A seal for sealing component openings in components of a means of transport, in particular for sealing openings in aircraft airfoils and tail units, comprising an inner cover connected to an outer cover via connecting members. An insert may be arranged in the component opening the outer cover being
A seal for sealing component openings in components of a means of transport, in particular for sealing openings in aircraft airfoils and tail units, comprising an inner cover connected to an outer cover via connecting members. An insert may be arranged in the component opening the outer cover being at least locally adjacent to an insert outer surface, and the inner cover being at least locally adjacent to an insert inner surface. Due to the insert arranged in the component opening, manufacturing of the seal, e.g., by an injection molding technique, may be possible, producing already at manufacturing level a high surface quality of the resulting sealing surfaces between the insert, the inner cover, as well as the outer cover.
대표청구항▼
The invention claimed is: 1. A sealed structure of an aircraft airfoil, wing, or aircraft tail unit, the sealed structure comprising a component opening and a seal, the seal comprising: an inner cover; an outer cover; a plurality of connecting members; an insert having an inner surface and an outer
The invention claimed is: 1. A sealed structure of an aircraft airfoil, wing, or aircraft tail unit, the sealed structure comprising a component opening and a seal, the seal comprising: an inner cover; an outer cover; a plurality of connecting members; an insert having an inner surface and an outer surface; wherein the plurality of connecting members connect the inner cover to the outer cover; wherein the insert is arrangeable in the component opening; wherein the outer cover abuts against at least a first region of the outer surface of the insert; wherein the outer cover is flush with the outer surface of the component to obtain a fluidically advantageous configuration of the outer surfaces of the component; and, wherein the inner cover abuts against at least a second region of the inner surface of the insert; the sealed structure further comprising a peripheral inner cutout; a second locating surface; wherein the outer cover is provided with an outer cover edge area; wherein the peripheral inner cutout is provided in the insert; wherein the peripheral inner cutout includes the second locating surface; wherein the outer cover edge area is interlockingly insertable in at least a portion of the peripheral inner cutout. 2. The sealed structure of claim 1, further comprising: at least one insert opening; wherein the at least one insert opening is provided in the insert. 3. The sealed structure of claim 1, further comprising: a peripheral outer cutout; a first locating surface; wherein the peripheral outer cutout is provided in the insert; and wherein the outer cutout includes the first locating surface. 4. The sealed structure of claim 3, wherein, in at least a portion of a third region of the first locating surface, the insert is fixed to a inner surface of the component, in particular by means of an adhesive layer. 5. The sealed structure of claim 1, wherein the insert is at least regionally flush with an outer surface of the component to obtain a fluidically convenient configuration of the outer surface of the component. 6. The structure of claim 1, further comprising: a sealing element; wherein the sealing element is arranged in at least a region between the inner cover and the insert inner surface. 7. The sealed structure of claim 1, wherein the insert is disc-shaped. 8. The sealed structure of claim 7, wherein an outer surface of the insert is at least regionally attached to an inner surface of the component, in particular by means of an adhesive layer. 9. The sealed structure of claim 7, further comprising: a sealing element; wherein the sealing element is arranged in at least a region between the inner cover and the insert inner surface. 10. A seal for sealing a component opening in an aircraft foil, wing, or tail unit, the seal comprising: an inner cover; an outer cover; a plurality of connecting members; an insert having an inner surface and an outer surface; a peripheral inner cutout; a second locating surface; wherein the plurality of connecting members connect the inner cover to the outer cover; wherein the insert is arrangeable in the component opening; wherein the outer cover abuts against at least a first region of the outer surface of the insert; wherein the outer cover is at least regionally flush with the outer surface of the component, and wherein the inner cover abuts against at least a second region of the inner surface of the insert; wherein the outer cover is provided with an outer cover edge area; wherein the peripheral inner cutout is provided in the insert; wherein the peripheral inner cutout includes the second locating surface; wherein the outer cover edge area is interlockingly insertable in at least a portion of the peripheral inner cutout.
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이 특허에 인용된 특허 (8)
Isenberg Jack M. (Bellevue WA), Apparatus and method for manufacturing laminar flow control aircraft structure.
Porter ; Jr. Frank K. (Billerica MA) Nelson Eliot D. (Acton MA) Arimento Daniel R. (Westford MA) Reidy Terence J. (Chelmsford MA), Thermally compensating insert fastener.
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