Specifications | ||||||
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Mod-1 = 2 Stages |
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Mod-2 = 3 Stages |
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DIA |
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SS-LX-? " City Buster" ICBM |
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SS-LX-? FOBS |
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NATO |
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N/A |
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N/A |
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Bilateral |
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N/A |
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N/A |
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Service |
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UR-500 |
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UR-500, UR-500K |
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OKB/Industry |
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(8K82) |
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(8K82)/(8K82K) |
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Design Bureau |
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OKB-52 Acad. V.N. Chelomey |
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OKB-52 Acad. V.N. Chelomey |
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Approved |
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4/24-29/1962 |
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4/24- 29/1962 |
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Cancellation |
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ICBM 5/15/1964 |
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ICBM 5/15/1964 |
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Years of R&D |
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1961-1965 |
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1961-1967 |
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Engineering and Testing |
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1962-1965 |
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1962-1970 |
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First Flight Test |
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7/16/1965 |
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11/22/67 |
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IOC |
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N/A |
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N/A |
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Deployment Date |
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N/A |
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N/A |
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Type of Warhead |
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1 |
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1 |
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Warheads |
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Single |
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Single |
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Yield (Mt) |
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50 – 100 – 150 (35-45) |
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30 – 50 (45 –55) |
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Payload (t) |
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12.2 - 14 |
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14.0 –17.0 |
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Total length (m) |
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37 – 46.28 |
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Total length w/o warhead (m) |
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30.68 |
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44.3 |
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Missile Diameter (m) |
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7.4 with 1.6 strap-on tanks, 4.1 core tank |
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7.4 with 1.6 strap-on tanks, 4.1 core tank |
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Launch Weight (t) |
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600 |
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620 - 621.9 |
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Fuel Weight (t) |
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Range (km) |
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10,000 |
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12,000 |
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CEP (m) (Russian Sources) |
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N/A |
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N/A |
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CEP (m) (Western Sources) |
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N/A |
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N/A |
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Basing Mode |
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Hardened launch complex |
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Hardened launch complex |
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Number of Stages |
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2 |
3 |
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Canister length w/o front meters (m) |
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N/A N/A |
N/A N/A |
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Canister diameter (m) |
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N.A |
N/A |
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Booster guidance system |
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Inertial autonomous |
Inertial autonomous |
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1st stage |
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2nd stage |
3rd. Stage |
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Length (m) |
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21.07 – 21.18 Strap-on Tanks 19.9 |
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14.56 |
6.857 |
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Body diameter (m) |
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7.4 With 1.6 Strap-on Tanks, 4.1 Core Tank |
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4.1 |
4.1 |
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Fueled weight (t) |
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449.8 |
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172.1 |
46.562 |
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Dry weight (t) |
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32.5 – 34.5 |
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12.1 |
4.185 |
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Main Engine Designation |
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RD-253 (11D48)(11D43) |
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RD-0208/RD-0209 or (three)RD-0210/(one)RD-0211 |
RD-0210/RD-0211 or RD-0213/RD-0214 |
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Vernier Engine Designation |
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N/A |
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N/A |
RD-0214 Four Chamber Vernier Engine |
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Configuration |
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Cluster of Six Engines |
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Four Engine |
One Engine |
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Design Bureau |
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OKB-456, Acad. V. P. Glushko |
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OKB- 154 Acad. S. A. Kosberg |
OKB-154, Acad. S. A. Kosberg |
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Years of R&D |
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1961-1965 |
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1961-1964 |
1961 – 1967 |
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Propellants |
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Liquid |
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Liquid |
Liquid |
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Fuel |
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UDMH |
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UDMH |
UDMH |
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Oxidizer |
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N204 = Nitrogen Tetroxide |
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N204 = Nitrogen Tetroxide |
N204 = Nitrogen Tetroxide |
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Burning time (sec.) |
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127 - 130 |
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210-230 |
240 |
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Verniers Thrust Sea Level/Vacuum (Tonnes) |
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N/A |
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? |
3.21 x 4 = 12.8493 Vacuum |
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Main engines Thrust Sea Level/Vacuum (Tonnes) |
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147 – 148.8884 – 150.25 / 166.7347 |
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233.6 Vacuum |
58.4 Vacuum |
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Total Thrust Sea Level/Vacuum (Tonnes) |
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6 x 147 - 150.25 = 901.5 |
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4 x 58.4 – 59.4 = 233.6 Vacuum |
58.4 – 59.4 + 12.8493 = 71.2493 Vacuum |
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Main Engines Specific Impulse Sea Level/Vacuum (sec.) |
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284.9/310.0 |
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326.5 |
326.5 |
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Vernier Engine Specific Impulse Sea Level/Vacuum (sec.) |
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N/A |
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N/A |
? |
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Hardness |
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N/A |
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Launching Technique |
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Hot launch |
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Deployed boosters |
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N/A |
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Test Boosters |
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N/A |
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Warheads Deployed |
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N/A |
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Training Launchers |
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N/A |
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Space Booster Variant |
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SL-LX-?, SL-9/Proton/D, Proton 1-3B SL-12/Proton K, Zond, (UR-500L1), Lunar, Venera, Mars, SL-13/Proton K, Proton-4, Salyut, Mir, Proton-K |
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START |
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Locale US-Designation |
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N/A |
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N/A |