| 摘要 |
FIELD: rocketry; construction of solid propellant engine bodies for volley fire. ^ SUBSTANCE: maintainable body of solid propellant rocket engine has cylindrical ferrule of large fineness ratio with end threaded sections and heat-protective coat on inner surface of ferrule. Body is sectional in construction with intermediate threaded sections. Inner surface of ferrule is provided with adhesive sublayer at destruction temperature below temperature of structural transformation of ferrule material. Thickness of heat-protective coat is 0.5-0.8 of thickness of ferrule; end faces of heat-protective coat are sealed-up with compound with addition of refractory oxides. Method of repair of solid propellant rocket engine body consists in preliminary disassembly of body, removal of heat-protective coat from ferrules, inspection of body components and preparation of ferrule inner surfaces. Then, adhesive sublayer is applied on inner surface at destruction temperature below temperature of structural transformation of ferrule material, after which semi-finished product of heat-protective material made from asbestos cloth and impregnated with binder is subjected to molding and heat treatment. After final molding and hardening, heat-protective coat is faced and sealed-up. Then, heat-protective coat is checked for condition. In case of single ply separation in heat-protective coat exceeding 0.0012 of coat area and total area of ply separation exceeding 0.023 and distance between ply separation lesser than 0.96 of inner diameter of ferrule, heat-protective coat is removed and is applied anew. ^ EFFECT: facilitated procedure of repair; enhanced operational reliability during protracted storage. ^ 3 cl, 3 dwg |
