초록 ▼

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 s

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.

대표청구항 ▼

We 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 por

We 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. 2. The structural panel of claim 1 wherein the support member includes a mating surface without a joggle or 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. 3. The structural panel of claim 1 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. 4. The structural panel of claim 1 wherein the first stiffener further includes a first raised portion projecting away from the skin, wherein the second stiffener further includes a second raised portion projecting away from the skin, and wherein the support member further includes at least first and second openings, wherein the first raised portion of the first stiffener extends through the first opening and the second raised portion of the second stiffener extends through the second opening. 5. The structural panel of claim 1 wherein the offset surface of the skin is a first offset surface, wherein the skin further includes a second offset surface spaced apart from the first offset surface, wherein the structural panel further includes a third stiffener spaced apart from the second stiffener, the third stiffener having a third flange portion mated to the skin adjacent to the second offset surface, and wherein the support member mates to the first flange portion of the first stiffener, the second flange portion of the second stiffener, the third flange portion of the third stiffener, the first offset surface of the skin, and the second offset surface of the skin. 6. The structural panel of claim 1 wherein the support member is a sheet metal frame. 7. The structural panel of claim 1 wherein the support member has a Z-shaped cross-section. 8. The structural panel of claim 1 wherein the skin includes at least one chemically milled surface adjacent to the offset surface. 9. The structural panel of claim 1 wherein the first and second stiffeners are adhesively bonded to the skin adjacent to the offset surface. 10. The structural panel of claim 1 wherein the first and second stiffeners are mechanically fastened to the skin adjacent to the offset surface. 11. The structural panel of claim 1 wherein the first and second stiffeners are welded to the skin adjacent to the offset surface. 12. The structural panel of claim 1 wherein the second surface is offset from the first surface in a direction at least generally normal to the first surface. 13. The structural panel of claim 1 wherein the first and second surfaces are integral portions of the skin. 14. A fuselage comprising: 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. 15. The aircraft fuselage of claim 14 wherein the skin includes a composite material. 16. A fuselage comprising: 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. 17. The aircraft fuselage of claim 16, further comprising a plurality of passenger seats positioned in the interior portion ranging in number from about 100 seats to about 700 seats, and wherein the skin and stiffeners include composite materials. 18. A fuselage comprising: 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. 19. The aircraft fuselage of claim 18 wherein the plurality of structural panels are operably coupled together to form an exterior portion of a passenger cabin. 20. The aircraft fuselage of claim 18, further comprising a plurality of passenger seats positioned in the interior portion ranging in number from about 100 seats to about 700 seats.