FIELD: rocket technology.
SUBSTANCE: invention relates to rocket technology, in particular to missiles having a warhead, a main pulsating ramjet engine and an accelerating solid-fuel engine. The main engine has an input diffuser, a block of pulsating combustion chambers, an output jet nozzle. The block of pulsating combustion chambers has four fixed horizontal combustion chambers, the first and second rotating valve discs installed in front and behind the combustion chambers and connected by a common shaft, a fuel system, a control system. Rotary nozzle blades and rotating working blades mounted on a common shaft are placed between the inlet diffuser and the first valve disc. The fuel tank is connected to the combustion chambers through a fuel valve, an internal cavity of the common shaft and a fixed fuel supply unit to the combustion chambers. The control system is connected by pulse lines with a speed sensor, a fuel valve, a nozzle blade rotation device and provides synchronization of the number of revolutions of rotating valve discs, fuel supply processes and ignition in each combustion chamber.
EFFECT: simplification of the design is achieved.
1 cl, 5 dwg
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Authors
Dates
2023-02-17—Published
2022-02-03—Filed