초록 ▼

The deformation characteristic of a profiled aerodynamic aircraft component is improved by forming ridges (6, 7) in the top and bottom skin (4, 5) of the component. Two ridges (6, 7) form a pair in which the bottom ridge (7) is at least partially nested in the top ridge (6) to the extent that the ri

The deformation characteristic of a profiled aerodynamic aircraft component is improved by forming ridges (6, 7) in the top and bottom skin (4, 5) of the component. Two ridges (6, 7) form a pair in which the bottom ridge (7) is at least partially nested in the top ridge (6) to the extent that the ridges are bonded to each other in a trailing edge area (9) of the component along a width (W) extending in the depth or y-direction of the component. The ridges taper from the trailing edge area (9) toward the leading edge (1) of the component and the forward ridge end (6A, 7A) merges into the respective skin at a point spaced form the leading edge. The ridges function as ribs and strengthen the component while making it flexible for minimizing the introduction of compulsion forces when the component is deflected.

대표청구항 ▼

1. An aircraft component comprising an inner structure, a leading edge (1) and a trailing edge (2), a top skin (4) supported by said inner structure between said leading and trailing edges, a bottom skin (5) supported by said inner structure between said leading and trailing edges, said aircraft com

1. An aircraft component comprising an inner structure, a leading edge (1) and a trailing edge (2), a top skin (4) supported by said inner structure between said leading and trailing edges, a bottom skin (5) supported by said inner structure between said leading and trailing edges, said aircraft component having a longitudinal axis (3) extending from end to end of said aircraft component and a depth axis (8) extending perpendicularly to and between said leading edge (1) and said trailing edge (2), said aircraft component further comprising at least one first ridge (6) bulging outwardly in said top skin (4) and at least one second ridge (7) bulging in said bottom skin (5) toward said at least one first ridge (6), wherein said first and second ridge begins in an area (9) of said trailing edge (2) and extends toward said leading edge in the direction of said depth axis (8), each of said first and second ridges (6, 7) having a height (H) that is largest in said trailing edge area (9), said height (H) of said first and second ridges (6, 7) diminishing from said trailing edge area (9) toward said leading edge (1).2. The aircraft component of claim 1, wherein said aircraft component has a depth (t) extending from said leading edge (1) to said trailing edge (2) in a direction of said depth axis (8), said first and second ridges (6, 7) having a ridge length (L) in said depth direction, said ridge length (L) being shorter than one half of said depth (t).3. The aircraft component of claim 1, wherein said first and second ridges (6, 7) begin at said trailing edge (2) and end centrally in said aircraft component.4. The aircraft component of claim 1, wherein said aircraft component has a depth (t) extending from said leading edge (1) to said trailing edge (2) in a direction of said depth axis (8), said first and second ridges (6, 7) having a ridge length (L) in said depth direction, said ridge length (L) being longer than one half of said depth (t).5. The aircraft component of claim 1, wherein said first and second ridges (6 and 7) taper toward a respective ridge end (6A, 7A) that is spaced from said leading edge (1) in the direction of said depth axis (8), whereby one ridge end (6A) is positioned in a spar area (15) of said aircraft component in said top skin (4) and the other ridge end (7A) is positioned in said bottom skin (5), respectively.6. The aircraft component of claim 1, comprising a trailing edge area (9) extending along said trailing edge (2) and toward said leading edge, said first ridge (6) having a first ridge portion (6B) in said trailing edge area (9), said second ridge (7) having a second ridge portion (7B) in said trailing edge area (9), said first and second ridge portions (6B, 7B) having a fitting, nesting configuration so that said second ridge portion (7B) fits snugly into said first ridge portion (6B) in said trailing edge area (9) along a width (W).7. The aircraft component of claim 6, further comprising an interconnection between said first ridge portion (6B) and said second ridge portion (7B) in said trailing edge area (9).8. The aircraft component of claim 7, wherein said interconnection is a rigid, permanent connection.9. The aircraft component of claim 8, wherein said rigid, permanent connection is an adhesive bond connection along said width (W).10. The aircraft component of claim 5, wherein at least one of said ridge ends (6A, 7A) is positioned on a line (L1) extending perpendicularly to said depth axis (8) in said spar area (15).11. The aircraft component of claim 10, wherein both ridge ends (6A, 7A) are positioned on said line (L1).12. The aircraft component of claim 1, wherein said first ridge (6) and said second ridge have a cross-section configuration resembling a parabola.13. The aircraft component of claim 12, wherein said parabola opens downwardly in a wing or elevator component or backwardly in a tail fin component.14. The aircraft component of claim 12, wherein said first and second ridges have the configuration of a longitudinal portion of an aerodynamically formed cone.15. The aircraft component of claim 5, wherein said ridge ends (6A, 7A) are formed as pointed tips.16. The aircraft component of claim 1, comprising a plurality of said at least one first ridge (6) and a corresponding plurality of said at least one second ridge (7) to provide pairs of first and second ridges, wherein a second ridge of a pair is at least partly nested in a first ridge in said pair of ridges, and wherein said pairs of ridges are spaced from each other along said aircraft component at predetermined spacings along said longitudinal axis.17. The aircraft component of claim 16, wherein said predetermined spacings are equal to one another.18. The aircraft compound of claim 16, wherein said predetermined spacings are unequal to one another.19. The aircraft component of claim 16, wherein both first and second ridges forming a pair have cross-sectional configurations which open downwardly or backwardly.20. The aircraft component of claim 1, wherein each of said first and second ridges has an open end that begins at said trailing edge (2) or is spaced from said trailing edge.21. The aircraft component of claim 1, wherein said aircraft component is any one component of the following aircraft components: a wing, a wing flap, an aileron, a rudder fin, a rudder tab, and an elevator flap.22. The aircraft component of claim 1, wherein said first ridge (6) comprises a first ridge portion (6B) in said trailing edge area (9), a first ridge end (6A) opposite said first ridge portion (6B) and a first elongated ridge section (6C, 6D, 6E) between said first ridge end (6A) and said first ridge portion (6B), wherein said second ridge comprises a second ridge portion (7B) in said trailing edge area (9), a second ridge end (7A) opposite said second ridge portion (7B), and a second elongated ridge section (7C, 7D, 7E) between said second ridge end (7A) and said second ridge portion (7B), wherein said first ridge section (6C, 6D, 6E) has a first ridge line (6C), wherein said second ridge section has a second ridge line (6C), and wherein a spacing (VS) between said first and second ridge lines (6C, 7C) increases in a direction toward said first and second ridge ends (6A, 7A).23. The aircraft component of claim 22, wherein said first ridge portion (6B) and said second ridge portion (7B) are intimately bonded to each other along a width (W) of said trailing edge area (9).