RT-25 MRBM
| Specifications | |||
|---|---|---|---|
| DIA | |||
| NATO | |||
| Bilateral | |||
| Service | RT-25 | ||
| OKB/Industry | 8K97 | ||
| Design Bureau | OKB-1/Mashinosteroeniya | ||
| Approved | 4/4/1961 | ||
| Years of R&D | 1961-1966 | ||
| Engineering and Testing | |||
| First Flight Test | No flight tests conducted | ||
| IOC | Not operational | ||
| Deployment Date | Not deployed | ||
| Type of Warhead | Single | ||
| Warheads | 1 | ||
| Yield (Mt) | |||
| Payload (t) | |||
| Total length (m) | 15-16 | ||
| Total length w/o warhead (m) | |||
| Missile Diameter (m) | 2-1.84 | ||
| Launch Weight (t) | 40-42 | ||
| Range (km) | 4000-5000 | ||
| CEP (m) | ? | ||
| Number of Stages | 2 | |
| Canister length (m) | ||
| Canister length w/o front meters (m) |
||
| Canister diameter (m) | ||
| Booster guidance system | Inertial autonomous |
| 1st stage | 2nd stage | |||
| Length (m) | 8.7 | 3.83 | ||
| Body diameter (m) | 2.0-1.84 | 1.01 | ||
| Fueled weight (t) | 34.5 | |||
| Dry weight (t) | ||||
| Solid Motor Designation | 15D23 | 15D25 | ||
| Design Bureau | ||||
| Years R & D | ||||
| Propellants | Solid motor | Solid motor | ||
| Fuel | N/A | N/A | ||
| Oxidizer | N/A | N/A | ||
| Burning time (sec.) | 75 | |||
| Thrust Sea Level/Vacuum (Tonnes) | 91 | |||
| Specific Impulse Sea Level/Vacuum (sec.) | ||||
| Basing Mode mobile, silo concept | ||
| Hardness | ||
| Launching Technique Hot launch | ||
| Deployed boosters 0 | ||
| Test Boosters | ||
| Warheads Deployed 0 | ||
| Deployment Sites | ||
| Training Launchers | ||
| Space Booster Variant N/A |
|
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