FIELD: rocket equipment.
SUBSTANCE: invention relates to the field of rocket equipment, namely to rocket solid propellant engines (RSPE), and is intended for use in missiles of various purposes. Proposed device comprises cylindrical housing, starting and sustainer combustion chambers and diaphragm. Pipes are uniformly located along periphery of diaphragm. They are equipped with membranes on the side of starting combustion chamber. There is also a nozzle and a heat-insulating coating. Gas ducts are arranged at angle of 5…15 degrees to engine axis, and their length makes (0.1…0.2)D. Thickness of heat-shielding coating in front part of starting chamber at distance of not less than 10h is equal to 1.5…2.5 of thermal-protective coating thickness in the middle part of the starting chamber, at h=(Dd)/2, where h is gas duct outlet hole height; D is internal diameter of the combustion starting chamber at the diaphragm; d is diameter of outer circumscribing circle of gas ducts.
EFFECT: higher efficiency of RSPE.
1 cl, 1 dwg
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