FIELD: solid propellant rocket engines.
SUBSTANCE: proposed method includes forming of heat protective coating on mandrels connecting of metal flange with coating and subsequent vulcanization. Ring groove with undercutting is preliminarily made on flange. Intermediate layer of heat protective coating is glued to flange surface without overlapping the groove, with subsequent upsetting and vulcanization of said layer. Ring groove is filled with heat protective coating material flush with intermediate layer, and main layer of heat protective coating is formed with subsequent vulcanization of pack.
EFFECT: improved adhesion of heat protective coating to metal flange and increased reliability of operation of heat protective coating of combustion chamber.
2 dwg
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