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1. 发明申请

US20170369145A1 METHOD FOR MANUFACTURING A PANEL WITH A DOUBLER 审中-公开
公开(公告)号：US20170369145A1
公开(公告)日：2017-12-28
申请号：US15633926
申请日：2017-06-27
申请人： Fokker Aerostructures B.V.
发明人： Abdoel Faziel RAJABALI , Pim TAMIS
IPC分类号： B64C1/12 , B32B15/04 , B32B37/12 , B32B37/00 , B32B7/12 , B32B38/00 , B32B15/20
摘要： Disclosed is a panel for an aircraft structure, including a laminated skin of layers of metal of which in each case two are joined together by a fibre-reinforced adhesive layer, as well as a laminated doubler of layers of metal and at least one fibre-reinforced adhesive layer in each case between two layers of metal, wherein the doubler has a smaller size of perimeter than the skin and is bonded to an outermost layer of metal of the laminated skin by a fibre-reinforced supplementary adhesive layer, with the feature that at least one part of the perimeter of the fibre-reinforced supplementary adhesive layer is staggered inwards relative to the corresponding perimeter of the doubler and that that part of the inwards-staggered perimeter of the fibre-reinforced supplementary adhesive layer is delimited by a glued edge. Also disclosed is a method for manufacturing such a panel.

2. 发明申请

US20230036032A1 AIRCRAFT STRUCTURAL, ANTI-BALLISTIC FLOOR PANEL 有权
公开(公告)号：US20230036032A1
公开(公告)日：2023-02-02
申请号：US17790514
申请日：2021-01-14
申请人： Fokker Aerostructures B.V.
发明人： Erik Dekker
IPC分类号： B64D7/00 , B64C27/04 , B64C1/18 , F41H5/02 , F41H5/04
摘要： There is provided an anti-ballistic aerospace structure, said structure comprising a strike layer defining an outwardly facing surface and an opposing capture layer defining an inwardly facing surface and an intermediate structural layer arranged between the strike layer and capture layer, wherein the intermediate structural layer is spaced relative to the strike layer to define a space between the intermediate structural layer and the strike layer, said space comprising one or more reinforcement elements, and wherein the strike layer is formed of a fiber reinforced plastic laminate comprising at least one metallic layer.

3. 发明授权

US11326269B2 Anodizing an article of aluminum or alloy thereof 有权
公开(公告)号：US11326269B2
公开(公告)日：2022-05-10
申请号：US16094033
申请日：2017-04-18
申请人： Fokker Aerostructures B.V.
发明人： Johannes Marinus Maria De Kok , Vincent Kornelis Johannes Van Den Heuvel
IPC分类号： C25D11/08 , C25D11/02 , C25D11/24 , C25D11/18 , C25D11/16
摘要： A method of anodizing an article of aluminum or aluminum alloy for forming a porous anodic oxide coating comprises an immersion step of immersing the article to be anodized in an electrolyte in a tank, wherein the electrolyte comprises an aqueous solution of 5-50 g/l sulphuric acid and 2-50 g/l phosphoric acid, and arranging the article as an anode with respect to one or more counter electrodes as arranged cathodes in the electrolyte, and an anodizing step of applying a positive anode voltage Va to the article, while the temperature of the electrolyte is in the range of 33-60° C.

4. 发明授权

US09481127B2 Method for producing a connection between composite parts 有权
标题翻译：用于生产复合部件之间连接的方法
公开(公告)号：US09481127B2
公开(公告)日：2016-11-01
申请号：US13661220
申请日：2012-10-26
申请人： FOKKER AEROSTRUCTURES B.V.
发明人： Joost List , Robert Kruithof , Johannes Martinus Josephus Teunissen , Hendrik Van Croonenborg
IPC分类号： B29C65/02 , B29C65/42 , B29C65/00 , B29C65/48 , B29K71/00 , B29K105/06 , B29K105/12 , B29L31/00
CPC分类号： B29C65/02 , B29C65/42 , B29C65/4815 , B29C65/488 , B29C66/112 , B29C66/114 , B29C66/301 , B29C66/43441 , B29C66/532 , B29C66/61 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/72143 , B29C66/7392 , B29K2071/00 , B29K2105/06 , B29K2105/12 , B29L2031/003 , Y10T428/19 , Y10T428/24 , Y10T428/24174 , B29K2307/04 , B29K2309/08 , B29K2079/085 , B29C66/43 , B29C65/00
摘要： A method for joining together constructional parts which are made of a composite material and extend transversely to one another, such as a flange and a web of a profile, includes the steps of: placing the constructional parts in the desired position with respect to one another so as to form a connecting region in which one of the constructional parts abuts against or in proximity to the other constructional part, causing a thermoplastic material to flow out into the connecting region, fusing together the constructional parts under the influence of heat and pressure.

5. 发明申请

US20150291275A1 AIRPLANE WING, AN AIRPLANE AND A FLAP SYSTEM 有权
标题翻译： AIRPLANE WING，AIRPLANE和FLAP系统
公开(公告)号：US20150291275A1
公开(公告)日：2015-10-15
申请号：US14440272
申请日：2013-10-29
申请人： FOKKER AEROSTRUCTURES B.V.
发明人： Adrianus Marinus Franciscus Bastiaansen , Michel Schoonhoven
IPC分类号： B64C9/38 , B64C13/00
CPC分类号： B64C9/38 , B64C9/16 , B64C9/18 , B64C13/00 , Y02T50/32
摘要： An airplane wing comprises a main wing and a flap system that has a flap at the trailing edge of the main wing. An elongate flap track member is connected to the main wing in such a manner that it can be moved substantially in its longitudinal direction and is guided by supporting bearing elements relative to the main wing between a forward retracted position and a rearward extended position. The flap is rotatably connected to the rear end of the flap track member in such a manner that it can rotate about a rotation axis that extends substantially parallel to the trailing edge of the main wing, so that the flap moves together with the flap track member when the flap track member is moved and so that the flap can be rotated about the rotation axis mechanically independently of the movement of the flap track member. The flap system comprises an actuator system having two actuators. The first actuator is connected to the main wing and has an engagement member that engages the flap or the flap track member for moving the flap together with the flap track member so that the flap track member is move able between its retracted position and its extended position. The second actuator is connected to the flap track member so that the second actuator moves together with the flap track member when the flap track member is moved by means of the first actuator. The second actuator has an engagement member that engages the flap for rotating the flap about the rotation axis.
摘要翻译：飞机机翼包括主翼和在主翼的后缘具有翼片的翼片系统。细长的翼片轨道构件以这样的方式连接到主翼，使得其可以在其纵向方向上基本上移动，并且在前向缩回位置和向后延伸位置之间通过相对于主翼的支撑轴承元件来引导。翼片可旋转地连接到翼片轨道构件的后端，使得其可以围绕基本上平行于主翼的后缘延伸的旋转轴线旋转，使得翼片与翼片轨道构件一起移动当翼片轨道构件被移动并且使得翼片可以机械地围绕旋转轴线旋转而与挡板轨道构件的运动无关。皮瓣系统包括具有两个致动器的致动器系统。第一致动器连接到主翼并且具有接合翼片或翼片轨道构件的接合构件，用于将翼片与翼片轨道构件一起移动，使得翼片轨道构件能够在其缩回位置和其延伸位置之间移动。第二致动器连接到翼片轨道构件，使得当翼片轨道构件通过第一致动器移动时，第二致动器与翼片轨道构件一起移动。第二致动器具有接合翼片的接合构件，用于围绕旋转轴线旋转翼片。

6. 发明申请

US20210139128A1 AIRFOIL-SHAPED BODY WITH A VARIABLE OUTER SHAPE 有权
公开(公告)号：US20210139128A1
公开(公告)日：2021-05-13
申请号：US16492905
申请日：2018-03-16
申请人： FOKKER AEROSTRUCTURES B.V.
发明人： Adrianus Marinus Franciscus BASTIAANSEN
IPC分类号： B64C3/48 , B64C3/26
摘要： An airfoil-shaped body having a variable outer shape, comprising: a first skin, defining a suction surface, a second skin, defining a pressure surface and connected to the first skin at least at a leading edge and/or a trailing edge of the airfoil-shaped body, at least one elongate stiffening beam, arranged inside a cavity of the airfoil-shaped body and secured to at least one of said first and second skins, the stiffening beam including at least a first and a second beam section arranged one after the other and a joining member, arranged between end portions of the beam sections and connected thereto, said joining member being adapted to allow relative movement between the beam sections by an elastic deformation; and an actuator that is operationally associated with said elongate stiffening beam, wherein, upon operating the actuator, the first beam section is moved with respect to the second beam section, or vice versa, changing the orientation of the beam sections with respect to each other, which causes a change in the variable outer shape of the airfoil-shaped body.

7. 发明授权

US10766224B2 Panel made of laminates and method of manufacturing the same 有权
公开(公告)号：US10766224B2
公开(公告)日：2020-09-08
申请号：US15306215
申请日：2015-04-23
申请人： FOKKER AEROSTRUCTURES B.V.
发明人： Abdoelfaziel Rajabali
IPC分类号： B32B5/12 , B32B7/03 , B32B15/14 , B32B37/00 , B32B37/10 , B32B38/18 , B32B3/28 , B64C1/12 , B32B7/12 , B32B27/04 , B32B5/02 , B64C1/00
摘要： An integrated panel made of interconnected laminates includes stacked first and second metal layers (5, 5′, 5″) and fibre-reinforced adhesive layers (19) between adjacent metal layers. At the location of the transition from the outer surface (7) of the first outer metal layer (5) to the outer surface (7) of the second outer metal layer (4) is located a filler (11). The panel further includes a cladding layer (14), which includes at least one fibre material layer (15, 24) that extends over the filler (11) and the adjacent outer surface regions (12, 13) of the outer metal layers (5, 4) located on opposite sides and which are adhered to the outer surface regions.

8. 发明申请

US20190112725A1 ANODIZING AN ARTICLE OF ALUMINUM OR ALLOY THEREOF 审中-公开
公开(公告)号：US20190112725A1
公开(公告)日：2019-04-18
申请号：US16094033
申请日：2017-04-18
申请人： Fokker Aerostructures B.V.
发明人： Johannes Marinus Maria De Kok , Vincent Kornelis Johannes Van Den Heuvel
IPC分类号： C25D11/08 , C25D11/02 , C25D11/24
摘要： A method of anodizing an article of aluminum or aluminum alloy for forming a porous anodic oxide coating comprises an immersion step of immersing the article to be anodized in an electrolyte in a tank, wherein the electrolyte comprises an aqueous solution of 5-50 g/l sulphuric acid and 2-50 g/l phosphoric acid, and arranging the article as an anode with respect to one or more counter electrodes as arranged cathodes in the electrolyte, and an anodizing step of applying a positive anode voltage Va to the article, while the temperature of the electrolyte is in the range of 33-60° C.

9. 发明授权

US09868512B2 Airplane wing, an airplane and a flap system 有权
公开(公告)号：US09868512B2
公开(公告)日：2018-01-16
申请号：US14440272
申请日：2013-10-29
申请人： FOKKER AEROSTRUCTURES B.V.
发明人： Adrianus Marinus Franciscus Bastiaansen , Michel Schoonhoven
IPC分类号： B64C9/38 , B64C9/16 , B64C9/18 , B64C13/00
CPC分类号： B64C9/38 , B64C9/16 , B64C9/18 , B64C13/00 , Y02T50/32
摘要： An airplane wing comprises a main wing and a flap system that has a flap at the trailing edge of the main wing. An elongate flap track member is connected to the main wing in such a manner that it can be moved substantially in its longitudinal direction and is guided by supporting bearing elements relative to the main wing between a forward retracted position and a rearward extended position. The flap is rotatably connected to the rear end of the flap track member in such a manner that it can rotate about a rotation axis that extends substantially parallel to the trailing edge of the main wing, so that the flap moves together with the flap track member when the flap track member is moved and so that the flap can be rotated about the rotation axis mechanically independently of the movement of the flap track member. The flap system comprises an actuator system having two actuators. The first actuator is connected to the main wing and has an engagement member that engages the flap or the flap track member for moving the flap together with the flap track member so that the flap track member is move able between its retracted position and its extended position. The second actuator is connected to the flap track member so that the second actuator moves together with the flap track member when the flap track member is moved by means of the first actuator. The second actuator has an engagement member that engages the flap for rotating the flap about the rotation axis.

10. 发明授权

US10556664B2 Method for manufacturing a panel with a doubler 有权
公开(公告)号：US10556664B2
公开(公告)日：2020-02-11
申请号：US15633926
申请日：2017-06-27
申请人： Fokker Aerostructures B.V.
发明人： Abdoel Faziel Rajabali , Pim Tamis
IPC分类号： B64C1/12 , B32B7/12 , B32B15/04 , B32B15/20 , B32B37/00 , B32B37/12 , B32B38/00
摘要： Disclosed is a panel for an aircraft structure, including a laminated skin of layers of metal of which in each case two are joined together by a fibre-reinforced adhesive layer, as well as a laminated doubler of layers of metal and at least one fibre-reinforced adhesive layer in each case between two layers of metal, wherein the doubler has a smaller size of perimeter than the skin and is bonded to an outermost layer of metal of the laminated skin by a fibre-reinforced supplementary adhesive layer, with the feature that at least one part of the perimeter of the fibre-reinforced supplementary adhesive layer is staggered inwards relative to the corresponding perimeter of the doubler and that that part of the inwards-staggered perimeter of the fibre-reinforced supplementary adhesive layer is delimited by a glued edge. Also disclosed is a method for manufacturing such a panel.

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