| 摘要 |
FIELD: aircraft engines. SUBSTANCE: invention relates to engines of small-size unmanned aircraft. Said pulsejet engine is essentially channel opened at both ends and including air intake, thrust unit with flap valve grid, several combustion chambers and nozzle. Combustion chambers (detonation chambers), each provided with thrust unit, are arranged in parallel relative to each other in form of pack of preset form, or ring. Combustion chambers are gasodynamically coupled with each other by means of detonation transmitters. Shock wave deflectors are installed opposite to inlet holes of detonation transmitters in chambers. Port is made in wall of deflection chamber washed out by air from outside and is closed from inside by movable member. Ignition system electric primer is placed in detonation initiator communicating by one end with first detonation chamber in order of operation. In said pulsejet engine, carrying elements of flap valve grid of thrust unit can be made in form of partitions smoothly curved in longitudinal direction and dividing space of thrust unit into number of curvilinear longitudinal channels. EFFECT: improved thrust of engine. 20 cl, 7 dwg
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