Mechanical and insulating connection between a nozzle and the filament-wound casing of the combustion chamber of a solid propellant rocket motor

In a solid propellant rocket motor having a filament-wound casing assembly constituting a wall for a combustion chamber and a hot nozzle made from a heat conducting refractory material, the casing assembly including an outer filament-wound casing and an inner heat protective layer, a mechanical and insulating connection between the casing assembly and the nozzle, said connection comprising:

• a single connecting ring formed from a low density insulating material having a sufficiently low heat conductivity for protecting the casing assembly from the heat of the nozzle, said connecting ring being substantially resistant to mechanical shocks and thermal stresses, said connecting ring including a first annular surface in facing relation to the combustion chamber, a second annular surface in facing relation to the inner surface of the outer casing adjacent an opening therein for receiving the nozzle, and a third annular surface in contact with an outer surface of the nozzle for connecting thereto;
• and
• a layer of bonding material interdigitated between the second annular surface of the connection ring and the facing inner surface of the outer casing for bonding said connecting ring directly to the casing assembly whereby said connecting ring and said layer of bonding material provide the sole mechanical connection between the outer casing and the nozzle to thereby militate against the transfer of heat energy.