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