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R-46

On 09 August 1961, Premier Nikita Khrushchev openly threatened the West with a new and terrifying weapon, the orbital H-bomb. "You do not have 50- or 100-megaton bombs, we have bombs more powerful than 100 megatons. We placed Gagarin and Titov in space, and we can replace them with other loads that can be directed to any place on Earth." Although the US had hypothesized orbital bombs, this was the first public indication that the Soviets were actively pursuing this course of action. Within a few months, however, American analysis of the threat diminished its proportions.

Specifications

   

SHB2

Mod-1 = 2 Stages

 

SHB3

Mod-2 = 3 Stages

 

DIA

 

SS-LX-? " City Buster" ICBM

 

SS-LX-? FOBS

 

NATO

 

N/A

 

N/A

 

Bilateral

 

N/A

 

N/A

 

Service

         

OKB/Industry

 

(8K68)

 

(8K68)

 

Design Bureau

 

OKB-586, (Acad. M. K. Yangel )

 

OKB-586, (Acad. M. K. Yangel )

 

Approved

 

4/16/1962

 

4/16/1962

 

Years of R&D

 

1962-1964

 

1962-1964

 

Engineering and Testing

 

Model Dynamic Testing Only

 

Model Dynamic Testing Only

 

First Flight Test

 

N/A Canceled 6/19/1964

 

N/A Canceled 6/19/1964

 

IOC

 

N/A

 

N/A

 

Deployment Date

 

N/A

 

N/A

 

Type of Warhead

 

1

 

1

 

Warheads

 

Single

 

Single

 

Yield (Mt)

 

50 100 150

 

30 50

 

Payload (t)

 

9,535 12,264

 

Orbital 10,960 11,220

 

Total length (m)

 

~56

 

~65

 

Total length

w/o warhead (m)

 

~49.87

 

~59.87

 

Missile Diameter (m)

 

3.9

 

3.9

 

Launch Weight (t)

 

383,096 - 390,400 + 12,764

 

383,735.8350 - 392,270 + 12,764 or 9,535

 

Fuel Weight (t)

         

Range (km)

 

12,000 16,000

 

12,000 16,000

 

CEP (m) (Russian Sources)

 

N/A

 

N/A

 

CEP (m) (Western Sources)

 

N/A

 

N/A

 

Basing Mode

 

Hardened launch complex

 

Hardened launch complex

 

Number of Stages

 

2

3

Canister length w/o front meters (m)

 

N/A

Canister diameter (m)

 

N/A

     

Booster guidance system

 

Inertial autonomous

   

1st stage

 

2nd stage

 

Length (m)

 

24 or (32.94 - 39.46)

 

10 10.41

~10

Body diameter (m)

 

4.0 - 3.9

 

4.0 - 3.9

~4.0 - 3.9

Fueled weight (t)

 

200,334 +77,052 = 277,386

 

62,477 +24,039 = 86,516

1,639 + 0.603 = 1639.603

Dry weight (t)

 

13,869

 

4,325

0.232

Engine Designation

 

RD-253 (11D48)(11D43)

 

RD-254

KTDU-5A

Configuration

 

Cluster of Four Engines

 

One Engine

One Engine

Design Bureau

 

OKB-456, Acad. V. P. Glushko

 

OKB-456, Acad. V. P. Glushko

OKB-2, Acad. A. M. Isayev

Years of R&D

 

1961-1965

 

1962-1964

1961 1965

Propellants

 

Liquid

 

Liquid

Liquid

Fuel

 

UDMH

 

UDMH

TG-02 = A Amine based fuel

Oxidizer

 

Nitrogen Tetroxide

 

Nitrogen Tetroxide

AK-27I = 73% HNO3 + 27%N204 = Nitrogen Tetroxide concentrated in Nitric Acid

Burning time (sec.)

 

130

 

159.7

100.3 +11.6+22.5=

134.4 total

Verniers Thrust Sea Level/Vacuum (Tonnes)

 

N/A

 

?

?

Main engines Thrust Sea Level/Vacuum (Tonnes)

 

148.8884 - 150.25 / 166.7347

 

174.7

4.638

Total Thrust Sea Level/Vacuum (Tonnes)

 

4 x 150.25 = 601.0

 

174.7

4.638

Specific Impulse Sea Level/Vacuum (sec.)

 

284.9/310.0

 

329.89

277.78

Hardness

 

N/A

Launching Technique

 

Hot launch

Deployed boosters

 

N/A

Test Boosters

 

N/A

Warheads Deployed

 

N/A

Training Launchers

 

N/A

Space Booster Variant

 

SL-LX-? SHB-2 & SHB-3 not developed

Deployment Sites

START

 

Locale US-Designation

N/A

 

N/A

Sources and Resources



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