초록 ▼

A substantially strong, lightweight load bearing window for use in a mobile platform, for example, an aircraft. The window includes a rim portion having a carbon reinforced resin structure and a transparent portion having a fiberglass reinforced resin structure. A plurality of holes are formed in th

A substantially strong, lightweight load bearing window for use in a mobile platform, for example, an aircraft. The window includes a rim portion having a carbon reinforced resin structure and a transparent portion having a fiberglass reinforced resin structure. A plurality of holes are formed in the rim portion for enabling a plurality of connectors to be inserted therethrough. The rim portion has a smaller cross sectional area (i.e., thickness) than the transparent portion such that the rim portion is adapted to fit behind a skin of an aircraft, the transparent portion is adapted to be flush with the skin of the aircraft. The connectors fix the window to the skin of the aircraft. The window effectively forms a strong, structurally integral portion of the skin.

대표청구항 ▼

What is claimed is: 1. A composite, load bearing window for use in a mobile platform comprising: a composite rim portion having a first reinforced resin structure; a composite, transparent window portion having a second reinforcing structure, the rim portion being integrally formed with the transpa

What is claimed is: 1. A composite, load bearing window for use in a mobile platform comprising: a composite rim portion having a first reinforced resin structure; a composite, transparent window portion having a second reinforcing structure, the rim portion being integrally formed with the transparent window portion; a plurality of openings located in said rim portion for accepting a plurality of connectors; and wherein said rim portion has a smaller cross sectional area than said transparent window portion such that said rim portion is adapted to fit adjacent a flange free opening in a skin of the mobile platform, said transparent window portion being adapted to be generally flush with the skin of the mobile platform, and wherein said connectors are adapted to be fixed to the skin of the aircraft. 2. The load bearing window of claim 1, wherein said plurality of connectors extend around said rim portion in a double row. 3. The load bearing window of claim 1, wherein said load bearing window is adapted to be used as a modular patch in an aircraft to replace an existing aircraft window. 4. The load bearing window of claim 1, wherein said rim portion comprises carbon as said reinforcing structure. 5. The load bearing window of claim 1, wherein said transparent portion comprises fiberglass and resin, said fiberglass and said resin having approximately equal indices of refraction. 6. An aircraft having a composite load, bearing window comprising: an airframe skin having an inner, an outer surface and a flange free opening; a composite, load bearing window mounted within said airframe skin, said load bearing window comprising: an integrally formed, composite peripheral rim portion having a reinforced resin structure that is not transparent; a composite, transparent window portion having a reinforced resin structure integrally formed with the rim portion; and a plurality of holes located in said rim portion for receiving a plurality of connectors; wherein said plurality of connectors are secured to said airframe skin such that said rim portion fits to said inner surface adjacent said flange free opening, and said transparent window portion is approximately flush with said outer surface; wherein said connectors secure said composite load bearing window to said airframe skin and loads are transferred through said airframe skin, through said rim portion and into said composite, transparent window portion; wherein said rim portion rests against said inner surface of said airframe skin; a first seal mounted between said outer surface of said airframe skin and said composite transparent window portion of said composite load bearing window; and a secondary seal mounted between said inner surface of said airframe skin and said rim portion of said composite load bearing window. 7. The composite load bearing window of claim 6, wherein said plurality of connectors extend around said rim portion in a double row. 8. The composite load bearing window of claim 6, wherein said composite load bearing window is adapted to be used as a modular patch in the aircraft to replace an existing aircraft window. 9. The composite load bearing window of claim 6, wherein said rim portion comprises carbon as a reinforcing component. 10. The composite load bearing window of claim 6, wherein said transparent portion is reinforced with fiberglass, and said fiberglass and said resin have approximately equal indices of refraction.