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RD-250

 

The R-36 rocket family

The R-36 family represented the second generation of the intercontinental ballistic missiles, ICBMs, developed in the USSR during the Cold War. It was developed in parallel with the Titan-2 ICBM in the United States.

 

The heavy-weight R-36 recieved several new and exotic features, such as multiple warheads and decoys, as well as a capability to develop an orbital speed. The latter became a base for the Fractional Orbital Bombardment System, or FOBS, where the warhead and the upper stage of the ICBM would actually enter the orbit around the Earth on its way to a target.

The development of the R-36 was officially authorized on April 16, 1962. (74) The missile was declared operational in 1966 and remained in armaments until 1978.

 

Specifications of the R-36 family:

- R-36 (8K67) (with light warhead) R-36 (8K67) (with heavy warhead) R-36 (8K69, OR-36, R-36orb) R-36P (8K67P)
Number of stages
2
2
3
2
Length
34.5 meters

32.2 meters (31.7 meters in some modifications)

32.65 - 34.5 meters
32.2 meters
Diameter
3.05 meters (with protruding elements - 3.6 meters)
3.05 meters (with protruding elements - 3.6 meters)
3.05 meters (with protruding elements - 3.6 meters)
3.05 meters (with protruding elements - 3.6 meters)
Total mass (fueled)
179 -183.89 tons
179 -183.89 tons
181,297 kilograms
183.45 tons
Fuel
Oxidizer
Nitrogen tetroxide
Nitrogen tetroxide
Nitrogen tetroxide
Nitrogen tetroxide
Mass of fuel
48.5 tons
48.5 tons
48.5 tons
48.5 tons
Mass of oxidizer
121.7 tons
121.7 tons
121.7 tons
121.7

Flight range

15,200 km
10,200 km
40,000 km
10,200 - 12,000 km
Stage 1
Stage 1 length
18.87 meters
18.87 meters
18.87 meters

18.87 meters

Stage 1 diameter
3.0 meters
3.0 meters
3.0 meters
3.0 meters
Stage 1 propellant mass:
118.9 tons
118.9 tons
118.9 tons
118.9 tons
Stage 1 dry mass
6.4 tons
6.4 tons
6.4 tons
6.4 tons
Stage 1 total mass (fueled)
122.3 tons
122.3 tons
122.3 tons
122.3 tons
1st stage propulsion

3 two-chamber RD-250 engines creating RD-251 (8D723) main engine;

1 four chamber RD-68M steering engine

3 two-chamber RD-250 engines creating RD-251 (8D723) main engine;

1 four chamber RD-68M steering engine

3 two-chamber RD-250 engines creating RD-251 (8D723) main engine;

1 four chamber RD-68M steering engine

3 two-chamber RD-250 engines creating RD-251 (8D723) main engine;

1 four chamber RD-68M steering engine

Stage 2
Stage 2 length
9.4 meters
9.4 meters
10.03 meters

12.9 meters

Stage 2 diameter
3.0 meters
3.0 meters
3.0 meters
2.2 meters
Stage 2 dry mass:
3.7 tons
3.7 tons
3.7 tons
3.7 tons
Stage 2 fueled mass:
49.3 tons
49.3 tons
49.3 tons
57.52 tons
2nd stage propulsion

1 two-chamber RD-252 engine;

1 four-chamber RD-69M engine

1 two-chamber RD-252 engine;

1 four-chamber RD-69M engine

1 two-chamber RD-252 engine;

1 four-chamber RD-69M engine

1 two-chamber RD-252 engine;

1 four-chamber RD-69M engine

Stage 3
Stage 3 (orbital) fueled mass
n/a
n/a
3,648 kg
n/a
Stage 3 (orbital) propellant mass
n/a
n/a
2 tons
n/a
Warhead type
Single 8F675: 8 Megatons
Single 8F675: 20 Megatons
Single 8F021: 5 Megatons (2.3 MT according to 98)
Three 8F676: 2.3 Megatons warheads each;
Warhead mass
3,950 kilograms
5,825 kilograms
1,410-1,700 kg
3 warheads 1,425 kg each;
Decoy mass
272 kilograms
272 kilograms
238 kilograms
401 kilograms

 

 

R-36 development team:

Element Developer Leading designer Location
Overall design
OKB-586
M. Yangel
Dnepropetrovsk
Main engine (two stages)
OKB-456
V. Glushko
Moscow
Steering engine (two stages)
OKB-586
M. Yangel
Dnepropetrovsk
The launch complex (surface)
KBTM (PKO-8)
-
Moscow
Control system
NII-885
N. A. Pilugin
Moscow
The launch complex (silo)
KBSM
E. G. Rudyak
-
Thermo-nuclear warhead
VNIIEF
B. V. Litvinov
Chelyabinsk

 

 

RD-251/252 engine specifications:

-
RD-251 (1st stage)
RD-252 (2nd stage)
Developer
OKB-456 (Moscow)
OKB-456 (Moscow)
Thrust at the sea level
241 tons
-
Thrust in vacuum
270.4 tons
92 -120 tons
Chamber pressure
85 kg per sq. cm
91 kg per sq. cm
Burn time
120 seconds
160 seconds
Height
2.88 meters
2.168 meters
Diameter
2.52 meters
2.59 meters
Dry mass
1,730 kilograms
715 -725 kilograms

 

insider content

 

The R-36 family of ballistic missiles (left to right): 8K67, 8K69, 8K67P. Credit: KB Yuzhnoe


Left to right: scale models of R-36-O, R-16 and R-36 ICBMs. Copyright © 2001 Anatoly Zak


The R-36 missile lifts off from the silo complex in Baikonur. Credit: KB Yuzhnoe


The propulsion section of the orbital warhead of the R-36-O missile. Credit: KB Yuzhnoe


The RD-252 engine, which powered the second stage of the R-36 missile. Copyright © 2002 Anatoly Zak


The MIRV warhead is being integrated with the R-36P missile in silo complex in Baikonur. Credit: KB Yuzhnoe


The warhead of the R-36 missile. Credit: KB Yuzhnoe


The dissected warhead 8F675 of the R-36 ICBM, which was retrieved after a test flight. Copyright © 2001 Anatoly Zak