Abstract: The connection between the traditional airborne missile solid engine wing/suspension structure and the combustion chamber shell is generally formed by welding the wing/suspension base to the shell compartment section or connecting skirt column section, and the bearing limit of the suspension/wing structure is determined by the weld strength. However, the traditional molding method is no longer suitable for the molding of composite material combustion chamber shells with metal suspension structures, and the margin for further lightweight and cost reduction is limited. Based on the engineering development of some advanced forming technologies and in response to the above issues, this article proposes a new integrated forming technology for composite combustion chamber shells with external components from the aspects of shell structure design and forming. It compares and analyzes the design and forming process with conventional metal combustion chamber shells with external components, verifies the preparation of composite shells, and conducts relevant bearing performance and forming economy analysis, the feasibility of this molding technology has been verified, providing a new approach for the subsequent molding of composite material shells in the combustion chambers of airborne/shipborne missiles.

Key words: composite material shell with external components, integrated design and molding