METHOD OF FORMATION HEAT-PROTECTIVE COATING FOR SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 1996 - IPC

FIELD: combustion chambers of rocket engines; heat-protective coatings of solid-propellant rocket engines having metal casing. SUBSTANCE: heat-protective coating on base of rubber is applied on inner side of combustion chamber to protect it against burn-out. Erosion-resistant underlayer made, for example, from carbon fabric is applied on hollow mandrel after which heat-insulating layer is applied by winding the rubber-like cord; then layers are subjected to pressing at simultaneous supply of heat both within and without mandrel followed by cooling which is effected by feeding the cooling agent inside mandrel. Heat-protective sleeve thus formed is removed from mandrel and inserted in combustion chamber. Then mandrel made of material whose linear expansion coefficient exceeds that of combustion chamber by 1.5 to 2.5 times is inserted in combustion chamber and coating is subjected to vulcanization. EFFECT: enhanced reliability. 4 dwg