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公开(公告)号：US20090072090A1
公开(公告)日：2009-03-19
申请号：US11447235
申请日：2006-06-05
IPC分类号： B64C1/00
摘要： A pivoting panel for an aircraft and to a composite support piece for this kind panel. The support piece (17) is arranged as a part of the frame structure of the panel (3). The support piece has an extension portion (23) to which an actuator connection fitting (7) of an actuator (4) can be fastened. The extension portion (23) distributes the forces to the structures of the panel (3).
摘要翻译： 用于飞机的枢转面板和用于这种面板的复合支撑件。 支撑件（17）被布置为面板（3）的框架结构的一部分。 支撑件具有延伸部分（23），致动器（4）的致动器连接配件（7）可以紧固到该延伸部分。 延伸部分（23）将力分配到面板（3）的结构。
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公开(公告)号：US07631840B2
公开(公告)日：2009-12-15
申请号：US11447235
申请日：2006-06-05
摘要： A pivoting panel for an aircraft and to a composite support piece for this kind panel. The support piece (17) is arranged as a part of the frame structure of the panel (3). The support piece has an extension portion (23) to which an actuator connection fitting (7) of an actuator (4) can be fastened. The extension portion (23) distributes the forces to the structures of the panel (3).
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公开(公告)号：US07708224B2
公开(公告)日：2010-05-04
申请号：US11703600
申请日：2007-02-07
申请人： Antti Aho-Mantila , Pentti Ahtonen , Juha Halme , Lauri Halme , Mikko Hoffrén , Outi Tervala
发明人： Antti Aho-Mantila , Pentti Ahtonen , Juha Halme , Lauri Halme , Mikko Hoffrén , Outi Tervala
IPC分类号： B64D35/00
摘要： The invention relates to an aircraft wing, a fastening arrangement, and an intermediate support. A support structure of a wing (1) comprises transverse wing ribs (7a, 7b), between which an intermediate support (10) is arranged for providing a fastening point for a motor (9). The intermediate support comprises a vertical first side part (15a) and a vertical second side part (15b) which are at a distance from one another and connected to one another at their lower part by means of a horizontal bottom part (16) at least at a fastening lug (11). The lug is supported on the bottom part of the intermediate support.
摘要翻译： 本发明涉及飞机机翼，紧固装置和中间支架。 机翼（1）的支撑结构包括横向翼肋（7a，7b），中间支撑件（10）之间布置有用于提供马达（9）的紧固点。 所述中间支撑件包括垂直的第一侧部（15a）和垂直的第二侧部（15b），所述垂直的第一侧部（15a）和垂直的第二侧部（15b）彼此间隔一定距离，并且在其下部通过水平底部部分 在紧固凸耳（11）上。 凸耳支撑在中间支架的底部。
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公开(公告)号：US20090212154A1
公开(公告)日：2009-08-27
申请号：US11703600
申请日：2007-02-07
申请人： Antti Aho-Mantila , Pentti Ahtonen , Juha Halme , Lauri Halme , Mikko Hoffren , Outi Tervala
发明人： Antti Aho-Mantila , Pentti Ahtonen , Juha Halme , Lauri Halme , Mikko Hoffren , Outi Tervala
摘要： The invention relates to an aircraft wing, a fastening arrangement, and an intermediate support. A support structure of a wing (1) comprises transverse wing ribs (7a, 7b), between which an intermediate support (10) is arranged for providing a fastening point for a motor (9). The intermediate support comprises a vertical first side part (15a) and a vertical second side part (15b) which are at a distance from one another and connected to one another at their lower part by means of a horizontal bottom part (16) at least at a fastening lug (11). The lug is supported on the bottom part of the intermediate support.
摘要翻译： 本发明涉及飞机机翼，紧固装置和中间支架。 机翼（1）的支撑结构包括横向翼肋（7a，7b），中间支撑件（10）之间布置有用于提供马达（9）的紧固点。 所述中间支撑件包括垂直的第一侧部（15a）和垂直的第二侧部（15b），所述垂直的第一侧部（15a）和垂直的第二侧部（15b）彼此间隔一定距离，并且在其下部通过水平底部部分 在紧固凸耳（11）上。 凸耳支撑在中间支架的底部。
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