Tumanski R201-300
The Tumanski R201-300 is a Soviet two-chamber liquid rocket engine . It was developed by OKB-300 (now AMNTK "Soyuz" ( Russian АМНТК "Союз" )) under the leadership of Sergei Tumanski . Tests followed from 1961 to 1967.
The R201-300 is used by the Raduga Ch-22 missile , which is considered to be one of the most powerful anti-ship guided missiles in Russia . A special feature of the R201-300 is the very wide range of thrust from 6 to over 80 kN. For comparison: the thrust of the Isajew C5.33 engine is between 11 and 70 kN.
commitment
The R201-300 takes off 3 seconds after the rocket separates from the aircraft. 11 seconds after take-off, an ascent begins and the Ch-22 reaches Mach 3.44 regardless of the initial speed (speed of the aircraft) . Then the R201-300 changes from take-off to marching thrust of 13.7 kN and level flight begins at an altitude of 22,500 meters. As the weight of the rocket decreases rapidly, the cruising altitude increases, the air resistance decreases and the thrust-to-weight ratio increases , which means that the rocket continues to accelerate to Mach 4. Then, to prevent the rocket from overheating, the R201-300 goes into an operating mode with a thrust of 6 kN. At the end of the cruise the Ch-22 has a Mach 4.6 (about 1400 m / s) and reaches an altitude of about 30,000 m. During the flight, the on-board radar measures the bearing angle between the rocket's longitudinal axis and the target. When the angle reaches 30 degrees (at a distance of approximately 60 km from the target), the R201-300 switches off and the missile descends on a ballistic trajectory, whereby it is already over the target because of the high speed and falls almost vertically. It hits the target at a speed of around 800 m / s.
Technical specifications
| Introductory year | 1967 |
| Weight | 112 kg |
| Maximum burn time | 530 s |
| fuel | TG-02 ( unsymmetrical dimethylhydrazine (UDMH) ) |
| Oxidizer | AK-27I |
| Starting thrust (H = 10 km) | 82 kN |
| Maximum marching thrust (H = 25 km) | 13.7 kN |
| Minimum marching thrust (when approaching the target, maximum altitude) |
6 kN |