A method and apparatus comprising a composite panel and a number of structures to reduce noise radiation from the composite panel. The composite panel has a first face sheet, a second face sheet, and a core located between the first face sheet and the second face sheet. The number of structures is a
A method and apparatus comprising a composite panel and a number of structures to reduce noise radiation from the composite panel. The composite panel has a first face sheet, a second face sheet, and a core located between the first face sheet and the second face sheet. The number of structures is associated with the first face sheet. The number of structures has a mass with a configuration to reduce a speed of waves propagating in the composite panel such that noise radiating from the composite panel is reduced.
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1. An apparatus comprising: a composite panel having a first face sheet, a second face sheet, and a core located between the first face sheet and the second face sheet; anda number of structures associated with the first face sheet, the number of structures having a mass with a configuration to redu
1. An apparatus comprising: a composite panel having a first face sheet, a second face sheet, and a core located between the first face sheet and the second face sheet; anda number of structures associated with the first face sheet, the number of structures having a mass with a configuration to reduce a speed of waves propagating in the composite panel such that noise radiating from the composite panel is reduced, the number of structures comprising a number of patches attached to an inner surface of the first face sheet, the core including a number of voids, the number of patches located in the number of voids, and the number of voids and the number of patches configured to provide gaps between the number of patches and the core. 2. The apparatus of claim 1, wherein the number of structures is configured to reduce the speed of the waves to less than about a speed of sound. 3. The apparatus of claim 1, wherein the core comprises a honeycomb. 4. The apparatus of claim 1, wherein the patches comprise elongate members. 5. The apparatus of claim 1, wherein the patches comprise a shape selected from one of a cube, a cylinder, a sphere, a pyramid, or a cuboid. 6. The apparatus of claim 1, wherein the composite panel is disposed in one of a wall, a ceiling, or a floor, of an aircraft. 7. The apparatus of claim 1, wherein the number of voids are closed with respect to the core. 8. The apparatus of claim 1, wherein the number of voids comprise a number of channels in a honeycomb structure of the core. 9. The apparatus of claim 1, wherein the core comprises a material selected from one of paper, plastic, foam, a meta aramid material, and a para aramid material. 10. A method for reducing noise radiation from a composite panel, the method comprising: causing waves to propagate through the composite panel comprising a first face sheet, a second face sheet, and a core located between the first face sheet and the second face sheet; andreducing a speed of the waves propagating through the composite panel with a number of structures associated with the first face sheet, the number of structures having a mass with a configuration to reduce the speed of the waves propagating in the composite panel such that the noise radiating from the composite panel is reduced, the number of structures comprising a number of elongate members having the mass, the number of elongate members attached to an inner surface of the first face sheet and further comprising a number of voids in the core, the number of elongate members located in the number of voids in the core and the number of voids and number of elongate members configured to provide a number of gaps between the number of elongate members and the core. 11. The method of claim 10, wherein a second number of structures is associated with the second face sheet. 12. The method of claim 10, wherein the number of structures reduces the speed of the waves to less than about a speed of sound. 13. The method of claim 10 further comprising installing the composite panel in an aircraft. 14. The method of claim 10 further comprising reducing the speed of a shear wave through the composite panel.
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