Composite material structure with integral fire protection
AssigneeThe Boeing Company
InventorsWan T. Chee, Douglas McLaren, Keith E. Therrien
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AssigneeThe Boeing Company
InventorsWan T. Chee, Douglas McLaren, Keith E. Therrien
Estimating the term…
A load-bearing composite material structure (2, 2') has a plurality of layers of composite material. Each layer includes a matrix material (4) that maintains its structural integrity at 1200.degree. F. for at least five minutes. Preferred matrix materials are polyimide resins. Outer layers that will be directly exposed to a fire are reinforced with a woven fabric (8) that is sufficiently flame resistant and has a sufficiently fine weave to prevent flame penetration at 2000.degree. F. for at least fifteen minutes. The woven fabric (8) is preferably ceramic. The rest of the layers are reinforced with a fibrous material (6) to provide the necessary structural strength. The layers may be laminate cured together to form a single, integral structure (2) or such laminates adhesively bonded to a honeycomb (12).
A load-bearing composite material structure with integral thermal and flame protection, said structure comprising a plurality of layers of composite material;
In a flight vehicle, a load-bearing composite material structure with integral thermal and flame protection, said structure being positioned to separate a designated fire zone from other portions of the vehicle, and said structure comprising a plurality of layers of composite material;
A method of providing a fire zone in a flight vehicle with a load-bearing composite material structure and of protecting said structure from high temperatures and fire in said zone, said method comprising:
Dependencies are inferred from the claim text.