SOLID FUEL RAMJET ENGINE AND ENGINE OPERATION

FIELD: air engines.SUBSTANCE: solid-fuel ramjet engine contains an air intake, a housing with a solid fuel charge, a combustion chamber and an afterburner that form a flow path, and a supersonic nozzle. The air intake is directly coupled with a charge installed with a guaranteed clearance in the housing. The charge is made sectional and rests on the upper boundary of the flow path, and each section is made armored along the end and outer surfaces, except for the area adjacent to the upper boundary of the flow path. The section closest to the air intake is communicated with it and with the combustion chamber and rests on erosion-resistant stiffeners. The lengths of each section are equal to the length of the combustion chamber. The combustion chamber is connected to the afterburner and the nozzle. The end armor of the charge sections facing the air intake device is made in the form of L-shaped cuffs, and compensation wedges are installed between the upper boundary of the flow path and the charge sections. The method of operation of a solid-fuel ramjet engine is that air from the air intake device is supplied through a guaranteed gap between the body and the charge into the free volume of the body at the rear bottom, as well as directly to the surface of the charge in the body from the side of the combustion chamber and the surface fuel layer is decomposed. A mixture of decomposition products and air is fed into the afterburner, and then sent to a nozzle and a jet thrust is created.EFFECT: this design of the engine eliminates the presence of a separate gas generator housing, inlet and outlet pipes, as well as fuel pylons with nozzles in the fuel supply system to the combustion chamber and increases the energy-ballistic efficiency of the ramjet.2 cl, 3 dwg Прямоточный воздушно-реактивный двигатель на твердом топливе содержит воздухозаборник, корпус с зарядом твердого топлива, камеру сгорания и камеру дожигания, образующие проточный тракт, и сверхзвуковое сопло. Воздухозаборное устройство непосредственно сопряжено с зарядом, установленным с гарантированным зазором в корпусе. Заряд выполнен секционным и опирается на верхнюю границу проточного тракта, а каждая секция выполнена бронированной по торцевым и наружным поверхностям, кроме участка, примыкающего к верхней границе проточного тракта. Ближайшая к воздухозаборному устройству секция сообщена с ним и с камерой сгорания и опирается на эрозионно стойкие ребра жесткости. Длины каждой секции равны длине камеры сг