The Boeing Company

Paul Gooch

Brad James Reeves

Systems and methods are provided for blade-and-slot panel affixation. One embodiment is a method. The method includes cutting a first slot into a first composite panel that includes a core between two facesheets. The first slot penetrates through the core of the first composite panel. The method also includes cutting a second slot into a second composite panel that includes a core between two facesheets. The second slot penetrates through a facesheet of the second composite panel as well as the core of the second composite panel. The method further includes inserting a blade into the first slot, and inserting the blade into the second slot.

Blade-and-slot joints that unite composite panels via internal blades

A method and apparatus for forming a joint between a first composite structure and a second composite structure. A number of tab sections may be formed at an end of the first composite structure. The first composite structure may comprise a first skin, a second skin, and a core located between the first skin and the second skin. A tab section in the number of tab sections may comprise a first skin section of the first skin, a second skin section of the second skin, and a core section of the core. A portion of the core section may be removed from each tab section to form a number of tabs at the end of the first composite structure. The first composite structure may be attached to the second composite structure using the number of tabs to form the joint between the first composite structure and the second composite structure.

Method and apparatus for joining composite structures

A method of fabricating a self-locking joint in a panel structure. The method provides a panel structure having at least two face sheets and a core portion sandwiched therebetween. The method further fabricates in a first portion of the panel structure at least one mortice opening having self-locking end portions. The method further fabricates on a second portion of the panel structure at least one tenon extension having flexible self-locking members. The method further interlocks the flexible self-locking members of the at least one tenon extension with the self-locking end portions of the at least one mortice opening to form a self-locking joint in the panel structure.

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Everett, WA, United States of America

Paul Gooch