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公开(公告)号：US09033272B2
公开(公告)日：2015-05-19
申请号：US13234611
申请日：2011-09-16
摘要： The present invention provides an arrangement, in particular for an aircraft or spacecraft, comprising an outer skin portion, the outside of which comes into contact with the atmosphere; a facing portion, which is arranged on the inside of the outer skin portion; a gap which is formed between the outer skin portion and the facing portion; and a device by means of which an airstream can be passed through the gap at a sufficient temperature to displace the dew point into the outer skin portion.
摘要翻译： 本发明提供了一种特别是用于飞行器或航天器的装置，包括外表面部分，其外部与大气接触; 布置在外皮部分的内侧的面对部分; 在外皮部分和相对部分之间形成的间隙; 以及能够以足够的温度将空气流过间隙的装置，以将露点移位到外皮部分中。
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2.发明授权Method for manufacturing a core composite provided with cover layers on both sides 有权在两侧设置有覆盖层的芯复合体的制造方法公开(公告)号：US08784592B2
公开(公告)日：2014-07-22
申请号：US12736301
申请日：2009-02-20
IPC分类号： B29C65/00 , B32B37/00 , B29C63/10 , B65H81/00 , B31C3/00 , B31F1/20 , B29D22/00 , B65C3/16 , A61F13/15 , B32B3/12
CPC分类号： B29C70/086 , B29D99/0021 , B29K2063/00 , B29K2105/246 , B29K2707/04 , B29L2031/608 , B32B3/12 , B32B5/024 , B32B5/026 , B32B5/26 , B32B7/045 , B32B7/14 , B32B15/14 , B32B29/02 , B32B37/0007 , B32B37/146 , B32B38/10 , B32B2260/021 , B32B2260/028 , B32B2260/046 , B32B2262/101 , B32B2262/106 , B32B2307/50 , B32B2307/718 , B32B2605/18 , Y10T156/1025 , Y10T156/103 , Y10T156/1033 , Y10T156/1051 , Y10T428/24149 , Y10T428/24157
摘要： The invention relates to a method for manufacturing flat, single or double curved core composites 1, 23 with at least one folded honeycomb core 4, 19. Prior to applying the initially not yet hardened cover layers 2, 3, 13, 22 a curable and later removable core filler material 15, 16 is introduced into full-length drainage-enabling channels 5, 6 of the folded honeycomb core 4, 19 in order to prevent telegraphing of the cover layers 2, 3, 13, 22 into the channels 5, 6 of the folded honeycomb core when arranging and/or hardening the cover layers 2, 3, 13, 22 and to produce edge-free and polygon-free surfaces of the core composite 1, 23. The core composites 1, 23 made according to the method have optimum structural mechanical properties, an ideal surface quality from the aerodynamic and aesthetic point of view, whereby a direct reprocessing of the core composites 1, 23 is possible without the need for further time and cost-intensive as well as in some circumstances weight-increasing finishing steps. With the method it is possible to manufacture in particular one-piece fuselage sections with wound core composites 1, 23 with a folded honeycomb 4, 19 as well as shell segments with laid cover layers 2, 3, 13, 22 for longitudinally divided (segmented) fuselage sections for large aircraft.
摘要翻译： 本发明涉及一种用于制造具有至少一个折叠蜂窝芯4,19的扁平，单或双弯曲芯复合材料1,23的方法。在施加最初尚未硬化的覆盖层2,3,13,22之前，可固化和 后来的可移除芯填充材料15,16被引入到折叠的蜂窝芯4,19的全长引流通道5,6中，以防止覆盖层2,3,13,22向通道5， 6，当布置和/或硬化覆盖层2,3,13,22时，折叠的蜂窝芯体6，并且产生芯复合材料1,23的无边缘和无多边形的表面。根据 该方法具有最佳的结构力学性能，从空气动力学和美学角度来看是理想的表面质量，由此可以无需进一步的时间和成本密集型以及在某些情况下对核心复合材料1 23的直接再加工 增重完成 步骤。 利用该方法，可以特别地制造具有卷绕的芯复合材料1,23的单件机身部分，其具有折叠蜂窝4,19以及具有铺设的覆盖层2,3,13,22的壳段，用于纵向分割（分段 ）大型飞机的机身部分。
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3.发明申请METHOD FOR MANUFACTURING A CORE COMPOSITE PROVIDED WITH COVER LAYERS ON BOTH SIDES AS WELL AS A CORE COMPOSITE 有权用于制作核心复合材料的方法，作为核心复合材料，在两面上提供覆盖层公开(公告)号：US20110020595A1
公开(公告)日：2011-01-27
申请号：US12736303
申请日：2009-02-20
CPC分类号： B29C70/086 , B29D99/0021 , B29K2063/00 , B29K2707/04 , B29L2031/608 , B32B3/12 , B32B3/28 , B32B5/024 , B32B5/22 , B32B5/26 , B32B7/045 , B32B7/08 , B32B7/14 , B32B37/1018 , B32B37/146 , B32B38/10 , B32B2038/008 , B32B2260/021 , B32B2260/023 , B32B2260/046 , B32B2262/0269 , B32B2262/106 , B32B2305/188 , B32B2307/50 , B32B2307/718 , B32B2311/00 , B32B2313/04 , B32B2605/18 , Y02T50/43 , Y10T428/24149
摘要： The invention relates to a method for manufacturing a core composite (1, 20, 26) having a folded honeycomb core (2, 21, 29) provided on both sides with cover layers (3, 4, 22, 23, 27, 28) wherein the folded honeycomb core (2, 21, 29) has a number of drainage-enabling channels (5). First a core filler material (16, 17) is introduced into the folded honeycomb core (2, 21, 29) at least in some areas in order to provide the filler material with sufficient stability for the subsequent sewing process. The cover layers (3, 4, 22, 23, 27, 28) which are not yet impregnated with a curable plastics material are then placed on the folded honeycomb core (2, 21, 29) and stitched to this along the base lines (6 to 8) and/or apex lines (9, 10) at least in some sections by means of a sewing thread (19). The infiltration of the overall structure with a curable plastics material is then carried out followed by hardening by applying pressure and/or temperature. The core filler material (16, 17) can to complete the process be removed again completely from the folded honeycomb core (2, 21, 29) by being dissolved and washed out or by melting and flowing out. Delamination of the cover layers (3, 4, 22, 23, 27, 28) from the folded honeycomb core (2, 21, 29) is prevented by the stitching so that core composites (1, 20, 26) manufactured by the method according to the invention can be used in the primary structure of aircraft.The invention further relates to a core composite (1, 20, 26) manufactured according to the provisions of the method.
摘要翻译： 本发明涉及一种用于制造具有折叠蜂窝芯（2,21,29）的芯复合材料（2,20,26）的方法，该复合蜂窝芯（2,21,29）在两侧设置有覆盖层（3,4,22,23,27,28） 其中所述折叠的蜂窝芯（2,21,29）具有多个引流通道（5）。 首先，至少在一些区域中，将芯填充材料（16,17）引入到折叠的蜂窝芯（2,21,29）中，以便为随后的缝制过程提供足够的稳定性的填充材料。 然后将尚未浸渍可固化塑料材料的覆盖层（3,4,22,23,27,28）放置在折叠的蜂窝芯（2,21,29）上，并沿着基线（ 6至8）和/或顶线（9,10），至少在一些部分中借助于缝纫线（19）。 然后用可固化塑料材料渗透整个结构，然后施加压力和/或温度进行硬化。 芯填充材料（16,17）可以通过溶解和洗涤或熔化和流出而完成从折叠的蜂窝芯（2,21,29）完全去除的过程。 通过缝合防止从折叠的蜂窝芯（2,21,29）中的覆盖层（3,4,22,23,27,28）的分层，使得通过该方法制造的芯复合材料（1,20,26） 根据本发明可以用于飞机的一级结构。 本发明还涉及根据该方法的规定制造的芯复合体（1,20,26）。
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公开(公告)号：US20120068012A1
公开(公告)日：2012-03-22
申请号：US13234611
申请日：2011-09-16
摘要： The present invention provides an arrangement, in particular for an aircraft or spacecraft, comprising an outer skin portion, the outside of which comes into contact with the atmosphere; a facing portion, which is arranged on the inside of the outer skin portion; a gap which is formed between the outer skin portion and the facing portion; and a device by means of which an airstream can be passed through the gap at a sufficient temperature to displace the dew point into the outer skin portion.
摘要翻译： 本发明提供了一种特别是用于飞行器或航天器的装置，包括外表面部分，其外部与大气接触; 布置在外皮部分的内侧的面对部分; 在外皮部分和相对部分之间形成的间隙; 以及能够以足够的温度将空气流过间隙的装置，以将露点移位到外皮部分中。
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5.发明申请METHOD FOR MANUFACTURING A CORE COMPOSITE PROVIDED WITH COVER LAYERS ON BOTH SIDES 有权用于制造在两面上具有覆盖层的核心复合材料的方法公开(公告)号：US20110011521A1
公开(公告)日：2011-01-20
申请号：US12736301
申请日：2009-02-20
CPC分类号： B29C70/086 , B29D99/0021 , B29K2063/00 , B29K2105/246 , B29K2707/04 , B29L2031/608 , B32B3/12 , B32B5/024 , B32B5/026 , B32B5/26 , B32B7/045 , B32B7/14 , B32B15/14 , B32B29/02 , B32B37/0007 , B32B37/146 , B32B38/10 , B32B2260/021 , B32B2260/028 , B32B2260/046 , B32B2262/101 , B32B2262/106 , B32B2307/50 , B32B2307/718 , B32B2605/18 , Y10T156/1025 , Y10T156/103 , Y10T156/1033 , Y10T156/1051 , Y10T428/24149 , Y10T428/24157
摘要： The invention relates to a method for manufacturing flat, single or double curved core composites 1, 23 with at least one folded honeycomb core 4, 19. Prior to applying the initially not yet hardened cover layers 2, 3, 13, 22 a curable and later removable core filler material 15, 16 is introduced into full-length drainage-enabling channels 5, 6 of the folded honeycomb core 4, 19 in order to prevent telegraphing of the cover layers 2, 3, 13, 22 into the channels 5, 6 of the folded honeycomb core when arranging and/or hardening the cover layers 2, 3, 13, 22 and to produce edge-free and polygon-free surfaces of the core composite 1, 23. The core composites 1, 23 made according to the method have optimum structural mechanical properties, an ideal surface quality from the aerodynamic and aesthetic point of view, whereby a direct reprocessing of the core composites 1, 23 is possible without the need for further time and cost-intensive as well as in some circumstances weight-increasing finishing steps. With the method it is possible to manufacture in particular one-piece fuselage sections with wound core composites 1, 23 with a folded honeycomb 4, 19 as well as shell segments with laid cover layers 2, 3, 13, 22 for longitudinally divided (segmented) fuselage sections for large aircraft.
摘要翻译： 本发明涉及一种用于制造具有至少一个折叠蜂窝芯4,19的扁平，单或双弯曲芯复合材料1,23的方法。在施加最初尚未硬化的覆盖层2,3,13,22之前，可固化和 后来的可移除芯填充材料15,16被引入到折叠的蜂窝芯4,19的全长引流通道5,6中，以防止覆盖层2,3,13,22向通道5， 6，当布置和/或硬化覆盖层2,3,13,22时，折叠的蜂窝芯体6，并且产生芯复合材料1,23的无边缘和无多边形的表面。根据 该方法具有最佳的结构力学性能，从空气动力学和美学角度来看是理想的表面质量，由此可以无需进一步的时间和成本密集型以及在某些情况下对核心复合材料1 23的直接再加工 增重完成 步骤。 利用该方法，可以特别地制造具有卷绕的芯复合材料1,23的单件机身部分，其具有折叠蜂窝4,19以及具有铺设的覆盖层2,3,13,22的壳段，用于纵向分割（分段 ）大型飞机的机身部分。
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6.发明授权Method for manufacturing a core composite provided with cover layers on both sides as well as a core composite 有权用于制造在两侧具有覆盖层的芯复合体以及芯复合体的方法公开(公告)号：US08926880B2
公开(公告)日：2015-01-06
申请号：US12736303
申请日：2009-02-20
IPC分类号： B31D3/00 , B32B37/14 , B29C70/08 , B32B3/12 , B29D99/00 , B32B38/10 , B32B38/00 , B29K707/04 , B29K63/00 , B29L31/60 , B32B37/10
CPC分类号： B29C70/086 , B29D99/0021 , B29K2063/00 , B29K2707/04 , B29L2031/608 , B32B3/12 , B32B3/28 , B32B5/024 , B32B5/22 , B32B5/26 , B32B7/045 , B32B7/08 , B32B7/14 , B32B37/1018 , B32B37/146 , B32B38/10 , B32B2038/008 , B32B2260/021 , B32B2260/023 , B32B2260/046 , B32B2262/0269 , B32B2262/106 , B32B2305/188 , B32B2307/50 , B32B2307/718 , B32B2311/00 , B32B2313/04 , B32B2605/18 , Y02T50/43 , Y10T428/24149
摘要： The invention relates to a method for manufacturing a core composite (1, 20, 26) having a folded honeycomb core (2, 21, 29) provided on both sides with cover layers (3, 4, 22, 23, 27, 28) wherein the folded honeycomb core (2, 21, 29) has a number of drainage-enabling channels (5). First a core filler material (16, 17) is introduced into the folded honeycomb core (2, 21, 29) at least in some areas in order to provide the filler material with sufficient stability for the subsequent sewing process. The cover layers (3, 4, 22, 23, 27, 28) which are not yet impregnated with a curable plastics material are then placed on the folded honeycomb core (2, 21, 29) and stitched to this along the base lines (6 to 8) and/or apex lines (9, 10) at least in some sections by means of a sewing thread (19). The infiltration of the overall structure with a curable plastics material is then carried out followed by hardening by applying pressure and/or temperature. The core filler material (16, 17) can to complete the process be removed again completely from the folded honeycomb core (2, 21, 29) by being dissolved and washed out or by melting and flowing out. Delamination of the cover layers (3, 4, 22, 23, 27, 28) from the folded honeycomb core (2, 21, 29) is prevented by the stitching so that core composites (1, 20, 26) manufactured by the method according to the invention can be used in the primary structure of aircraft.The invention further relates to a core composite (1, 20, 26) manufactured according to the provisions of the method.
摘要翻译： 本发明涉及一种用于制造具有折叠蜂窝芯（2,21,29）的芯复合材料（2,20,26）的方法，该复合蜂窝芯（2,21,29）在两侧设置有覆盖层（3,4,22,23,27,28） 其中所述折叠的蜂窝芯（2,21,29）具有多个引流通道（5）。 首先，至少在一些区域中，将芯填充材料（16,17）引入到折叠的蜂窝芯（2,21,29）中，以便为随后的缝制过程提供足够的稳定性的填充材料。 然后将尚未浸渍可固化塑料材料的覆盖层（3,4,22,23,27,28）放置在折叠的蜂窝芯（2,21,29）上，并沿着基线（ 6至8）和/或顶线（9,10），至少在一些部分中借助于缝纫线（19）。 然后用可固化塑料材料渗透整个结构，然后施加压力和/或温度进行硬化。 芯填充材料（16,17）可以通过溶解和洗涤或熔化和流出而完成从折叠的蜂窝芯（2,21,29）完全去除的过程。 通过缝合防止从折叠的蜂窝芯（2,21,29）中的覆盖层（3,4,22,23,27,28）的分层，使得通过该方法制造的芯复合材料（1,20,26） 根据本发明可以用于飞机的一级结构。 本发明还涉及根据该方法的规定制造的芯复合材料（1,20,26）。
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7.发明授权System and a method for fastening aircraft components in the case of a CFK-metal hybrid construction 有权在CFK-金属混合结构的情况下，系统和用于紧固飞行器部件的方法公开(公告)号：US08844868B2
公开(公告)日：2014-09-30
申请号：US12519556
申请日：2008-01-22
CPC分类号： B64C1/064 , B64C1/12 , F16B19/06 , Y10T403/18 , Y10T403/75
摘要： The present invention relates to the use of connecting elements for fastening CFK components and metal components in an aircraft or spacecraft, wherein a CFK component and a metal component can be connected to each other via at least one connecting element. The connecting element in this case is produced from an electrically non-conducting material, or has a shank and is produced from an electrically conducting or non-conducting material, wherein the shank is provided with a sleeve consisting of an electrically non-conducting material.
摘要翻译： 本发明涉及在飞行器或航天器中紧固CFK部件和金属部件的连接元件的使用，其中CFK部件和金属部件可以经由至少一个连接元件相互连接。 在这种情况下，连接元件由不导电材料制成，或具有柄，并且由导电或非导电材料制成，其中柄部设置有由非导电材料组成的套筒。
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8.发明申请FUSELAGE STRUCTURAL COMPONENT OF AN AIRCRAFT OR SPACECRAFT, WITH A FOAM LAYER AS THERMAL INSULATION 审中-公开具有作为热绝缘的泡沫层的飞机或间隙的熔敷结构构件公开(公告)号：US20100038487A1
公开(公告)日：2010-02-18
申请号：US12520892
申请日：2008-01-18
摘要： The present invention creates a fuselage structural component of an aircraft or spacecraft, with a non-load-bearing outer skin and a load-bearing inner framework structure, wherein a foam layer which effects heat insulation and/or impact protection is arranged between the outer skin and the inner framework structure.
摘要翻译： 本发明创造了一种飞机或航天器的机身结构部件，具有非承重外表皮和承重内框架结构，其中实现绝热和/或冲击保护的泡沫层布置在外部 皮肤和内部框架结构。
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9.发明申请FUSELAGE ARRANGEMENT, AIRCRAFT OR SPACECRAFT AND METHOD 审中-公开FUSELAGE ARRANGEMENT，AIRCRAFT或SPACECRAFT AND METHOD公开(公告)号：US20120074261A1
公开(公告)日：2012-03-29
申请号：US13240174
申请日：2011-09-22
CPC分类号： B64C1/18 , B64C2001/0072 , Y02T50/43 , Y10T29/49826
摘要： The present invention provides a fuselage arrangement for an aircraft or spacecraft, comprising: a skin portion which consists substantially of fibre composite material and/or of a fibre-composite/metal mixed material; a metal floor structure which is mounted on the skin portion; and a plurality of electrical system components which are interconnected in an electrically conductive manner by means of the floor structure.
摘要翻译： 本发明提供了一种用于飞机或航天器的机身装置，包括：基本上由纤维复合材料和/或纤维复合材料/金属混合材料组成的皮肤部分; 安装在皮肤部分上的金属地板结构; 以及通过地板结构以导电方式互连的多个电气系统部件。
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10.发明申请FUSELAGE OF AN AIRCRAFT OR SPACECRAFT OF CRP/METAL HYBRID CONSTRUCTION WITH A METAL FRAMEWORK 审中-公开使用金属框架对航空器或CRP /金属混合结构进行补偿公开(公告)号：US20100090061A1
公开(公告)日：2010-04-15
申请号：US12520893
申请日：2008-01-18
摘要： The present invention provides an inherently rigid fuselage of an aircraft or spacecraft comprising shell elements or fuselage barrels of CRP construction, wherein the shell elements or fuselage barrels each have an outer skin and an inner skin, which each at least partially or completely consist of a CRP material, wherein a composite core element is provided between the outer skin and the inner skin, and wherein the fuselage in the interior has a metal framework which is connected to the shell elements or fuselage barrels.
摘要翻译： 本发明提供了一种包括壳体元件或CRP结构的机身壳体的飞机或航天器的固有刚性机身，其中壳体元件或机身壳体各自具有外皮和内皮，每个至少部分或完全由 CRP材料，其中在所述外皮和所述内皮之间设置有复合芯元件，并且其中所述内部机身具有连接到所述外壳元件或机身套筒的金属框架。
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