Structural panels for use in aircraft fuselages and other structures
First Claim
1. A structural panel comprising:
- a skin having at least one offset surface;
a first stiffener having a first flange portion mated to the skin adjacent to the offset surface;
at least a second stiffener spaced apart from the first stiffener, the second stiffener having a second flange portion mated to the skin adjacent to the offset surface; and
a support member mated to the first flange portion of the first stiffener, the second flange portion of the second stiffener, and the offset surface of the skin, wherein the offset surface is a first surface associated with a first skin thickness, wherein the skin further includes a second surface associated with a second skin thickness that is less than the first thickness, and wherein the first and second stiffeners are mated to the second surface.
1 Assignment
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Accused Products
Abstract
Structural panels for use in manufacturing aircraft fuselages and other structures are disclosed herein. In one embodiment, a structural panel configured in accordance with the invention includes a skin having at least one offset surface. The structural panel can further include at least first and second stiffeners. The first stiffener can have a first flange portion mated to the skin adjacent to the offset surface. The second stiffener can be spaced apart from the first stiffener and can similarly have a second flange portion mated to the skin adjacent to the offset surface. The structural panel of this embodiment can additionally include a support member mated to the first flange portion of the first stiffener, the second flange portion of the second stiffener, and the offset surface of the skin.
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Citations
20 Claims
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1. A structural panel comprising:
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a skin having at least one offset surface; a first stiffener having a first flange portion mated to the skin adjacent to the offset surface; at least a second stiffener spaced apart from the first stiffener, the second stiffener having a second flange portion mated to the skin adjacent to the offset surface; and a support member mated to the first flange portion of the first stiffener, the second flange portion of the second stiffener, and the offset surface of the skin, wherein the offset surface is a first surface associated with a first skin thickness, wherein the skin further includes a second surface associated with a second skin thickness that is less than the first thickness, and wherein the first and second stiffeners are mated to the second surface. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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14. A fuselage comprising:
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an interior portion; and a plurality of structural panels operably coupled together to enclose the interior portion, wherein each of the structural panels includes; a skin having at least one offset surface; a first stiffener having a first flange portion mated to the skin adjacent to the offset surface; at least a second stiffener spaced apart from the first stiffener, the second stiffener having a second flange portion mated to the skin adjacent to the offset surface; and a support member mated to the first flange portion of the first stiffener, the second flange portion of the second stiffener, and the offset surface of the skin, wherein the support member includes a mating surface without a joggle, and wherein the mating surface mates to the first flange portion of the first stiffener, the second flange portion of the second stiffener, and the offset surface of the skin. - View Dependent Claims (15)
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16. A fuselage comprising:
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an interior portion, and a plurality of structural panels operably coupled together to enclose the interior portion, wherein each of the structural panels includes; a skin having at least one offset surface; a first stiffener having a first flange portion mated to the skin adjacent to the offset surface; at least a second stiffener spaced apart from the first stiffener, the second stiffener having a second flange portion mated to the skin adjacent to the offset surface; and a support member mated to the first flange portion of the first stiffener, the second flange portion of the second stiffener, and the offset surface of the skin, wherein the support member includes a mating surface without a step, and wherein the mating surface mates to the first flange portion of the first stiffener, the second flange portion of the second stiffener, and the offset surface of the skin. - View Dependent Claims (17)
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18. A fuselage comprising:
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an interior portion; and a plurality of structural panels operably coupled together to enclose the interior portion, wherein each of the structural panels includes; a skin having at least one offset surface; a first stiffener having a first flange portion mated to the skin adjacent to the offset surface; at least a second stiffener spaced apart from the first stiffener, the second stiffener having a second flange portion mated to the skin adjacent to the offset surface; and a support member mated to the first flange portion of the first stiffener, the second flange portion of the second stiffener, and the offset surface of the skin, wherein the first flange portion of the first stiffener, the second flange portion of the second stiffener, and the offset surface of the skin form an at least approximately continuous support surface, and wherein the support member mates to the at least approximately continuous support surface. - View Dependent Claims (19, 20)
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Specification