UR-100, 8K84, SS-11 Mod 1 Sego
UR-100M, 8K84M, SS-11 Mod 1 Sego
UR-100K 15A20, RS-10, SS-11 Mod 2 Sego
UR-100U, 15A20U, RS-10, SS-11 Mod 3 Sego
Basic data
Beginning of development: UR-100 - 30. march 1963
Design bureau: OKB-52
Manufacturer: race Chruničev, Moscow, Omský an air race and other races
Flight test:
UR-100 - 19. April 1965 - 27.October 1966
UR-100M - 23. July 1969 - 15. march 1971
UR-100K - 2. February 1971 - 24. November 1971
UR-100U - July 1971 - January 1973
Combat duty:
UR-100 - 24. November 1966
UR-100M - 1. march 1971
Entry into service:
UR-100 - 21. July 1967
UR-100K - 28. December 1971
UR-100U - 26. September 1974
Number of steps: 2
Propulsion: storable liquid propellants
Launchers:
silo (hot launch)
The number of warheads and power:
UR-100 - 1x1.1 Mt
UR-100K - 1x1.3 Mt
UR-100U - 3x350 kt (no separate guide)
Combat load:
UR-100 -760-1500 kg
UR-100K -1200 kg
UR-100U -1200 kg
Maximum range:
UR-100 - 11000 km
UR-100K - 10600 - 12000 km
UR-100U - 10600 - 12000 km
Guide: autonomous inertial
Accuracy:
UR-100 - CEP of 1.4 km, the maximum error of 5.0 km (another source CEP 2.2 km)
UR-100K - CEP 900 m, the maximum error of 5.0 km (another source CEP 2.2 km)
Length:
UR-100 - 16.7 m
UR-100K - 18.9 m
UR-100U - 19.1 m
Maximum diameter: 2.0 m
Starting weight:
UR-100 - 42.3 t
UR-100K - 50.1 t
UR-100U - 50.1 t
The mass of the fuel:
UR-100K - 45.3 t
UR-100U - 45.3 t
Oxidizer: nitrogen tetroxide
Fuel: unbalanced dimetylhydrazine (UDMH)
Thrust (sea level/vacuum): 784/876 cn (first degree), -/149 kN (the second stage)
Specific impulse (sea level/vacuum): 2744/3067 m/s (first stage), -/3200 m/s (second level)
Preparing to launch: a few minutes
Service life: several years
Source: Russian Strategic Nuclear Forces, Pavel Podvig, Oleg Bukharin, MIT Press, Cambridge, 2001
(original: Raketnije troops strategičeskogo naznačenija).
UR-100M, 8K84M, SS-11 Mod 1 Sego
UR-100K 15A20, RS-10, SS-11 Mod 2 Sego
UR-100U, 15A20U, RS-10, SS-11 Mod 3 Sego
Basic data
Beginning of development: UR-100 - 30. march 1963
Design bureau: OKB-52
Manufacturer: race Chruničev, Moscow, Omský an air race and other races
Flight test:
UR-100 - 19. April 1965 - 27.October 1966
UR-100M - 23. July 1969 - 15. march 1971
UR-100K - 2. February 1971 - 24. November 1971
UR-100U - July 1971 - January 1973
Combat duty:
UR-100 - 24. November 1966
UR-100M - 1. march 1971
Entry into service:
UR-100 - 21. July 1967
UR-100K - 28. December 1971
UR-100U - 26. September 1974
Number of steps: 2
Propulsion: storable liquid propellants
Launchers:
silo (hot launch)
The number of warheads and power:
UR-100 - 1x1.1 Mt
UR-100K - 1x1.3 Mt
UR-100U - 3x350 kt (no separate guide)
Combat load:
UR-100 -760-1500 kg
UR-100K -1200 kg
UR-100U -1200 kg
Maximum range:
UR-100 - 11000 km
UR-100K - 10600 - 12000 km
UR-100U - 10600 - 12000 km
Guide: autonomous inertial
Accuracy:
UR-100 - CEP of 1.4 km, the maximum error of 5.0 km (another source CEP 2.2 km)
UR-100K - CEP 900 m, the maximum error of 5.0 km (another source CEP 2.2 km)
Length:
UR-100 - 16.7 m
UR-100K - 18.9 m
UR-100U - 19.1 m
Maximum diameter: 2.0 m
Starting weight:
UR-100 - 42.3 t
UR-100K - 50.1 t
UR-100U - 50.1 t
The mass of the fuel:
UR-100K - 45.3 t
UR-100U - 45.3 t
Oxidizer: nitrogen tetroxide
Fuel: unbalanced dimetylhydrazine (UDMH)
Thrust (sea level/vacuum): 784/876 cn (first degree), -/149 kN (the second stage)
Specific impulse (sea level/vacuum): 2744/3067 m/s (first stage), -/3200 m/s (second level)
Preparing to launch: a few minutes
Service life: several years
Source: Russian Strategic Nuclear Forces, Pavel Podvig, Oleg Bukharin, MIT Press, Cambridge, 2001
(original: Raketnije troops strategičeskogo naznačenija).