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1.发明申请公开(公告)号：US20090147429A1
公开(公告)日：2009-06-11
申请号：US12069574
申请日：2008-02-11
CPC分类号： B64D45/02 , F16B33/004 , F16B37/14 , F16B43/001
摘要： The invention relates to an integrated device (1) for the protection against electrical discharges of conductive fixing elements (2) between one another or of a fixing element and another conductive element of aircraft, comprising a cap (3) and an o-ring gasket (4) made of non-conductive insulating material, the mentioned integrated device (1) comprising a modified fixing element (2) working together with the cap (3) and the o-ring gasket (4), the fixing element (2) surrounding the cap (3) and the o-ring gasket (4) in a non-conductive manner, thus preventing the possibility of electrical discharges such that in the device (1) the number of necessary components is minimized, the impact in weight for the aircraft being minimum, the modified fixing element (2) further comprising a thread (5) on the outer face of the area that has to be protected.
摘要翻译： 本发明涉及一种用于防止导电固定元件（2）彼此之间或固定元件与飞机另一导电元件的放电的集成装置（1），其包括盖（3）和O形圈垫圈 （4）由不导电绝缘材料制成，所述集成装置（1）包括与盖（3）和O形环垫圈（4）一起工作的改进的固定元件（2），固定元件（2） 以不导电的方式围绕盖（3）和O型圈垫圈（4），从而防止放电的可能性，使得在装置（1）中所需部件的数量最小化，对于 所述飞行器是最小的，所述修改的固定元件（2）还包括在所述区域的外表面上必须被保护的螺纹（5）。
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2.发明授权公开(公告)号：US07907382B2
公开(公告)日：2011-03-15
申请号：US12069574
申请日：2008-02-11
IPC分类号： H05F3/00
CPC分类号： B64D45/02 , F16B33/004 , F16B37/14 , F16B43/001
摘要： The invention relates to an integrated device (1) for the protection against electrical discharges of conductive fixing elements (2) between one another or of a fixing element and another conductive element of aircraft, comprising a cap (3) and an o-ring gasket (4) made of non-conductive insulating material, the mentioned integrated device (1) comprising a modified fixing element (2) working together with the cap (3) and the o-ring gasket (4), the fixing element (2) surrounding the cap (3) and the o-ring gasket (4) in a non-conductive manner, thus preventing the possibility of electrical discharges such that in the device (1) the number of necessary components is minimized, the impact in weight for the aircraft being minimum, the modified fixing element (2) further comprising a thread (5) on the outer face of the area that has to be protected.
摘要翻译： 本发明涉及一种用于防止导电固定元件（2）彼此之间或固定元件与飞机另一导电元件的放电的集成装置（1），其包括盖（3）和O形圈垫圈 （4）由不导电绝缘材料制成，所述集成装置（1）包括与盖（3）和O形环垫圈（4）一起工作的改进的固定元件（2），固定元件（2） 以不导电的方式围绕盖（3）和O型圈垫圈（4），从而防止放电的可能性，使得在装置（1）中所需部件的数量最小化，对于 所述飞行器是最小的，所述修改的固定元件（2）还包括在所述区域的外表面上必须被保护的螺纹（5）。
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3.发明授权Sealing system for the gap existing between the fuselage and the elevator of an aircraft with orientable horizontal stabilizer 失效密封系统存在于具有可定向水平稳定器的飞机机身和电梯之间的差距公开(公告)号：US07699266B2
公开(公告)日：2010-04-20
申请号：US11790453
申请日：2007-04-25
摘要： A sealing system for a gap (2) existing between the fuselage (3) and the elevator (4) of a orientable horizontal stabilizer (5) of an aircraft, comprises a main body (1) formed by an upper surface (18) and a lower surface (19) and at least one longitudinal vertical element (22) arranged between the two surfaces (18,19) which grants rigidity to the main body (1), and a plurality of first elastic sealing profiles (9) between the first surface (11) of the main body (1) and the outer surface of the fuselage (3) and making contact with them, and a plurality of second elastic sealing profiles (13) between the second surface (12) of the main body (1) and the first end of the elevator (15) and making contact with them, in such a way that the sealing of the gap (2) takes place and an aerodynamic continuity is produced between the fuselage (3) and the elevator (4) when the elevator (4) is at rest in the plane of the orientable horizontal stabilizer (5) for any of the orientation positions of the orientable horizontal stabilizer (5).
摘要翻译： 存在于飞机的可定向水平稳定器（5）的机身（3）和电梯（4）之间的间隙（2）的密封系统包括由上表面（18）形成的主体（1）和 布置在两个表面（18,19）之间的至少一个纵向垂直元件（22）的下表面（19）和至少一个纵向垂直元件（22），其向主体（1）提供刚性;以及多个第一弹性密封型材（9） 主体（1）的第一表面（11）和机身（3）的外表面与它们接触，以及在主体的第二表面（12）之间的多个第二弹性密封型材（13） （1）和电梯（15）的第一端并与其接触，使得间隙（2）的密封发生并且在机身（3）和电梯（3）之间产生空气动力学连续性 4）当电梯（4）在可定向的水平稳定器（5）的平面中静止时，用于任何取向位置 可定向水平稳定器（5）。
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4.发明申请Sealing system for the gap existing between the fuselage and the elevator of an aircraft with orientable horizontal stabiliser 失效密封系统存在于具有可定向水平稳定器的飞机机身和电梯之间的差距公开(公告)号：US20080169382A1
公开(公告)日：2008-07-17
申请号：US11790453
申请日：2007-04-25
IPC分类号： B64C1/00
摘要： Sealing system for the gap (2) existing between the fuselage (3) and the elevator (4) of the orientable horizontal stabiliser (5) of an aircraft which comprises a main body (1) formed by an upper surface (18) and a lower surface (19) and at least one longitudinal vertical element (22) arranged between the two surfaces (18,19) which grants rigidity to the main body (1), and a plurality of first elastic sealing profiles (9) between the first surface (11) of the main body (1) and the outer surface of the fuselage (3) and making contact with them, and a plurality of second elastic sealing profiles (13) between the second surface (12) of the main body (1) and the first end of the elevator (15) and making contact with them, in such a way that the sealing of the gap (2) takes place and an aerodynamic continuity is produced between the fuselage (3) and the elevator (4) when the elevator (4) is at rest in the plane of the orientable horizontal stabiliser (5) for any of the orientation positions of the orientable horizontal stabiliser (5).
摘要翻译： 存在于飞机的可定向水平稳定器（5）的机身（3）和升降机（4）之间的间隙（2）的密封系统，包括由上表面（18）形成的主体（1） 下表面（19）和布置在两个表面（18,19）之间的至少一个纵向垂直元件（22），其向主体（1）提供刚性;以及多个第一弹性密封型材（9） 主体（1）的表面（11）和机身（3）的外表面与它们接触，以及在主体的第二表面（12）之间的多个第二弹性密封型材（13） 1）和电梯（15）的第一端并与其接触，使得间隙（2）的密封发生并且在机身（3）和电梯（4）之间产生空气动力学连续性 ）当电梯（4）在可定向的水平稳定平面中静止时 ser（5）用于可定向水平稳定器（5）的任何取向位置。
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5.发明申请SEALING SYSTEM FOR THE GAP EXISTING BETWEEN THE FUSELAGE AND THE ELEVATOR OF THE ORIENTABLE HORIZONTAL STABILISER OF AN AIRCRAFT, EXTENDED WITH AN AERODYNAMIC FAIRING FOR SEALING OF THE OPENING EXISTING BETWEEN THE FUSELAGE AND THE ORIENTABLE HORIZONTAL STABILISER 有权密封件与密封件之间存在的密封件和飞机上的定向水平稳定器的电梯之间的密封系统，用于密封金属和方位水平稳定器之间的开放现象的空气动力学公差公开(公告)号：US20100282907A1
公开(公告)日：2010-11-11
申请号：US11790401
申请日：2007-04-25
IPC分类号： B64C1/38
摘要： Sealing system for the gap (2) between the fuselage (3) and the elevator (4) of the orientable horizontal stabiliser (5) of an aircraft, extended with an aerodynamic fairing (8) for sealing of the opening (24) between the fuselage (3) and said orientable horizontal stabiliser (5) which comprises a main body (1) and an aerodynamic fairing (8) which is extended from the main body (1) in continuity with the latter, and a plurality of first elastic sealing profiles (9) between the first surface (11) of the main body (1) including the aerodynamic fairing (8) and the outer surface of the fuselage (3) and making contact with them, and a plurality of second elastic sealing profiles (13) between the second surface (12) of the main body (1) and the first end of the elevator (15) and making contact with them, in such a way that the sealing takes place of the gap (2) and the opening (24) and an aerodynamic continuity is produced between the orientable horizontal stabiliser (5), the fuselage (3) and the elevator (4) when the elevator (4) is at rest in the plane of the orientable horizontal stabiliser (5) for any of the orientation positions of the orientable horizontal stabiliser (5).
摘要翻译： 用于机身（3）与飞机的可定向水平稳定器（5）的电梯（4）之间的间隙（2）的密封系统，其延伸有空气动力学整流罩（8），用于密封开口（24） 机身（3）和所述可定向水平稳定器（5），其包括从主体（1）延伸的与主体（1）延伸的主体（1）和空气动力整流罩（8），以及多个第一弹性密封 主体（1）的包括气动整流罩（8）和机身外表面（3）的第一表面（11）与其接触并且与多个第二弹性密封型材 13）在主体（1）的第二表面（12）和电梯（15）的第一端之间并与它们接触，使得密封发生在间隙（2）和开口 （24），并且在可定向水平稳定器（5），机身（3）a之间产生空气动力学连续性 d电梯（4）在可定向水平稳定器（5）的任何取向位置处于可定向水平稳定器（5）的平面中静止时。
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公开(公告)号：US20090126973A1
公开(公告)日：2009-05-21
申请号：US12008987
申请日：2008-01-15
IPC分类号： H01B3/00
CPC分类号： B64D45/02 , F16B33/004 , F16B37/14 , F16B43/001
摘要： The invention relates to a device (1) for the protection against electrical discharges of a conductive fixing element (4) of an aircraft, comprising a cap (2) made of non-conductive material and a washer (3) made of non-conductive material insulating the fixing element (4) from electrical discharges, said cap being an open receptacle with a cylindrical shape closed at one of its ends and open at the other end, comprising at the lower part of its inner face a thread (15), the washer (3) being retained by the fixing element (4), said washer (3) having a thread (5) on its outer face coupling with the complementary thread (15) in the lower area of the inner face of the cap (2), relative movements between the washer (3) and the cap (2) being prevented.
摘要翻译： 本发明涉及一种用于防止飞机的导电固定元件（4）的放电的装置（1），包括由非导电材料制成的盖（2）和由非导电材料制成的垫圈（3） 材料将固定元件（4）从放电中绝缘，所述帽是敞开的容器，其圆柱形形状在其一端处封闭并在另一端开口，在其内表面的下部包括螺纹（15）， 所述垫圈（3）由所述固定元件（4）保持，所述垫圈（3）在其外表面上具有螺纹（5），所述外表面与所述互补螺纹（15）联接在所述盖的内表面的下部区域 2），防止垫圈（3）和盖（2）之间的相对运动。
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公开(公告)号：US20100108845A1
公开(公告)日：2010-05-06
申请号：US12318793
申请日：2009-01-08
IPC分类号： A47B96/06
CPC分类号： B64C13/341 , Y02T50/44
摘要： Applicable in installations with two reaction bars attached to a first and a second piece, arranged above two actuators, also attached to the first and second piece for producing the relative displacement between both pieces. It comprises a support located between the reaction bars, fastened to them, covering at least their upper part; each reaction bar having at least one first cable, located above the surface of the support and whose ends are attached to the confronting side walls of an actuator; some vertical arms attached to the support and to two horizontal parallel bars, located between the confronting side faces of the actuators; at least one second cable located around each one of the horizontal parallel bars that are fastened to the side face of an actuator so that, when an actuator is disconnected from the first or second piece, it is kept retained by means of the device.
摘要翻译： 适用于安装有安装在第一和第二部件上的两个反作用杆的安装件，其布置在两个致动器上方，也连接到第一和第二部件上，用于产生两个部件之间的相对位移。 它包括位于反应杆之间的支撑件，固定到它们上，至少覆盖其上部; 每个反应杆具有位于支撑件表面上方的至少一个第一电缆，并且其端部附接到致动器的相对侧壁; 附接到支撑件的一些垂直臂和位于致动器的相对侧面之间的两个水平平行杆; 围绕每个水平平行杆的至少一个第二缆索，其紧固到致动器的侧面，使得当致动器与第一或第二部件断开连接时，其通过该装置保持保持。
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公开(公告)号：US20100078540A1
公开(公告)日：2010-04-01
申请号：US12318795
申请日：2009-01-08
IPC分类号： F16M13/02
CPC分类号： B64C13/341 , Y02T50/44
摘要： Applicable in installations that comprise a reaction bar (1) located above an actuator (4), and both attached to a first piece (2) and to a second piece (3) for producing the relative displacement between the first piece (2) and the second piece (3). It also comprises two supports (6) which are fixed to the reaction bar (1) and which, by means of some vertical arms (7), support two horizontal bars (8) which are located facing and parallel to the lateral sides of the actuator. It includes a cable (9), located around each one of the horizontal parallel bars (8), whose ends are fixed to the lateral sides of the actuator (4) so that, when disconnection takes place of the actuator from the first piece (2) or second piece (3), said actuator (4) is kept retained by means of the safety device.
摘要翻译： 适用于包括位于致动器（4）上方的反作用杆（1）并且两者都连接到第一件（2）和第二件（3）的装置中，用于产生第一件（2）和 第二件（3）。 它还包括固定在反作用杆（1）上的两个支撑件（6），并且通过一些垂直臂（7）支撑两个水平杆（8），这两个水平杆面对并平行于 执行器。 它包括位于每个水平平行杆（8）周围的电缆（9），其端部固定到致动器（4）的侧面，使得当致动器从第一部件发生断开时 2）或第二件（3），所述致动器（4）通过安全装置保持保持。
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9.发明申请Protection device against electrical discharges in fixing elements with high charges 审中-公开保护装置防止高电荷固定元件放电公开(公告)号：US20090128983A1
公开(公告)日：2009-05-21
申请号：US12008990
申请日：2008-01-15
IPC分类号： H05F3/00
CPC分类号： B64D45/02 , F16B33/004 , F16B37/14 , F16B43/001
摘要： The invention relates to a device (12) for protecting a conductive fixing element (5) of an aircraft subjected to high charges against electrical discharges, the device (12) comprising a cap (6) made of non-conductive material, a washer (7) made of conductive metal material and an o-ring gasket (8) made of non-conductive material retained by the washer (7), the washer (7) being retained by the fixing element (5) subjected to a high charge that must be protected, and the cap (6) and the o-ring gasket (8) non-conductively surrounding the fixing element (5), thus preventing the possibility of electrical discharges.
摘要翻译： 本发明涉及一种用于保护受到高电荷抵抗放电的飞行器的导电固定元件（5）的装置（12），所述装置（12）包括由非导电材料制成的盖（6），垫圈（ 7），由垫圈（7）保持的由导电材料制成的O形环垫圈（8），垫圈（7）由经受高充电的固定元件（5）保持， 必须被保护，并且帽（6）和O形环垫圈（8）不导电地围绕固定元件（5），从而防止放电的可能性。
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公开(公告)号：US20080121758A1
公开(公告)日：2008-05-29
申请号：US11825661
申请日：2007-07-05
IPC分类号： B64C1/38
CPC分类号： B64C7/00
摘要： Reinforced cover for gaps in an aerodynamic contour of a vehicle, with a first attachment section 1a attachable to a structural element 2, 5 of the vehicle 11, on a first axial plane I; a second elastic section 1c which covers a gap 3 which is located between a fixed part 5 and a moving part 6, 12 of the vehicle 11, and provided with a low-friction coating 8 on its inner surface 1e, an outer surface 1k with a fiberglass layer 7a; a main internal body 9 of an elastic material, a flexible transition section 1g between the first and the second section, 1a, 1c; the outer surface 1k of the second section 1c flushing with the outer surface 5a and extending towards the free end 1d as a continuation of the outer surface 5a of the fixed part 5.
摘要翻译： 在车辆的空气动力学轮廓中的间隙的加强罩，具有可连接到车辆11的结构元件2,5的第一附接部分1a，在第一轴向平面I上; 第二弹性部分1c覆盖位于车辆11的固定部分5和移动部分6,12之间并且在其内表面1e上设置有低摩擦涂层8的间隙3，外表面 1k具有玻璃纤维层7a; 弹性材料的主内部体9，第一和第二部分之间的柔性过渡部分1g，1a，1c; 第二部分1c的外表面1k与外表面5c冲洗并且朝向自由端1d延伸，作为固定部分5的外表面5a的延续。
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