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RT-25 MRBM

The RT-25 was intended to be based on the first and third stages of the RT-2. Its maximum range was supposed to be 4000-4500 kms. The governmental order issued on 04 April1961 providing for the development missiles based on solid fuel led to plans to develop this missile. The designated design bureau was Korolev's OKB-1, and the project received the industrial index 8K98 But its development never got beyond the initial stage as the Ministry of Defense suspended further development.

Specifications

     

DIA

   

NATO

   

Bilateral

   

Service

 

RT-25

OKB/Industry

 

8K97

Design Bureau

 

OKB-1/Mashinosteroeniya

Approved

 

4/4/1961

Years of R&D

 

1961-1966

Engineering and Testing

   

First Flight Test

 

No flight tests conducted

IOC

 

Not operational

Deployment Date

 

Not deployed

Type of Warhead

 

Single

Warheads

 

1

Yield (Mt)

   

Payload (t)

   

Total length (m)

 

15-16

Total length w/o warhead (m)

   

Missile Diameter (m)

 

2-1.84

Launch Weight (t)

 

40-42

Range (km)

 

4000-5000

CEP (m)

 

?

Number of Stages

 

2

Canister length (m)

   

Canister length w/o

front meters (m)

   

Canister diameter (m)

   

Booster guidance system

 

Inertial autonomous

   

1st stage

 

2nd stage

Length (m)

 

8.7

 

3.83

Body diameter (m)

 

2.0-1.84

 

1.01

Fueled weight (t)

 

34.5

   

Dry weight (t)

       

Solid Motor Designation

 

15D23

 

15D25

Design Bureau

       

Years R & D

       

Propellants

 

Solid motor

 

Solid motor

Fuel

 

N/A

 

N/A

Oxidizer

 

N/A

 

N/A

Burning time (sec.)

 

75

   

Thrust Sea Level/Vacuum (Tonnes)

 

91

   

Specific Impulse Sea Level/Vacuum (sec.)

 

 

 

 

 

         

Basing Mode mobile, silo concept

   

Hardness

   

Launching Technique Hot launch

   

Deployed boosters 0

   

Test Boosters

   

Warheads Deployed 0

   

Deployment Sites

   

Training Launchers

   

Space Booster Variant N/A

   

Sources and Resources



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