Schemes of anti-aircraft missiles of the Reintochter series R-3:
1 - distance sensor with heat-resistant fairing; 2 - steering wheels (two pairs); 3 - rudder shafts with bearings; 4 - mechanical steering machines; 5 - electric motor steering gear; 6 - "middle building" with electrical equipment; 7 - elastic suspension frame of a gyroscope; 8 - a gyroscope; 9 - receiver and battery; 10 - oxidizer tank - Salbai; 11 - rotary intake of the oxidizer; 12 - warhead with ready-to-use striking elements; 13 - a tank with fuel - Vizol; 14 - ball balloon with compressed air; 15 - a combustion chamber with a nozzle; 16 - tail fairing made of tin; 17 - pressure reducing valve for testing the engine thrust change program; 18 - rotary fuel intake; 19 - wings of glued wood; 20 - tracer; 21 - cable channel; 22 - emphasis for the accelerator; 23 - pyrobolt accelerator; 24 - jet nozzles of the accelerator (axes pass through the central heating unit); 25 - removable accelerator cover with igniter; 26 - air brake; 27 - yoke for mounting a rocket on a launcher; 28 - igniter; 29 - charge of solid fuel; 30 - grate; 31 - starting accelerator
The accelerator consisted of a steel case with a diameter of 320 mm and a 7 mm wall. At the ends, it was closed with removable covers - flat - in front and spherical - in the back. The starting accelerator weighing 390 kg contained 170 kg of diglycol gunpowder. Within 0.9 s, he developed a thrust of the order of 143 kN (1450 kgf). Each accelerator had seven nozzles inclined to the longitudinal axis, the thrust vector of which passed through the center of gravity of the rocket. This simplified rocket balancing with different thrust accelerators. Reliable and synchronous separation of accelerators was carried out by pyro-bolts and aerodynamic brakes in the form of duralumin plates.
The missile head was borrowed from the R-1 variant and significantly upgraded. It housed a rechargeable battery, a three-phase converter that fed all the equipment, a radio control system, a non-contact Canoe fuse, a gyroscope and electric steering machines. The rudders deviated by angles of ± 10 ° at a speed of 30 °.
The launch weight of the rocket is 1830 kg, of which the second stage is 1050 kg. At the end of the active section, the missile launcher accelerated to 450 - 470 m / s, climbed more than 10,000 m and had an inclined range of 20 ... 25 km. At the beginning of 1945, an order was received: by February 20, 1945, to deliver 15 R-3F missiles to Peenemuende. But they did not manage to work out the rocket.
In parallel with work on R-3F, its solid-fuel version of R-3F was developed.
For this sample, the instrument compartment, wings, and starting boosters remained the same as those of the R-3F. To achieve a predetermined firing height of 12 km, the charge mass was required to be increased to 450 kg and the engine operating time to 40 s. To achieve these parameters, the checker must have a large arch thickness and an outer diameter of 500 mm. The press technology for producing powder bombs that was used at that time could not solve this problem. We worked out two ways to get out of this situation.
In the first case, a transition to non-volatile solvents such as trotyl was possible. At the same time, the checker was made by casting, which removed the restriction on its diameter and length.
In the second case, a checker of six to eight powder modules was used. This was a pioneering invention, which subsequently found wide application in the creation of large solid propellant solid propellant solid propellants.
The engine thrust was about 21 kN (2060 kgf) for 40 s. This allowed the 2nd stage weighing 1120 kg to maintain a high subsonic flight speed. The warhead remained unchanged and was located in the tail.Rheintochter RIII’s liquid-fuel rocket engine on display at RAF Cosford.
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