R-36 | 8K67 | SS-9 | Scarp
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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 |
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