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1.发明申请METHOD FOR ATTACHMENT OF A PRE-ASSEMBLED POWERPLANT AND PYLON ASSEMBLY TO AN AIRCRAFT 审中-公开用于安装预先组装的动力飞轮和飞镖组装给飞机的方法公开(公告)号：US20160167808A1
公开(公告)日：2016-06-16
申请号：US14907345
申请日：2014-07-16
Applicant: Bombardier Inc.
Inventor： Alexandros Iliopoulos , Kevin Shephard , Roger-Andre Bergeron , George Bradley
Abstract: A method for installing a pre-assembled powerplant and pylon assembly on an aircraft comprises determining a first length of a first link, determining a second length of a second link, determining a first distance occupyable by the first link between the pylon and the aircraft, determining a second distance occupyable by the second link between the pylon and the aircraft, determining a first result by subtracting the first distance from the first length, determining a second result by subtracting the second distance from the second length, and determining a third result by adding the first result and the second result. If the third result is less than or equal to zero, the first link is installed between the pylon and the aircraft before the second link If the third result is greater than zero, the second link is installed between the pylon and the aircraft before the first link.
Abstract translation: 一种用于在飞行器上安装预组装的动力装置和塔架组件的方法，包括确定第一连杆的第一长度，确定第二连杆的第二长度，确定由所述塔架和所述飞机之间的第一连杆占据的第一距离， 确定由所述吊架和所述飞机之间的第二连杆占据的第二距离，通过从所述第一长度减去所述第一距离来确定第一结果，通过从所述第二长度减去所述第二距离来确定第二结果，并且通过 添加第一个结果和第二个结果。 如果第三个结果小于或等于零，则在第二个链路之前，第一个链路安装在塔架和飞机之间如果第三个结果大于零，则第二个链路在第一个链路之前安装在塔架和飞机之间 链接。
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公开(公告)号：US11661170B2
公开(公告)日：2023-05-30
申请号：US16608545
申请日：2018-04-26
Applicant: BOMBARDIER INC.
Inventor： Michael Murphy , Jack Araujo , Gary Shum , George Bradley
Abstract: Assemblies and methods for facilitating the assembly of aircraft wings to a fuselage are disclosed. In some embodiments, a wing unit includes features that are configured to define one of more parts of a pressure vessel that is partially defined by the fuselage portion. In some embodiments, the aircraft assemblies disclosed herein comprise one or more first structural interfaces that permit positional adjustment between the wing unit and the fuselage portion so that one or more second structural interfaces may be finished only after such positional adjustment. In some embodiments, the aircraft assemblies disclosed herein comprise one or more structural interfaces that are disposed outside of the wing unit in order to eliminate or reduce the need for assembly personnel to access the interior of the wing unit to carry out the structural assembly of the wing unit to the fuselage portion.
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公开(公告)号：US11891173B2
公开(公告)日：2024-02-06
申请号：US16608978
申请日：2018-04-26
Applicant: BOMBARDIER INC.
Inventor： Michael Murphy , Jack Araujo , Gary Shum , George Bradley
Abstract: Assemblies and methods for facilitating the assembly of aircraft wings to a fuselage are disclosed. In some embodiments, a wing unit includes features that are configured to define one of more parts of a pressure vessel that is partially defined by the fuselage portion. In some embodiments, the aircraft assemblies disclosed herein comprise one or more first structural interfaces that permit positional adjustment between the wing unit and the fuselage portion so that one or more second structural interfaces may be finished only after such positional adjustment. In some embodiments, the aircraft assemblies disclosed herein comprise one or more structural interfaces that are disposed outside of the wing unit in order to eliminate or reduce the need for assembly personnel to access the interior of the wing unit to carry out the structural assembly of the wing unit to the fuselage portion.
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公开(公告)号：US10295970B2
公开(公告)日：2019-05-21
申请号：US14907345
申请日：2014-07-16
Applicant: Bombardier Inc.
Inventor： Alexandros Iliopoulos , Kevin Shephard , Roger-Andre Bergeron , George Bradley
Abstract: A method for installing a pre-assembled powerplant and pylon assembly on an aircraft comprises determining a first length of a first link, determining a second length of a second link, determining a first distance occupyable by the first link between the pylon and the aircraft, determining a second distance occupyable by the second link between the pylon and the aircraft, determining a first result by subtracting the first distance from the first length, determining a second result by subtracting the second distance from the second length, and determining a third result by adding the first result and the second result. If the third result is less than or equal to zero, the first link is installed between the pylon and the aircraft before the second link. If the third result is greater than zero, the second link is installed between the pylon and the aircraft before the first link.
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