FIELD: rocketry. SUBSTANCE: solid propellant rocket engine has combustion chamber in wall of which groove is made at side of front end face into which seal is fitted, and charge restricted over outer surface is installed with ring clearance in combustion chamber. Thermal protective coating of combustion chamber wall is provided additionally with groove from side of nozzle end face. Ring made of flexibly deformable material, for instance, rubber, is fitted into groove. Cord made of flexibly deformable material is glued lengthwise the charge over helical line at angle relative to charge axis over thermoplastic inhibiting layer. Invention makes it possible to create charge of simple design providing higher operation reliability in wide temperature range at axial and radial loads. EFFECT: improved operation reliability. 2 dwg
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