FIELD: technological processes.
SUBSTANCE: invention relates to technology of making parts from composite materials, namely, shells for load-carrying structures, mainly, parts of nozzle clusters in solid propellant rocket engines. The technical result is achieved in the method of preparing a shaping mandrel for operation, and the mandrel is designed to manufacture parts from composite materials, which includes application of an anti-adhesion solution of an organosilicic lubricant in benzene on the shaping mandrel and heating in a thermal furnace. At the same time at first the shaping mandrel is heated in the thermal furnace to the temperature of 40-50°C. Then the shaping mandrel is withdrawn from the thermal furnace, the surface of the shaping mandrel is degreased, and the anti-adhesion solution is applied on it. Then the shaping mandrel is again placed into the thermal furnace, and the shaping mandrel is heated to the temperature of anti-adhesion solution hardening. Afterwards the shaping mandrel is cooled down to the room temperature.
EFFECT: development of a strong anti-adhesion coating with even thickness that is preserved during multiple use of the shaping mandrel.
3 cl, 1 dwg
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