IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0641996
(2011-04-05)
|
등록번호 |
US-9902481
(2018-02-27)
|
우선권정보 |
DE-10 2010 017 822 (2010-04-20) |
국제출원번호 |
PCT/EP2011/001689
(2011-04-05)
|
§371/§102 date |
20121128
(20121128)
|
국제공개번호 |
WO2011/131290
(2011-10-27)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
11 |
초록
▼
An aircraft interior equipment component (10) with a frame (12) which comprises two rigid frame sections (14a-h) and a joint (16a-h) connecting the rigid frame sections (14a-h) to one another, and with a sheetlike section (18) which is supported by the frame (12) and is formed by a flexible and/or f
An aircraft interior equipment component (10) with a frame (12) which comprises two rigid frame sections (14a-h) and a joint (16a-h) connecting the rigid frame sections (14a-h) to one another, and with a sheetlike section (18) which is supported by the frame (12) and is formed by a flexible and/or foldable membrane (20) connected to the frame (12).
대표청구항
▼
1. An aircraft interior equipment component, comprising: a frame which comprises at least two rigid frame sections and a hinged joint connecting the rigid frame sections to one another; anda sheet-like section extending between the at least two rigid frame sections, the sheet-like section being supp
1. An aircraft interior equipment component, comprising: a frame which comprises at least two rigid frame sections and a hinged joint connecting the rigid frame sections to one another; anda sheet-like section extending between the at least two rigid frame sections, the sheet-like section being supported by the frame and formed by a single flexible or foldable membrane connected to the frame;a non-flexible or non-foldable reinforcement structure which extends over an interior surface of the sheet-like section;wherein the hinged joint is arranged on a fold line traversing the frame and the sheet-like section, about which fold line the aircraft interior equipment component, including the sheet-like section, can be bent or folded about the fold line. 2. The aircraft interior equipment component according to claim 1, wherein the aircraft interior equipment component comprises a plurality of hinged joints which connect two frame sections to one another, which hinged joints are arranged on an imaginary fold line about which the aircraft interior equipment component can be bent or folded. 3. The aircraft interior equipment component according to claim 1, wherein the hinged joints are formed by cutouts in the frame, by non-reinforced, flexible or foldable sections of the frame, or by regions of the membrane which are formed in one piece with the sheetlike section which is supported by the frame. 4. The aircraft interior equipment component according to claim 1, wherein the frame extends substantially continuously along the outer periphery of the aircraft interior equipment component. 5. The aircraft interior equipment component according to claim 1, wherein the frame, the hinged joint, the membrane or a reinforcement structure comprises a gas-impermeable material or a burn-through-resistant material. 6. The aircraft interior equipment component according to claim 1, wherein the frame, the hinged joint, the membrane or a reinforcement structure comprises a thermoplastic material selected from a group comprising polyphenyl sulfides, polyether sulfones or polyether ketones. 7. The aircraft interior equipment component according to claim 1, wherein the frame, the hinged joint, the membrane or a reinforcement structure comprises a material reinforced with glass fibres, basalt fibres, aramid fibres or carbon fibres. 8. The aircraft interior equipment component according to claim 1, wherein the frame or a reinforcement structure is connected to the membrane by a thermoplastic weld. 9. The aircraft interior equipment component according to claim 1, wherein a reinforcement structure is in the form of a grid. 10. An aircraft interior equipment component system with: a first aircraft interior equipment component which is directly fastened to a flexible first connecting element sheet,a second aircraft interior equipment component which is directly fastened to a flexible second connecting element sheet, wherein the second connecting element sheet is separate from and complementary to the first connecting element, anda coupling device configured to join the first aircraft interior component to the second aircraft interior component, wherein the coupling device is a separate component to the first and second connecting elements,wherein the first connecting element and the second connecting element are adapted, upon connection of the first aircraft interior equipment component to the second aircraft interior equipment component, to engage with one another to form a connecting seam which is impermeable to gas. 11. The aircraft interior equipment component system according to claim 10, wherein at least one further connecting element is fastened to the first aircraft interior equipment component, which further connecting element is adapted, upon connection of the first aircraft interior equipment component to a further aircraft interior equipment component or an aircraft structure, to engage with a complementary connecting element of the further aircraft interior equipment component or the aircraft structure in order to form a connecting seam which is impermeable to gas, or in that at least one further connecting element is fastened to the second aircraft interior equipment component, which further connecting element is adapted, upon connection of the second aircraft interior equipment component to a further aircraft interior equipment component or an aircraft structure, to engage with a complementary connecting element of the further aircraft interior equipment component or the aircraft structure in order to form a connecting seam which is impermeable to gas. 12. The aircraft interior equipment component system according to claim 10, wherein the first connecting element of the first aircraft interior equipment component or the second connecting element of the second aircraft interior equipment component is formed as a tongue tab of a pressure closure strip or as a groove tab of a pressure closure strip. 13. The aircraft interior equipment component system according to claim 10, wherein the first connecting element of the first aircraft interior equipment component extends along at least a partial section of an outer periphery of the first aircraft interior equipment component or in that the second connecting element of the second aircraft interior equipment component extends along at least a partial section of an outer periphery of the second aircraft interior equipment component. 14. The aircraft interior equipment component system according to claim 10, wherein the first aircraft interior equipment component is penetrated by at least one bore which is arranged in an edge region of the first aircraft interior equipment component which adjoins the outer periphery of the first aircraft interior equipment component, with a slot which reaches as far as the outer periphery of the first aircraft interior equipment component extending from the bore, or in that the second aircraft interior equipment component is penetrated by at least one bore which is arranged in an edge region of the second aircraft interior equipment component which adjoins the outer periphery of the second aircraft interior equipment component, with a slot which reaches as far as the outer periphery of the second aircraft interior equipment component extending from the bore. 15. The aircraft interior equipment component system according to claim 10, wherein the coupling device comprises: a coupling pin,a coupling eye which is arranged to receive the coupling pin, anda sealing disc, in which an opening which can be penetrated by the coupling pin is formed. 16. The aircraft interior equipment component system according to claim 10, wherein the first connecting element of the first aircraft interior equipment component or the second connecting element of the second aircraft interior equipment component each comprise a gas-impermeable material or of a burn-through-resistant material. 17. The aircraft interior equipment component system according to claim 10, wherein the first connecting element of the first aircraft interior equipment component or the second connecting element of the second aircraft interior equipment component comprises a thermoplastic material, selected from a group comprising polyphenyl sulfides, polyether sulfones or polyether ketones. 18. The aircraft interior equipment component system according to claim 10, wherein the first connecting element of the first aircraft interior equipment component is attached to the first aircraft interior equipment component by thermoplastic welding or in that the second connecting element of the second aircraft interior equipment component is attached to the second aircraft interior equipment component by thermoplastic welding. 19. The aircraft interior equipment component system according to claim 10, wherein the first connecting element of the first aircraft interior equipment component or the second connecting element of the second aircraft interior equipment component is coated with an intumescent paint. 20. The aircraft interior equipment component system according to claim 10, wherein the first aircraft interior equipment component or the second aircraft interior equipment component is an aircraft interior equipment component comprising: a frame which comprises two rigid frame sections and a joint connecting the rigid frame sections to one another, anda sheet-like section which is supported by the frame and is formed by a flexible or foldable membrane connected to the frame. 21. Use of the aircraft interior equipment component according to claim 1 as a paneling element in a cargo-hold region of a commercial aircraft. 22. An aircraft interior equipment component system with: a first aircraft interior equipment component, the first aircraft interior equipment component comprising a first connection bore and a first flexible connecting element projecting from the first aircraft interior equipment component;a second aircraft interior equipment component, the second aircraft interior equipment component comprising a second connection bore and a second flexible connecting element projecting from the second aircraft interior equipment component;a sealing disc; anda coupling system configured to pass through the first connection bore, the sealing disc, and the second connection bore, in order, and create a first gas-impermeable connection when installed;wherein:the first flexible connecting element and second flexible element are complementary and form a second gas-impermeable connection when connected;the second gas-impermeable connection comprises a seam which is configured to extend a length of an associated edge of an associated aircraft interior equipment component; andthe first aircraft interior equipment component and the second aircraft interior equipment component each comprises: a frame which comprises a plurality of rigid frame sections and a hinged joint connecting the rigid frame sections to one another, anda sheet-like section which is supported by the frame and is formed by a flexible or foldable membrane connected to the frame;further wherein the hinged joint is configured to maintain a gas impermeable barrier. 23. An assembly of panels of an aircraft interior component comprising: aircraft interior rigid panels formed of a rigid material and each panel including a first edge and a second edge opposite to the first edge of the panel;each aircraft interior rigid panel includes a first flexible sheet having a fastened sheet edge region fastened to a first surface of the rigid panel proximate to the first edge of the panel and a free sheet edge opposite to the fastened sheet edge region, wherein the free sheet edge is parallel to the first edge of the rigid panel and includes a groove, and wherein the first flexible sheet has a width extending an entire length between the first and second opposite edges of the rigid panel and extends lengthwise in a first direction from the fastened sheet edge region to the free sheet edge of the first flexible sheet;each aircraft rigid panel includes a second flexible sheet having a fastened sheet edge region fastened to a first surface of the rigid panel proximate to the second edge of the panel and a free sheet edge opposite to the fastened sheet edge region, wherein the free sheet edge is parallel to the second edge of the rigid panel and includes a tongue tab configured to attach to the groove of the first flexible sheet of an adjacent one of the aircraft interior rigid panels, and wherein the second flexible sheet has a width extending an entire length between the first and second opposite edges of the rigid panel and extends lengthwise in the first direction from the fastened sheet edge region to the free sheet edge of the second flexible sheet;each aircraft interior rigid panel includes openings proximate to the first edge and the second edge, andremovable coupling devices each extend through one of the openings proximate to the first edge of one of the aircraft interior rigid panels and through one of the openings proximate to the second edge of the adjacent rigid frame panel,wherein the assembly of panels is foldable while the coupling devices are not extending through the openings and the panels are connected by the first and second flexible sheets, andwherein the assembly of panels is rigid while the panels are connected together by the coupling devices each extend through the openings. 24. The panel as in claim 23 further comprising: a third edge and a fourth edge each extended between the first and second edges, andeach aircraft interior rigid panel includes a third flexible sheet having a fastened sheet edge region fastened to a second surface, opposite to the first surface, of the rigid panel and proximate to the third edge of the panel and a free sheet edge opposite to the fastened sheet edge region, wherein the free sheet edge is parallel to the third edge of the rigid panel and includes a groove, and wherein the third flexible sheet extends in a second direction, perpendicular to the first direction, from the fastened sheet edge region to the free sheet edge of the third flexible sheet, andeach aircraft interior rigid panel includes a fourth flexible sheet having a fastened sheet edge region fastened to the second surface of the rigid panel and proximate to the fourth edge of the panel and a free sheet edge opposite to the fastened sheet edge region, wherein the free sheet edge is parallel to the fourth edge of the rigid panel and includes a tongue tab configured to fasten to the groove of the third flexible sheet of an adjacent one of the rigid panels, and wherein the fourth flexible sheet extends in the second direction, from the fastened sheet edge region to the free sheet edge of the fourth flexible sheet. 25. The aircraft interior equipment component according to claim 1, wherein the reinforcement structure is arranged on the sheet-like section such that a folding ability of the aircraft interior equipment component about the fold lines is not affected.
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