The solid-propellant RT-15M missile was the sea-based counterpart of the RT-15 land-based missile, known in the West as the SS-14 SCAMP. Both consisted of the second and third stage of the RT-2, a prototype solid-fueled ICBM eventually deployed as the SS-13 SAVAGE. The 667 Yankee submarine, originally designed to carry the liquid-fueled R-21 missiles with the D-4 launch system, was to carry the RT-15M using the D-7 launch systems.
An order of the ministerial council on 04 April 1961 authorized the development of the system by SKB-385, under the industrial designation 4K22. However, SKB-385 was not particularly enthusiastic with the RT-15M missile, regarding liquid-propellant missiles as more promising The solid-propellant RT-15M missile, with a range of 2400 km, weighed three times more than the liquid propellant R-27 missile which had similar range capabilities.
Testing lagged substantially behind the initial schedule. Initially the missile underwent pop-up tests, with 5 launches conducted on "613" submarines. Beginning in late 1963 a series of 20 flight tests were conducted of the missile from Golf I submarines. The demonstration of underwater launch from a flooded platform was not completed until the middle of 1964. However, in July 1963 the initiation of integrated testing was postponed, pending successful results with tests of the solid-fuel RT-2 ICBM. Subsequently, development of the RT-15M missile and the D-7 launch system was halted due to the limited range and large weight and overall dimensions of the missile.
Specifications |
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DIA |
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NATO |
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Bilateral |
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Service |
RT-15M |
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OKB/Industry |
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Design Bureau |
SKB-385 |
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Approved |
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Years of R&D |
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Engineering and Testing |
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First Flight Test |
1964 |
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IOC |
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Deployment Date |
Not deployed |
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Launch system |
D-7 |
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Submarine |
667 Delta |
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Type of Warhead |
Single |
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Warheads |
1 |
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Yield (mt) |
1 |
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Payload (t) |
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Total length (m) |
10.5 |
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Total length w/o warhead (m) |
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Missile Diameter (m) |
1.5 |
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Launch Weight (t) |
50 |
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Fuel Weight (t) |
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Range (km) |
2400 |
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CEP (m) (Russian Sources) |
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CEP (m) Western Sources) |
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Number of Stages |
2 |
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Booster guidance system |
Inertial autonomous |
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1st stage |
2nd stage |
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Length (m) |
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Body diameter (m) |
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Fueled weight (t) |
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Dry weight (t) |
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Engine Designation |
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Propellants |
Solid |
Solid |
Fuel |
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Oxidizer |
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Burning time (s) |
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Verniers Thrust Sea Level/Vacuum (kn) |
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Specific Impulse (s) |
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Launching Technique |
Underwater start |
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Firing condition |
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