FIELD: missiles.
SUBSTANCE: invention relates to rocket engineering, specifically to multi-mode solid-propellant rocket engines, and can be used in making missiles. Multimode rocket engine comprises cylindrical housing, intermediate bottom dividing it into combustion chambers, solid fuel and output nozzle. Intermediate bottom is made of hemispherical perforated metal shell bent towards the second combustion chamber. On the side of the second combustion chamber, the perforated metal shell is reinforced by radial stiffeners in amount of not more than 4 pieces with heat-shielding straps. On the side of the first combustion chamber, the perforated metal shell is covered with metal foil and membrane with heat-protective coating function, which are hermetically fixed to the coating on the adhesive bond by its outer and inner diameters. Into central hole of intermediate bottom ignition device is installed.
EFFECT: invention allows providing uniform ignition of rocket engine charge without reducing intermediate bottom strength and improving operating reliability of such engine.
1 cl, 5 dwg
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