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US 11,260,619 B2Granted
Composite panel systems and methods
AssigneeThe Boeing Company
InventorLon E. Switzer
Life of this patent
Estimating the term…
Abstract
A composite panel assembly and method of forming the same includes a core, an inner skin coupled to a first side of the core, and an outer skin coupled to a second side of the core. A peripheral edge including portions of the core, the inner skin, and the outer skin, is compressed to close a path into the core.
Claims21
A composite panel assembly, comprising:
- a core;
- an inner skin coupled to a first side of the core;
- a decorative laminate coupled to the inner skin;
- and
- an outer skin coupled to a second side of the core,
- wherein a peripheral edge including portions of the core, the inner skin, the decorative laminate, and the outer skin, is compressed.
3 more elements
A method of forming a composite panel assembly, the method comprising:
- providing a core;
- coupling an inner skin to a first side of the core;
- coupling a decorative laminate to the inner skin;
- coupling an outer skin to a second side of the core;
- and
- compressing a peripheral edge including portions of the core, the inner skin, the decorative laminate, and the outer skin.
3 more elements
A composite panel system, comprising:
- a first composite panel assembly;
- and
- a second composite panel assembly, wherein each of the first composite panel assembly and the second composite panel assembly comprises:
- a core;
- an inner skin coupled to a first side of the core;
- a decorative laminate coupled to the inner skin;
- and
- an outer skin coupled to a second side of the core,
- wherein a peripheral edge including portions of the core, the inner skin, the decorative laminate, and the outer skin, is compressed.
6 more elements
Dependencies are inferred from the claim text.