R-36M Voyevoda / SS-18 SATAN
| Specifications | ||||||
|---|---|---|---|---|---|---|
| Mod | Mod-1 | Mod-2 | Mod-3 | Mod-4 | Mod-5 | Mod-6 |
| DIA | SS-18 | SS-18 | SS-18 | SS-18 | SS-18 | SS-18 |
| NATO | Satan | Satan | Satan | Satan | Satan | Satan |
| Bilateral | RS-20A | RS-20A | RS-20A | RS-20B | RS-20V | RS-20V |
| Service | R-36M | R-36M | R-36M UTTkh |
R-36MU UTTkh |
R-36M2 | R-36M2 |
| OKB/Industry | 15A14 | 15A14 | 15A14 | 15A18 | 15A18M | 15A18M |
| Design Bureau |
OKB-586 Acad. V. F. Utkin |
OKB-586 Acad. V. F. Utkin | OKB-586 Acad. V. F. Utkin |
OKB-586 Acad. V. F. Utkin |
OKB-586 Acad. V. F. Utkin | OKB-586 Acad. V. F. Utkin |
| Approved | 9/2/1969 | 9/2/1969 | 9/2/1969 | 8/16/1977 | 8/9/83 | 6/1979 ? 12/17/ 1980 ? |
| Years of R&D | 1969-1973 | 1969-1973 | 12/ 76 - 78 | 1983-1988 | 1979-1982 | |
| Engineering and Testing | 1973-1974 | 1973-1975 | 1978-1980 | 1977-1979 | 1986-88 | 1986-1990 |
| First Flight Test | 1 / / 72 1St. failure 2/21/1973 success 1 & another derivation 11-29-79 |
9/ /73, 08/ /73 & another derivation 07/ /78 |
7/ /1978 | 7/31/1977 or 10-31-1977 |
3/21/86 two failures in the flight test program |
1986 |
| IOC | 12 /25 / 1974 | 1975 | 1980 | 9/1979 ? 11-27-1979? | 12/1988 | 1990 |
| Deployment Date | 12/30/ 1975 |
12/30/ 1975 or 11/20/78 |
11/29/ 1979 |
12/17/ 1979, or 1980? |
12/1988 | 9/1991 |
| Type of Warhead |
Single | MIRV | Single | MIRV | MIRV | Single |
| Warheads | 1 | 8 | 1 | 10 | 10 | 1 |
| Yield (Mt) Russian sources |
18-20 | 0.5-1.3 | 24-25 | 0.55 | 0.55-0.75 | 20 |
| Yield (Mt) Western sources |
18-25 | 0.6-1.5 | 18-25 | 0.75-1.0 | ||
| Payload (t) | 7.2 | 7.2 - 8.8 | 7.2 - 8.8 | 8.8 | 8.8 | 8.8 |
| Total length (m) | 33.6 | 33.6 | 33.6 | 34.3 | 37.25 | 36.3 |
| Total length w/o warhead (m) | 28.5 | 28.5 | 28.5 | 28.5 -29.25 | 29.25 | 29.25 |
| Missile Diameter (m) | 3.0 | 3.0 | 3.0 | 3.0 | 3.0 | 3.0 |
| Launch Weight (t) | 209.6 -210 | 209.6 -210 | 209.6 -210 | 211.1 | 211.1 | 211.1 |
| Fuel Weight (t) | 188 | 188 | 188 | 188 | 188 | 188 |
| Range (km) | 11200 | 9250-10200 | 16.000 | 16000 11500 |
11000 15,000 |
16000 |
| CEP (m) Russian Sources |
1000 | 1000 | 1000 | 920 | 500 | 500 |
| CEP (m) Western Sources | 400-550 | 400-500 | 350 | 220-320 | 250 | ?250 |
| Number of Stages | 2 |
| Canister length (m) | 27.9 |
| Canister diameter (m) | 3.5 |
| Booster guidance system | Inertial, autonomous |
| 1st stage | 2nd stage | |
|---|---|---|
| Length (m) | 22.3 | 7.0 |
| Body diameter (m) | 3.0 | 3.0 |
| Fueled weight (t) | Total 161.5 | |
| Dry weight (t) | Total 48.1 ? 48.5 | |
| Engine Designation | RD-263 x 4 = RD-264 (11D119) for the R-36M |
RD-0228 = RD-0229 one main engine and RD-0230 four verniers for the R-36M |
| Engine Designation | RD-273 / RD-274 for the R-36MU | RD-0230 verniers for the R-36M |
| Engine Designation | N/A | RD-0255 = RD-0256 one main engine & RD-0257 four verniers for the R-36M2. |
| Design Bureau | Acad. V. P. Glushko (OKB-456) | Acad. S. A. Kosberg (OKB-154) |
| Configuration | Four RD-263Engines = RD-264 | 1 Main Engine + 4 Verniers |
| Years Of R & D | 1969-1973 = RD-263 x 4=RD-264 | 1967-1975 = RD-0228 / RD-0229 |
| Years Of R & D | 1975-1980 = RD-273 | 1967-1975 = RD-0230 |
| Years Of R & D | 1983-1989 = RD-0255 1983-1987 = RD-0256 1983-1987 = RD-0257 |
|
| Propellants | Liquid Storable | Liquid Storable |
| Fuel | UDMH | UDMH |
| Oxidizer | Nitrogen Tetraoxide | Nitrogen Tetraoxide |
| Burn Time (sec.) | ||
| Main Engines Thrust Sea Level/Vacuum (Tonnes) | 424 / 450-461 | 77 |
| Verniers Engine Thrust Sea Level/Vacuum (Tonnes) | N/A | ? |
| Main Engines Specific Impulse Sea Level/ Vacuum (sec.) | 293 / 312-318 | |
| MIRV Bus Third Stage Engine Designation for the R-36M2 | RD-869 | |
| Design Bureau (Bus) | Yuzhnoy SKB | |
| Years Of R & D (Bus) | 1983-1985 | |
| Propellants (Bus) | Liquid Storable | |
| Fuel (Bus) | UDMH | |
| Oxidizer (Bus) | Nitrogen Tetraoxide | |
| Thrust Vacuum (Tonnes) | 2.087- 0.875 | |
| Engines Specific Impulse (sec.) | 313 ? 302.3 | |
| Burn Time (sec.) | 700 |
| Basing Mode | Silo |
| Hardness | |
| Launching Technique | Cold and Solid motor |
| Deployed Boosters | |
| Test Boosters | |
| Warheads Deployed | |
| Training Launchers | |
| Space Booster Variant | Yes- SL-21?/Dnipr SS-18 derivation |
|
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