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公开(公告)号：US20200307756A1
公开(公告)日：2020-10-01
申请号：US16815225
申请日：2020-03-11
发明人： Chinnarajan Periyasamy , Akshay Srinivasamurthy , Wolfgang Entelmann , Wolfgang Schulze , Jens Rohde
摘要： A stiffened structural component for an aircraft includes a first material sheet with a first surface, and at least one elongate bulge that bulges out in a direction transverse to the first surface in order to stiffen the structural component, wherein each of the at least one bulge comprises two edges that extend along the first surface, wherein a continuous bulging surface extends between the edges, and wherein the bulges are formed integrally into the first material sheet through pressing.
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2.发明授权Method for connecting fiber-reinforced intermediate products for producing a structural fiber composite product, such a structural fiber composite product and a method and device for producing an adhesive layer 有权用于连接用于生产结构纤维复合材料的纤维增强中间产品的方法，这种结构纤维复合材料和用于生产粘合剂层的方法和装置公开(公告)号：US09248607B2
公开(公告)日：2016-02-02
申请号：US13648063
申请日：2012-10-09
发明人： Wolfgang Schulze , Thomas Kruse
CPC分类号： B29C65/564 , B29C65/483 , B29C65/4835 , B29C65/488 , B29C65/4885 , B29C65/5057 , B29C65/5092 , B29C65/72 , B29C65/8276 , B29C66/02245 , B29C66/0246 , B29C66/1122 , B29C66/43 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/73921 , B29C66/73941 , B29C66/83421 , B29C70/84 , B64C1/00 , C08K3/04 , C08K3/041 , C08K7/06 , C08K2201/001 , C09J5/02 , C09J5/06 , C09J7/10 , C09J9/02 , C09J11/04 , C09J2205/102 , C09J2205/31 , Y02T50/43 , Y10T156/17 , Y10T428/249923 , B29K2307/04 , B29K2309/08 , B29K2277/10 , B29K2067/00 , B29K2063/00 , B29K2305/00 , B29K2277/00 , B29K2309/02 , B29K2307/02 , B29K2309/14 , B29K2311/00 , B29K2061/04 , B29K2067/06 , B29K2075/02 , B29K2079/00 , B29K2083/00
摘要： Method for connecting two intermediate products for forming a fiber composite product, wherein the two intermediate products respectively are composite fiber material with a layer of matrix material and reinforcing fibers extending therein by connecting areas that adjoin one another in an overlapping region of the interconnected intermediate products, with the method including applying an adhesive layer with an adhesive film with connecting particles onto the connecting areas of the intermediate products, arranging the second intermediate product on the first intermediate product or vice versa so the connecting areas at least partially overlap one another, and connecting the two intermediate products. A structural component is also disclosed with at least a first and a second fiber-reinforced intermediate product.
摘要翻译： 用于连接用于形成纤维复合产品的两个中间产品的方法，其中两个中间产物分别是具有基质材料层的复合纤维材料和通过连接相互连接的互连中间产物的重叠区域中的区域而延伸的增强纤维 该方法包括将具有连接颗粒的粘合剂膜的粘合剂层施加到中间产品的连接区域上，将第二中间产品布置在第一中间产品上，反之亦然，使得连接区域至少部分地彼此重叠，并且 连接两个中间产品。 还公开了至少具有第一和第二纤维增强中间产品的结构部件。
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公开(公告)号：US20140151504A1
公开(公告)日：2014-06-05
申请号：US14084692
申请日：2013-11-20
CPC分类号： B64C1/069 , B64C1/061 , B64C1/068 , B64C2001/0081 , B64F5/10 , Y10T29/49622
摘要： An aircraft fuselage structure having a first fuselage barrel section and a second fuselage section barrel which are joined by tension fasteners extending through frame holes. A shank diameter of the fasteners is smaller than a respective frame hole diameter. A first positive locking element and a second positive locking element is provided forming a form-fit area with the first positive locking element in the circumferential direction. A method for producing such an aircraft fuselage section is also provided.
摘要翻译： 具有第一机身筒部和第二机身部筒的飞机机身结构，其通过延伸穿过框架孔的张力紧固件连接。 紧固件的柄直径小于相应的机架孔直径。 提供了第一正锁定元件和第二正锁定元件，其在圆周方向上与第一正锁定元件形成形状配合区域。 还提供了一种生产这种飞机机身部分的方法。
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公开(公告)号：US11685504B2
公开(公告)日：2023-06-27
申请号：US16881819
申请日：2020-05-22
CPC分类号： B64C1/069 , B29C66/1122 , B64C1/12 , B29L2031/3082 , B64C2001/0045
摘要： A shell arrangement for a fuselage of an aircraft includes a first shell portion extending in a curved manner in a shell peripheral direction and a second shell portion extending in a curved manner in the shell peripheral direction, wherein, in an overlapping portion of the shell arrangement, a first end region of the first shell portion and a second end region of the second shell portion overlap each other in the shell peripheral direction and a first outer face of the first shell portion and a second inner face of the second shell portion are adhesively bonded to each other by an adhesive layer, and wherein an edge of the first shell portion which terminates the first end region with respect to the shell peripheral direction extends in the overlapping portion in an undulating manner in a shell longitudinal direction which extends transversely relative to the shell peripheral direction.
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公开(公告)号：US11623729B2
公开(公告)日：2023-04-11
申请号：US16424315
申请日：2019-05-28
摘要： A method for producing a crossmember for a vehicle prepares a workpiece having different thicknesses and a preliminary contour from a metal sheet of uniform thickness by flat roll forming to achieve different local thicknesses. The method cuts out the workpiece, and bending roll forms the workpiece to form a crossmember with a cross section having at least two flanges opposite one another, and a web situated between said flanges. The distance between the flanges is not constant along a longitudinal extent of the crossmember, and a thickness profile at least of the web is determined by the flat roll forming. The local thicknesses and the preliminary contour are such that a geometrical shape of the crossmember corresponds to a predetermined geometrical shape with different thicknesses and heights of the web and differently shaped regions of the flanges along the longitudinal extent of the crossmember.
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公开(公告)号：US09567057B2
公开(公告)日：2017-02-14
申请号：US14084692
申请日：2013-11-20
CPC分类号： B64C1/069 , B64C1/061 , B64C1/068 , B64C2001/0081 , B64F5/10 , Y10T29/49622
摘要： An aircraft fuselage structure having a first fuselage barrel section and a second fuselage section barrel which are joined by tension fasteners extending through frame holes. A shank diameter of the fasteners is smaller than a respective frame hole diameter. A first positive locking element and a second positive locking element is provided forming a form-fit area with the first positive locking element in the circumferential direction. A method for producing such an aircraft fuselage section is also provided.
摘要翻译： 具有第一机身筒部和第二机身部筒的飞机机身结构，其通过延伸穿过框架孔的张力紧固件连接。 紧固件的柄直径小于相应的机架孔直径。 提供了第一正锁定元件和第二正锁定元件，其在圆周方向上与第一正锁定元件形成形状配合区域。 还提供了一种生产这种飞机机身部分的方法。
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公开(公告)号：US09511845B2
公开(公告)日：2016-12-06
申请号：US14163406
申请日：2014-01-24
CPC分类号： B64C1/061 , B29C64/00 , B29C67/0051 , B64C1/064 , B64C1/069 , B64C1/10 , Y10T29/49826
摘要： An aircraft frame includes a first partial aircraft frame configured to be attached to a first aircraft fuselage segment, and a second partial aircraft frame configured to be attached to a second aircraft fuselage segment. The first and second partial aircraft frames include corresponding first and second stringer coupling sections. The first partial aircraft frame and the second partial aircraft frame are configured to be attached to each other via a first web and a second web. The first stringer coupling section is located between the first inner flange and the first outer flange and the second stringer coupling section is located between the second inner flange and the second outer flange. The first stringer coupling section includes a first wall which extends from the first web into the first section of the first partial aircraft frame, and the second stringer coupling section comprises a second wall, which extends from the second web into the second section of the second partial aircraft frame.
摘要翻译： 飞机框架包括构造成附接到第一飞行器机身段的第一部分飞机框架和被配置为附接到第二飞行器机身段的第二部分飞机框架。 第一和第二部分飞行器架包括对应的第一和第二纵梁联接部分。 第一部分飞行器架和第二部分飞行器架被构造成经由第一腹板和第二腹板相互连接。 第一纵梁联接部分位于第一内凸缘和第一外凸缘之间，第二纵梁联接部分位于第二内凸缘和第二外凸缘之间。 第一纵梁联接部分包括从第一腹板延伸到第一部分飞行器框架的第一部分中的第一壁，并且第二纵梁联接部分包括第二壁，第二壁从第二腹板延伸到第二部分的第二部分 部分飞机架。
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公开(公告)号：US11541982B2
公开(公告)日：2023-01-03
申请号：US16815225
申请日：2020-03-11
发明人： Chinnarajan Periyasamy , Akshay Srinivasamurthy , Wolfgang Entelmann , Wolfgang Schulze , Jens Rohde
摘要： A stiffened structural component for an aircraft includes a first material sheet with a first surface, and at least one elongate bulge that bulges out in a direction transverse to the first surface in order to stiffen the structural component, wherein each of the at least one bulge comprises two edges that extend along the first surface, wherein a continuous bulging surface extends between the edges, and wherein the bulges are formed integrally into the first material sheet through pressing.
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公开(公告)号：US10046846B2
公开(公告)日：2018-08-14
申请号：US14617389
申请日：2015-02-09
CPC分类号： B64C1/12 , B23P2700/01 , B64C1/068 , B64C3/26 , B64F5/10 , B64G1/22 , Y10T29/49622 , Y10T29/5397
摘要： A method of manufacturing a shell component for an aircraft or spacecraft includes positioning a skin panel, which includes a skin of the aircraft or spacecraft and first and second stringers stiffening the skin, opposite a frame having first and second mouseholes for receiving the first and second stringers, elastically bending the skin panel, inserting the first stringer into the first mousehole, and releasing the elastic bend to insert the second stringer into the second mousehole.
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公开(公告)号：US11787125B2
公开(公告)日：2023-10-17
申请号：US16655368
申请日：2019-10-17
发明人： Wolfgang Schulze , Martin Eberle
CPC分类号： B29C66/721 , B29C65/48 , B29C66/81455 , B29L2031/3076
摘要： A method for connecting two components is proposed where a pressure acting on an adhesive between two join partners is supported by an auxiliary body which rests on a cutout of one of the components. Both components to be connected together and the auxiliary body are covered by a vacuum film and once the air has been sucked out, the compressive force is generated below the vacuum film.
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