公开(公告)号：US20130009008A1

公开(公告)日：2013-01-10

申请号：US12638423

申请日：2009-12-15

申请人： Philipp Westphal ,  Wolf-Dietrich Dolzinski ,  Thorsten Roming ,  Thorsten Schroeer ,  Dieter Kohlgrueber ,  Marius Luetzenburger

发明人： Philipp Westphal ,  Wolf-Dietrich Dolzinski ,  Thorsten Roming ,  Thorsten Schroeer ,  Dieter Kohlgrueber ,  Marius Luetzenburger

IPC分类号： B64C1/06

CPC分类号： B64C1/061 ,  B64C1/18 ,  B64C2001/0072 ,  Y02T50/43

摘要： The present invention provides a fuselage structure for an aircraft or spacecraft with an outer skin. The fuselage structure comprises a rib element for stiffening the outer skin and ad cross member element. Here the rib element is bent in the shape of an arc to correspond to an inner contour of the outer skin. The cross member element connects two arc sections of the rib element transversely to each other. The cross member element has a higher strength than the rib element. From another point of view the invention provides an aircraft with such a fuselage structure.

摘要翻译： 本发明提供一种具有外皮的飞机或航天器的机身结构。 机身结构包括用于加强外皮和横向构件元件的肋元件。 这里，肋元件弯曲成弧形，以对应于外皮的内轮廓。 横向构件元件将肋元件的两个弧形部分横向彼此连接。 横向构件元件具有比肋元件更高的强度。 从另一观点出发，本发明提供了一种具有这种机身结构的飞行器。

公开(公告)号：US08439307B2

公开(公告)日：2013-05-14

申请号：US12638423

申请日：2009-12-15

申请人： Philipp Westphal ,  Wolf-Dietrich Dolzinski ,  Thorsten Roming ,  Thorsten Schroeer ,  Dieter Kohlgrueber ,  Marius Luetzenburger

发明人： Philipp Westphal ,  Wolf-Dietrich Dolzinski ,  Thorsten Roming ,  Thorsten Schroeer ,  Dieter Kohlgrueber ,  Marius Luetzenburger

IPC分类号： B64C1/18

CPC分类号： B64C1/061 ,  B64C1/18 ,  B64C2001/0072 ,  Y02T50/43

摘要： The present invention provides a fuselage structure for an aircraft or spacecraft with an outer skin. The fuselage structure comprises a rib element for stiffening the outer skin and ad cross member element. Here the rib element is bent in the shape of an arc to correspond to an inner contour of the outer skin. The cross member element connects two arc sections of the rib element transversely to each other. The cross member element has a higher strength than the rib element. From another point of view the invention provides an aircraft with such a fuselage structure.

摘要翻译： 本发明提供一种具有外皮的飞机或航天器的机身结构。 机身结构包括用于加强外皮和横向构件元件的肋元件。 这里，肋元件弯曲成弧形，以对应于外皮的内轮廓。 横向构件元件将肋元件的两个弧形部分横向彼此连接。 横向构件元件具有比肋元件更高的强度。 从另一观点出发，本发明提供了一种具有这种机身结构的飞行器。

公开(公告)号：US09033272B2

公开(公告)日：2015-05-19

申请号：US13234611

申请日：2011-09-16

申请人： Wolf-Dietrich Dolzinski ,  Michael Kolax

发明人： Wolf-Dietrich Dolzinski ,  Michael Kolax

IPC分类号： B64C1/40 ,  B64C1/06 ,  B64C1/12

CPC分类号： B64C1/067 ,  B64C1/12 ,  B64C1/40 ,  Y02T50/46

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。

公开(公告)号：US08784592B2

公开(公告)日：2014-07-22

申请号：US12736301

申请日：2009-02-20

申请人： Michael Kolax ,  Wolf-Dietrich Dolzinski

发明人： Michael Kolax ,  Wolf-Dietrich Dolzinski

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。

公开(公告)号：US20110020595A1

公开(公告)日：2011-01-27

申请号：US12736303

申请日：2009-02-20

申请人： Michael Kolax ,  Wolf-Dietrich Dolzinski

发明人： Michael Kolax ,  Wolf-Dietrich Dolzinski

IPC分类号： B32B3/12 ,  B32B7/08

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）。

公开(公告)号：US20120068012A1

公开(公告)日：2012-03-22

申请号：US13234611

申请日：2011-09-16

申请人： Wolf-Dietrich Dolzinski ,  Michael Kolax

发明人： Wolf-Dietrich Dolzinski ,  Michael Kolax

IPC分类号： B64C1/40 ,  B64D13/00 ,  F28D21/00 ,  B64D11/00

CPC分类号： B64C1/067 ,  B64C1/12 ,  B64C1/40 ,  Y02T50/46

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。

公开(公告)号：US20120056037A1

公开(公告)日：2012-03-08

申请号：US13257367

申请日：2010-03-16

申请人： Wolf-Dietrich Dolzinski ,  Norbert Heltsch ,  Arne Hartwig ,  Markus Mueller ,  Markus Joerg Weber ,  Jens-Ulrich Prowe ,  Paul Joern

发明人： Wolf-Dietrich Dolzinski ,  Norbert Heltsch ,  Arne Hartwig ,  Markus Mueller ,  Markus Joerg Weber ,  Jens-Ulrich Prowe ,  Paul Joern

IPC分类号： B64C1/12 ,  B64C1/06

CPC分类号： B64C1/12 ,  B64C1/064 ,  B64C1/065 ,  B64C2001/0072 ,  Y02T50/43

摘要： A fuselage cell structure for an aircraft includes at least two skin panels including at least one double shell skin panel and at least one monolithic skin panel. At least one brace which is at least one of a longitudinal and a transverse brace is disposed so as to form at least one of a longitudinal seam and a transverse seam between the at least one double shell skin panel and the at least one monolithic skin panel. The fuselage cell structure includes at least one of a longitudinal bracket and a load transfer point. The longitudinal bracket is disposed in a region of the longitudinal seam and includes a first and a second longitudinal flange that are disposed offset with respect to one another and connected by a web. The load transfer point is disposed in a region of the transverse seam so as to connect the longitudinal brace disposed on the at least one monolithic skin panel to the at least one double shell skin panel.

摘要翻译： 用于飞行器的机身单元结构包括至少两个皮肤面板，其包括至少一个双壳皮肤面板和至少一个整体式皮肤面板。 布置至少一个纵向和横向支架中的至少一个的支架，以便形成至少一个双壳皮肤面板和至少一个整体外观面板之间的纵向接缝和横向接缝中的至少一个 。 机身单元结构包括纵向托架和载荷传递点中的至少一个。 纵向支架设置在纵向接缝的区域中，并且包括第一和第二纵向凸缘，该第一和第二纵向凸缘相对于彼此偏置并通过腹板连接。 负载转移点设置在横向接缝的区域中，以将设置在至少一个单片皮肤面板上的纵向支架连接到至少一个双壳皮肤面板。

公开(公告)号：US20110011521A1

公开(公告)日：2011-01-20

申请号：US12736301

申请日：2009-02-20

申请人： Michael Kolax ,  Wolf-Dietrich Dolzinski

发明人： Michael Kolax ,  Wolf-Dietrich Dolzinski

IPC分类号： B32B38/10 ,  B32B37/14

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。

公开(公告)号：US08926880B2

公开(公告)日：2015-01-06

申请号：US12736303

申请日：2009-02-20

申请人： Michael Kolax ,  Wolf-Dietrich Dolzinski

发明人： Michael Kolax ,  Wolf-Dietrich Dolzinski

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）。

公开(公告)号：US08844868B2

公开(公告)日：2014-09-30

申请号：US12519556

申请日：2008-01-22

申请人： Michael Kolax ,  Wolf-Dietrich Dolzinski

发明人： Michael Kolax ,  Wolf-Dietrich Dolzinski

IPC分类号： B64C1/12 ,  F16B19/06 ,  B64C1/06

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。