Some important Soviet solid fuel missiles

Norbert Brügge, Germany

     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

 

SLBM

Complex D-6 project



Complex D-6 three-stage typ; never completed (mock-up)



 



RT-2P missile



RT-2P second + third stages


Third stage


         
                                                                                                          RT-2 second stage propulsion

RT-2

 

stage 1

stage 2

stage 3

Diameter

m

 1.84 1.48 0.98

Mass

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

Mass

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

 

77777777


RT-15

 

stage 1

stage 2

Diameter

m

 1.48 (1.84) 0.98

Mass

tons

    

Propellant

tons

 ~9.9 ~2.5

Engine design. (nozzles)

 

 15D24 (4) 15D94 (4)

Thrust (s.l.)

kN

 383.0 -

Thrust (vac)

kN

 431.5 215.7

Isp (s.l.)

Ns/kg

 2324 -

Isp (vac)

Ns/kg

 2618 2658

Burn time

sec

 60 30


 

SLBM

RT-15M (RSM-25)
 The RT-15M SLBM was developed in the KB Arsenal (Tyurin) and is not related to the RT-2 or RT-15 !


Two-stage RT-15M SLBM of complex D-7
Never used (canceled 1964)
  




 



RT-15M SLBM (with gas generator for launch)

 

RT-20

 

stage 1

stage 2

Diameter

m

 1.60 1.60

Mass

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

 647 137.3

Isp (s.l.)

Ns/kg

  ? -

Isp (vac)

Ns/kg

 2550 3231

Burn time

sec

 65 234


 

Temp-2S

 

stage 1

stage 2

stage 3

Diameter

m

 1.79 1.47 1.34 ?

Mass

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

Mass

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

Mass

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    

Mass

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

Mass

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

Mass

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

  

 

R-30

 

 stage 1 stage 2 stage 3

Diameter

m

 2.00 2.00 2.00

Mass

tons

 18.6 17.05

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

      

 


 



Bulava second stage motor

 

SLBM

R-31 (RSM-45)
 R-31    stage 1  stage 2 PBV

Diameter

m

 1.54 1.54  

Mass

tons

 15.76 6.28  

Propellant

tons

 14.16 5.70  

Engine design. (nozzles)

 

  3D17 (4)  ? (1) ? (4)

Thrust (s.l.)

kN

      

Thrust (vac)

kN

 578.6 233.4 4 x 58.8

Isp (s.l.)

Ns/kg

      

Isp (vac)

Ns/kg

 2638 2741  

Burn time

sec

 84 74 95...120


           


First stage with four-nozzle motor

   
Second stage


 

 

R-39

 

stage 1

stage 2

stage 3

Diameter

m

2.40

 

 

Mass

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

 

 

 

 

 

R-39UTTX

 

stage 1

stage 2

stage 3

Diameter

m

2.40

 

 

Mass

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

 

 

 

 

         


  
R-39


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: 1.30 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: 1.30 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 (?)



                 
 



 

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 (M)

 

S-200VE

Vega-E

V-880E

export version

S-200D

Dubna

5V25V

nuclear WH

 


                

2022: North-Korean debris (V.880E/Vega-E):


Core engine Isayev 5D67

        
Solid booster engine 5S28 !

 
  Hypersonic scramjet test vehicle "Cholod"
 

 

SAM/ABM

3M8 hupersonic scramjet (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 scramjet sustainer turbo-engine
The Novator 3M8 missile is a Kerosene powered ramjet missile with Isopropylnitrate turbopump driven internal thrust.





 



 

Tactical Missile

9M71 (Temp)



 

Tactical Missile

9M76 (TR-1, Temp-S)



9M76 (Temp-S)

 

stage 1

stage 2

Diameter

m

 1.01 1.01

Mass

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

  ~6.4

Diameter

m

 0.65

Mass

tons

 0.926

Propellant

tons

 0.790

Engine design. (nozzles)

 

 ? (1)

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

 0.89

Mass

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

7.28

Diameter

m

0.91

Mass

tons

 

Propellant

tons

 

Engine design. (nozzles)

 

? (1)

Thrust (s.l.)

kN

 

Thrust (vac)

kN

-

Isp (s.l.)

Ns/kg

 

Isp (vac)

Ns/kg

-

Burn time

sec

 

 

Tactical Missile

Ukrainian "Grom"


Grom

 

 motor

Length

m

 7.28 ?

Diameter

m

 0.91 ?

Mass

tons

 3.153

Propellant

tons

 ~2.650

Engine design. (nozzles)

 

 ? (1)

Thrust (s.l.)

kN

 171.6

Thrust (vac)

kN

 -

Isp (s.l.)

Ns/kg

 2589

Isp (vac)

Ns/kg

 -

Burn time

sec

 ~40


     

 

 

Tactical Missile

"FROG"

 

 FROG-1

FROG-2

FROG-3

FROG-4

FROG-5

  FROG-6

FROG-7

FROG-7b

 

FROG-1

3R2

Filin

Diameter 0.612 m

 

3R3

 

3R4

FROG-2

3R1

Mars

Diameter 0.324 m

 

3R5

 Mars ?

 

3R6

3R7

3R8

FROG-3

3R9

Luna

Diameter 0.415 m

FROG-4

?

FROG-5

3R10

FROG-6

3R11

FROG-7

9M21

Luna-M

Diameter 0.544 m

FROG-7b

  9M25 (?)


FROG second stage motor



FROG-7b


 
FROG-7b



Starting system and main engine



FROG-7


Iraqi FROG-7

7