R-16 / SS-7 SADDLER
| Specifications | |||||
|---|---|---|---|---|---|
| Mod-1 | Mod-2 | Mod-3 | |||
| DIA | SS-7 | SS-7 | SS-7 | ||
| NATO | Saddler | Saddler | Saddler | ||
| Bilateral | R-16 | R-16 | R-16 | ||
| Service | R-16(U) 1 | R-16(U)1 | R-16(U) | ||
| OKB/Industry | 8K64(U) | 8K64(U) | 8K64(U) | ||
| Design Bureau | OKB-586 (Acad. M. K. Yangel) |
OKB-586 (Acad. M. K. Yangel) |
OKB-586 (Acad. M. K. Yangel) |
||
| Approved | 12/17/1956 | 05/30/1960 | 04/27/1961 | ||
| Years of R&D | 1956-1961 | ||||
| Engineering and Testing | 1961-1962 | 1961-1963 | |||
| First Flight Test | 10/24/1960 failure 02/02/1961 success |
10/10/1961 | 07/13/1962 11/22/1963 |
||
| IOC | 1961 | 1963 | |||
| Deployment Date | 11/__ /1961 | 02/05/1963, 6/15/1963 2 | |||
| Type of Warhead | Single | Single | Single | ||
| Warheads | 1 | 1 | 1 | ||
| Yield (Mt) | 3, 5-6 | 3, 5-6 | 3, 5-6 | ||
| Payload (t) | 1.475-1.5 | 2.175-2.2 | 2.175-2.2 | ||
| Total length (m) | 32.4 - 30.44/31 | 30.44/31 | 34.3 | ||
| Total length w/o warhead (m) |
|||||
| Missile Diameter (m) | 3 | 3 | 3 | ||
| Launch Weight (t) | 140.6, 141.2 | 146.6 | 148 | ||
| Fuel Weight (t) | 130 | 130 | 130 | ||
| Range (km) | 13,000, 10,500 -11,000 |
11,000 -13,000 | 10,500 | ||
| CEP (m) (Russian Sources) | 2,700 | 2,700 | 2,700 | ||
| CEP (m) (Western Sources) | 2,750-2,800 | 2,750-2,800 | 2,750-2,800 | ||
| Basing Mode | Soft site ground based | Silo based |
Silo based
(12) |
||
| Number of Stages | 2 |
| Canister length w/o front meters (m) | N/A |
| Canister diameter (m) | Canister length (m) |
| Booster guidance system | Inertial autonomous |
| 1st stage | 2nd stage | |
|---|---|---|
| Length (m) | 14.5, 16.8 | 10.8 ~12.7 |
| Body diameter (m) | 3.0 | 2.4 |
| Fueled weight (t) | Total 130.0 | |
| Dry weight (t) | Total 10.6 | |
| Engine Designation | Acad. V. P. Glushko, RD-218 (8D712) | Acad. V. P. Glushko, RD-219 (8D713) |
| Configuration | Cluster of three engines + Yuzhnoy Vernier engine RD - 68 / RD-851 |
One engine + Yuzhnoy Vernier engine RD - 69 / RD-852 |
| Design Bureau | Acad. V. P. Glushko OKB-456 | Acad. V. P. Glushko OKB-456 |
| Years of R&D | 1958-1961 | 1958-1961 |
| Propellants | Liquid Storable | Liquid Storable |
| Fuel | UDMH (heptyl) | UDMH (heptyl) |
| Oxidizer | AK-27 I, ,= 73%HNO3 + 27% N204 (NTO), Nitrogen Tetroxide concentrated in Nitric Acid N02 | AK-27 I,= 73%HNO3 + 27% N204 (NTO), Nitrogen Tetroxide concentrated in Nitric Acid N02 |
| Burning time (sec.) | 90 | 125 |
| Verniers Thrust Sea Level/Vacuum (Tonnes) | 28.850 / 38.7518 | 4.920 - 5.0173 |
| Main engines Thrust Sea Level/Vacuum (Tonnes) | 225.886 / 264.8379 | 90.1 Vacuum |
| Total Thrust Sea Level/Vacuum (Tonnes) | 254.736 -255.4/ 303.5897 Altitude | 95.02 - 95.1173 Vacuum |
| Specific Impulse Sea Level/Vacuum (sec.) | 246-247/266 altitude 290 Vacuum | 293 Vacuum |
| Hardness | |
| Launching Technique | Soft site and silo |
| Deployed boosters | 0 |
| Test Boosters | |
| Warheads Deployed | 0 |
| Training Launchers | |
| Space Booster Variant | N/A |
|
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