Composite laminate
First Claim
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1. A composite laminate including:
- a first layer of fibre reinforced composite material, said first layer providing primary structural strength for said composite laminate;
a second layer forming a protective skin and having a property of plastic deformation under a substantial impact; and
a third layer of impact energy-absorbing material interposed between the first and second layers and having a property of energy absorption when deformed, said second and third layers not providing primary structural strength for said composite laminate, said second and third layers in combination providing both a visible indication of a substantial impact sufficient to deform said second layer of said composite material and protection to said first layer by energy absorption of said substantial impact in said third layer.
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Abstract
A composite laminate, an aircraft skin panel, an airfoil, an aircraft and a method of manufacturing such a composite laminate are provided. The laminate includes at least three layers, namely a first layer of fiber reinforced composite material, a second layer usually metallic and usually forming a surface of the component and a third layer of impact energy-absorbing material interposed between the first and second layers, wherein the second and third layers protect the first layer from impact damage. The method of manufacture involves placing all three layers, including a said third layer of foaming adhesive, in a closed mould and foaming the adhesive to form a component to shape.
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Citations
20 Claims
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1. A composite laminate including:
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a first layer of fibre reinforced composite material, said first layer providing primary structural strength for said composite laminate; a second layer forming a protective skin and having a property of plastic deformation under a substantial impact; and a third layer of impact energy-absorbing material interposed between the first and second layers and having a property of energy absorption when deformed, said second and third layers not providing primary structural strength for said composite laminate, said second and third layers in combination providing both a visible indication of a substantial impact sufficient to deform said second layer of said composite material and protection to said first layer by energy absorption of said substantial impact in said third layer. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15)
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16. An aircraft skin panel comprising a composite laminate including:
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a first layer of fibre reinforced composite material, said first layer providing primary structural strength for said composite laminate; a metallic second layer and having a property of plastic deformation under a substantial impact; and a third layer of impact energy-absorbing material interposed between the first and second layers and having a property of energy absorption when deformed, said second and third layers not providing primary structural strength for said composite laminate, said second and third layers in combination providing both a visible indication of a substantial impact sufficient to deform said second layer of said composite material and protection to said first layer by energy absorption of said substantial impact in said third layer. - View Dependent Claims (17, 18, 19)
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20. A method of manufacturing a composite laminate including a first layer of fibre reinforced composite material, a metallic second layer and a third layer of impact energy-absorbing material interposed between the first and second layers, the method including the steps of:
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providing said pre-cured first layer of fibre reinforced composite material; placing foaming adhesive on the first layer; placing the second layer on the foaming adhesive to form a moulding assembly; placing the moulding assembly in a mould of the required form, and foaming the foaming adhesive where the expanding foam causes the second and third layers to form to the shape of the mould creating a composite laminate of the required form.
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Specification