FIELD: rocketry.
SUBSTANCE: invention can be used for volley fire rocket engines. Proposed method of removing thermal protective coating of rocket engine body includes thermal and mechanical actions, destruction of glue layer by heating of metal wall of body at speed of 40-60°C/s by high frequency currents to tempering temperature after hardening. Heating is effected in local ring zone, 30-40 mm wide, at rotation of body around its axis at angular speed of 20-20 rmp and shifting of single-turn two chamber water cooled inductor along axis of body at speed depending on thickness of body wall. Water is fed into inductor at heating through closed chamber, and at cooling, through spraying chamber. At cooling, inductor is repeatedly moved along axis without switching on heating. Invention provides removal of thermal protective coating on asbestos-phenol-rubber composition with flue layer at minimum emission of harmful gases and removal of said gases from zone of emission.
EFFECT: increased efficiency in process of removal of thermal protective coating from rocket engine body.
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