RT-21 / SS-16 SINNER
| Specifications | ||||
|---|---|---|---|---|
| DIA | SS-16 | |||
| NATO | Sinner | |||
| Bilateral | RS-14 | |||
| Service | RS-14/Temp-2S | |||
| OKB/Industry | 15Zh42 | |||
| Design Bureau | (MIT) Moscow Institute of Thermal Technology, NII-1, Acad. A. D. Nadiradze | |||
| Approved | 3/6/1966 - 3/ 4/1966 IRBM, 7/10/1969 officially | |||
| Years of R&D | 1964-73 | |||
| Engineering and Testing | 1972-74 | |||
| First Flight Test | 3/14/1972 | |||
| IOC | 2/21/1976, Halted in 1977 | |||
| Deployment Date | 3/11/1976 Late 1975 - US Estimate |
|||
| Type of Warhead | Single | |||
| Warheads | 1 | |||
| Yield (Mt) | 0.65-1.500 | |||
| Payload (t) | 0.940 | |||
| Total length (m) | 18.50 | |||
| Total length w/o Warhead (m) | 16.9 | |||
| Missile Diameter (m) | 1.79 | |||
| Launch Weight (t) | 41.5 - 44.2 | |||
| Fuel Weight (t) | ||||
| Range (km) | 9,200-10,500 | |||
| CEP (m) (Russian Sources) | 450-1,640 | |||
| CEP (m) (Western Sources) | 360-480 | |||
| Number of Stages | 3 |
| Canister length (m) | 20.01 |
| Canister length w/o front meters (m) |
|
| Canister diameter (m) | 3.22 |
| Booster Guidance System | Inertial, autonomous |
| 1st stage | 2nd stage | 3rd stage | Bus Stage | |
|---|---|---|---|---|
| Length (m) | 8.58 | 4.4 | 3.9 | |
| Body diameter (m) | 1.79 | 1.47 | 1.3 | |
| Fueled weight (t) | 26.63 | 8.7 | 8.7 | |
| Dry weight (t) | ||||
| Solid Motor Designation | ||||
| Propellants | Solid Propellant | Solid Propellant | Solid Propellant | |
| Burning time (sec.) | ||||
| Solid Motor Thrust Sea Level/Vacuum (Tonnes) | ||||
| Specific Impulse Sea Level/Vacuum (Sec.) | Vacuum | Vacuum |
| Basing Mode | Ground mobile |
| Hardness | |
| Launching Technique | Mortar Cold Launch |
| Deployed Boosters | |
| Test Boosters | |
| Warheads Deployed | |
| Deployment Sites | |
| Training Launchers | |
| Space Booster Variant | No |
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