1000 ("Leningrad")




 

ABM

A-350 ("Galosh")