Some important Soviet solid fuel missiles

Norbert Brügge, Germany

Update: 02.01.2012

     Content:

 


   


RT-1 rear


    

           
                      RT-1M launch                                      RT-1

 

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

 



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

 

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



 

RT-20  

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 647 137.5
Isp (s.l.) Ns/kg  ? -
Isp (vac) Ns/kg 2550 3285
Burn time sec 65 234


 

Temp-2S  

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

 

 

 

 

     

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  


                           

 



        


    
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

 


  

RT-2PM  

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      

 


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

  


   
Test launch
R-30   stage 1 stage 2 stage 3
Diameter m 2.00 2.00 2.00
Masse tons 18.6 17.05
Propellant tons     liquid
Engine design. (nozzles)   ? (1) ? (1) ?
Thrust (s.l.) kN ? - -
Thrust (vac) kN ? ? ?
Isp (s.l.) Ns/kg ? - -
Isp (vac) Ns/kg ? ? ?
Burn time sec      

 

SLBM

R-31
 R-31    stage 1  stage 2
Diameter m    
Masse tons    
Propellant tons    
Engine design. (nozzles)    ? (4)  ? (1)
Thrust (s.l.) kN    
Thrust (vac) kN    
Isp (s.l.) Ns/kg    
Isp (vac) Ns/kg    
Burn time sec    

 

SLBM

 R-39


  
 

R-39  

stage 1

stage 2

stage 3
Diameter m      
Masse tons      
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      

ABM

5V61 (GALOSH)


Overall Length: 19.8 meters
Overall Launch Mass: 32,700 kg
Maximum Range: 350 kilometers
Engagement Altitude: 120 kilometers

Booster Motor: Four clustered solid rocket boosters RDTT 5S47

Booster Length: 7.9 meters
Booster Diameter: 2.57 meters
Booster Launch Mass: 15,000 kg

Interceptor Length: ~11.9 meters
Interceptor Launch Mass: 15 tonnes

Interceptor Sustainer Motor: Single chamber liquid fuel motor 5D22*.
Thrust: 131.4 kN. Propellant: UDMH/N2O4.
Interceptor Steering Motor: Four chamber liquid fuel motor 5D18*.

* The 5D22 and 5D18 engines are similary the 15D13 and 15D14
    engines on the UR-100 ICBM.


  


  



 

ABM 51T6 (GORGON)


Overall Length: ~19.9 meters
Overall Launch Mass: 00,000 kg
Maximum Range: 000 kilometers
Engagement Altitude: 000 kilometers

Booster Motor: One solid rocket motor RDTT

Booster Length: ~8.00 meters
Booster Diameter: ~1.80 meters
Booster Launch Mass: 30 tonnes

Interceptor Length: ~11.9 meters
Interceptor Launch Mass: 15 tonnes

Interceptor Sustainer Motor: Single chamber liquid fuel motor 5D22*.
Thrust: 131.4 kN. Propellant: UDMH/N2O4.
Interceptor Steering Motor: Four chamber liquid fuel motor 5D18*.

* The 5D22 and 5D18 engines are similary the 15D13 and 15D14
    engines on the UR-100 ICBM.

 

 

 

          

 



51T6 ABM without motors


Interceptor + boost stage


Interceptor without motor


Boost stage tail
  

ABM

53T6/5Ya26 (GAZELLE)


Overall Length: ~9.0 meters
Overall Launch Mass: 00,000 kg
Maximum Range: 000 kilometers
Engagement Altitude: 000 kilometers

Booster Motor: One solid rocket motor RDTT 5S73

Booster Length: ~5.5 meters
Max. booster Diameter: 1.25 meters (?)
Booster Launch Mass: 00,000 kg

Interceptor Length: ~3.5 meters
Interceptor Launch Mass: 4 tonnes

      
 

 

Similar is China's ABM "FenJi" with added booster (L-SpaB-140A ?)

 

ABM

 5Ya27 (V-825)

Overall Length: ~18.0 meters
Overall Launch Mass: 18 tonnes
Maximum Range: 000 kilometers
Engagement Altitude: 000 kilometers

Booster Motor: One solid rocket motor RDTT 5S24.

Booster Length: ~9.0 meters
Booster Diameter: 1.25 meters
Booster Launch Mass: 14 tonnes

Interceptor Length: ~9.0 meters (similar 53T6/5Ya26 GAZELLE ?)
Interceptor Launch Mass: 4 tonnes

Interceptor Sustainer Motor: Solid rocket motor RDTT 5S73 (?)
 Thrust: 0 kN




 

ABM

V-1000 (Leningrad)




Booster a Kartukov PRD-70 motor ?



 

SAM (S-25, successor)

V-80 (ShB32)



Source: http://pvo.guns.ru/s25/shb32.htm


 

SAM/ABM (S-50)

V-400 (5V11, Dalh)



 


Left: Dalh second stage engine RD-0200 (former S2.1200)
Right: Third stage engine RD-0201 (former S2.1201) for V-1100 project



The V-400 booster used a Kartukov PRD-70 motor



 

SAM (SA-75)

V-750 (Dvina, Desna)


 


Dvina
Desna

 
System Name Factory code Military code  
SA-75 Dvina V-750 1D  
V-750V 11D  
V-750VK  
V-750VM 11DM  
11DU  
11DA  
S-75 Desna V-750VN 13D  
13DA  
  Volga V-760 15D  nuclear WH



Dvina nozzle



Dvina rear



Desna nozzle is differnt to Dvina)
 



Desna booster
 

SAM (S-75M)

V-755 (Volkhov)


System Name Factory code Military code  
S-75M Volkhov V-755 20D  
20DP  
20DA  
V-755OV 20DO  
V-755U 20DS  
20DSU  
20DU  
S-75M2 5Ya23 V-759 5V23  
  Volga-M V-760V 5V29  nuclear WH



 

SAM (S-75M)

V-759 (5Ya23)


 

SAM (S-125)

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

Propulsion (5V24):
The first stage employed a Kartukov PRD-36 solid rocket powerplant with 2-4 sec burn duration. This design used 14 tubes of NMF-3K solid propellant and a variable cross section throat.
The second stage used a 5B83 solid propellant sustainer, constructed with a 375 mm dia steel cylindrical casing and filled with NM-4Sh nitrocellulose based propellant charge, in an annular arrangement.

 

V-600

Neva

5V24

smaller WH

Neva-M

 

Neva-M1

 

V-601

Petchora

5V27

larger WH

Petchora-2

 

Petchora-2M

 

Petchora-2T

 

Petchora-2TM

 

 



V-600 Neva



V-601 Petchora







 

SAM (S-200)

V-860 ... V-880 & 5V25V (Angara, Vega, Dubna)


 

System

Missile name

Missile code

Remark

S-200A

Angara

V-860 (PA)

 

S-200V

Vega

V-860PV

 

Vega

V-870

new solid-fuel motor

S-200VM

Vega-M

V-880 (N)

 

S-200VE

Vega-E

V-880E

export version

S-200D

Dubna

5V25V

nuclear WH

 


   



 

SAM/ABM

3M8 supersonic ramjet (Krug)

  

The missiles are launched with the aid of four solid fuel rocket motors attached to the outside of the massive missile.
Once they have burned and the missile is aloft, it fires a liquid-fuelled ramjet sustainer engine (Isayev S2.727 and later S5.15).
The Novator 3M8 missile is a Kerosene powered ramjet missile with Isopropylnitrate turbopump driven internal thrust.





 



 

SAM/ABM

S-300P, S-300F & S-300V

The earliest origins of the S-300 series lie in the mid 1960s, when the Soviet Voyska PVO and Ministry of Military Production initiated its development. The aim was to produce an area defence SAM system capable of replacing the largely ineffective S-75 and S-200 systems.


   
S-300PM (Favorit)


S-300 family


S-300P



S-300P rear



S-300VM (9M83 Gladiator)



S-300VM Antey2500




S-300VM (9M82 Giant)




S-300VM (9M83 Gladiator)

 

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"

 

FROG-1

FROG-2

FROG-1/FOG-2

FROG-3

FROG-4-1

FROG-4-2

FROG-4-3

FROG-5

FROG-6-1

FROG-6-2

FROG-7-1

FROG-7-2

The "FROG" family
 

 FROG-1

 3R2  Filin two-stage Diameter 0.612 m
  3R3  
 

3R4

  

FROG-2

3R1

 Mars

Diameter 0.324 m
  3R5    ?
  3R6  
  3R7  

FROG-3

3R8

 Luna Diameter 0.415 m

FROG-4

3R9

 Luna

FROG-5

3R10

 Luna

FROG-6

3R11

 Luna

FROG-7

9M21

 Luna-M

 one-stage

Diameter 0.544 m


FROG-7 propulsion



FROG-7-2 (Luna-M)


 



Starting system and main engine



Iraqi FROG-7-1