Combustion chamber for rocket motor and its assembling method

Claim 1

Combustion chamber for rocket motor of the type comprising two domes, interconnected by a cylindrical shell, each of said domes and the intermediate shell being produced from a filamentary composite material, wherein each dome comprises a conical skirt section of which the external face is joined over at least part of its length to the inner face of the shell, via a split cylindro-conical connection ring, each of said rings having a substantially cylindrical outer surface and an inner surface of which at the portion of the length opposite said conical skirt section is substantially conical in shape, thus forming at the extremities of said rings a thinner end and a thicker end respectively, said cylindrical outer surface and said inner surface of said rings having a common central axis, the conicity of the conical portion of the inner surface of said rings being equal to the conicity of the conical skirt section, said rings being situated in the assembled combustion chamber between the inner face of said cylindrical shell and the conical skirt section of said domes the dome, shell and ring being secured together by adhesive bonding.