FIELD: rocket engines. SUBSTANCE: casing of solid-propellant rocket engine is made from composite materials and is lined with thermal protective coat. Casing is provided with load-bearing envelope with flanges and elastoflexible gaskets laid between them. Casing contains also circular band zones of attachment located between thermal protective coat and inner surfaces of flanges which overlap edges of flanges. Circular band zone are made between elastoflexible gaskets and outer surfaces of flanges. Circular contact cavities are formed inside elastoflexible gaskets. Reinforcing asbestos cloth is mounted in thermal protective coat in area of bottom in such position that angles between directions of threads and meridional generatrices of casing ranges from 30 to 60 deg. EFFECT: enhanced deformability of casing in area of bottoms; enhanced resistance to burn-outs; enhanced serviceability and reliability. 3 dwg
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