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公开(公告)号：US20240309686A1
公开(公告)日：2024-09-19
申请号：US18183228
申请日：2023-03-14
申请人： The Boeing Company
发明人： Michael T. Mortland
CPC分类号： E05D3/06 , B64C1/1423 , E05Y2201/21 , E05Y2201/254 , E05Y2201/456 , E05Y2201/624 , E05Y2201/686 , E05Y2900/502
摘要： An articulated hinge assembly for connecting a door to a fuselage of an aircraft includes an articulated hinge arm having a first hinge member pivotably coupled to a second hinge member at an elbow. A fuselage fitting is pivotably coupled to a fuselage bracket and a door fitting is pivotably coupled to a door bracket of the door. The articulated hinge arm is movable from a collapsed position to an expanded position to move the door from a door closed position to a door open position. The articulated hinge assembly includes a linkage assembly coupled to the articulated hinge arm, the fuselage fitting and the door fitting controlling movement of the first hinge member and the second hinge member relative to each other and relative to the fuselage fitting. The linkage assembly controls positioning of the door.
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公开(公告)号：US11821253B2
公开(公告)日：2023-11-21
申请号：US17450137
申请日：2021-10-06
申请人： The Boeing Company
发明人： Michael T. Mortland
CPC分类号： E05F5/025 , E05F5/06 , E05Y2201/224 , E05Y2201/682 , E05Y2201/706 , E05Y2600/622 , E05Y2600/626 , E05Y2900/502 , E05Y2900/531
摘要： A stop fitting assembly for an aircraft door is presented. The stop fitting assembly comprises a stop fitting, a connecting bracket, and a number of removable fasteners. The stop fitting has a shaft, a flange extending outward from the shaft, and a number of holes extending through the shaft. The connecting bracket has a stop fitting receptacle configured to receive the shaft of the stop fitting, a number of holes extending through walls of the stop fitting receptacle, the connecting bracket configured to be joined to structural members of the aircraft door. The number of removable fasteners is configured to pass through the number of holes in the stop fitting and the number of holes of the stop fitting receptacle to removably join the stop fitting and the connecting bracket.
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公开(公告)号：US20240133225A1
公开(公告)日：2024-04-25
申请号：US17971857
申请日：2022-10-23
申请人： THE BOEING COMPANY
发明人： Michael T. Mortland
IPC分类号： E05D3/12 , E05D5/06 , E05F15/614 , E05F15/63
CPC分类号： E05D3/122 , E05D3/127 , E05D5/062 , E05F15/614 , E05F15/63 , B64C1/1407
摘要： A hinge assembly for connecting a door to a fuselage of an aircraft includes a hinge arm having a fuselage fitting pivotably coupled to a fuselage rotatable interface and a door fitting pivotably coupled to a door rotatable interface. The hinge assembly includes a programmable gear assembly coupled to the hinge arm allowing the hinge arm to pivot around the fuselage fitting when the door is moved from a door closed position to a door open position and causing the door to maintain in a generally parallel orientation relative to the fuselage between the door closed position to the door open position. The programmable gear assembly includes a fuselage gear coupled to the fuselage fitting, a door gear coupled to the door fitting, and a rack operably coupled between the fuselage gear and the door gear.
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公开(公告)号：US20210139129A1
公开(公告)日：2021-05-13
申请号：US16679950
申请日：2019-11-11
申请人： The Boeing Company
发明人： Michael T. Mortland
摘要： Offset drive arm actuation of inboard flaps is disclosed. A disclosed example apparatus includes an inboard flap support for moving an inboard flap. The inboard flap support includes an offset drive arm extending between a first attachment point of the inboard flap and a first pivot of a support, and a linkage extending between a second attachment point of the inboard flap positioned at a different position from the first attachment point and a second pivot of the support.
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公开(公告)号：US11661166B2
公开(公告)日：2023-05-30
申请号：US17450136
申请日：2021-10-06
申请人： The Boeing Company
发明人： Michael T. Mortland
CPC分类号： B64C1/1423 , B64C2001/009
摘要： A coaxial pressure lock assembly of an aircraft door, the coaxial pressure lock assembly comprises a pressure panel positioned adjacent an opening formed in the aircraft door such that the pressure panel is seated in the opening when the pressure panel is in a closed position, and a latch shaft extending through a clevis of the pressure panel. The latch shaft is configured to rotate about a latch shaft rotational axis extending through the latch shaft. The pressure panel is rotatable between the closed position and an open position about the latch shaft rotational axis. The latch shaft is a portion of a latch assembly configured to allow or prevent unlatching the aircraft door.
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公开(公告)号：US11338905B2
公开(公告)日：2022-05-24
申请号：US16679950
申请日：2019-11-11
申请人： The Boeing Company
发明人： Michael T. Mortland
摘要： Offset drive arm actuation of inboard flaps is disclosed. A disclosed example apparatus includes an inboard flap support for moving an inboard flap. The inboard flap support includes an offset drive arm extending between a first attachment point of the inboard flap and a first pivot of a support, and a linkage extending between a second attachment point of the inboard flap positioned at a different position from the first attachment point and a second pivot of the support.
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公开(公告)号：US20190092454A1
公开(公告)日：2019-03-28
申请号：US15719393
申请日：2017-09-28
申请人： The Boeing Company
发明人： Michael T. Mortland
摘要： Example high-fowler flap actuation apparatus and related methods are disclosed. An example apparatus includes a control surface operatively coupled to a wing of an aircraft via a first support arm and a drive arm, the drive arm linearly extendible from a retracted position to a deployed position, the deployed position including the control surface extended away from the wing at a first angle with respect to the wing.
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公开(公告)号：US20220145685A1
公开(公告)日：2022-05-12
申请号：US17450137
申请日：2021-10-06
申请人： The Boeing Company
发明人： Michael T. Mortland
摘要： A stop fitting assembly for an aircraft door is presented. The stop fitting assembly comprises a stop fitting, a connecting bracket, and a number of removable fasteners. The stop fitting has a shaft, a flange extending outward from the shaft, and a number of holes extending through the shaft. The connecting bracket has a stop fitting receptacle configured to receive the shaft of the stop fitting, a number of holes extending through walls of the stop fitting receptacle, the connecting bracket configured to be joined to structural members of the aircraft door. The number of removable fasteners is configured to pass through the number of holes in the stop fitting and the number of holes of the stop fitting receptacle to removably join the stop fitting and the connecting bracket.
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公开(公告)号：US20220135201A1
公开(公告)日：2022-05-05
申请号：US17450136
申请日：2021-10-06
申请人： The Boeing Company
发明人： Michael T. Mortland
摘要： A coaxial pressure lock assembly of an aircraft door, the coaxial pressure lock assembly comprises a pressure panel positioned adjacent an opening formed in the aircraft door such that the pressure panel is seated in the opening when the pressure panel is in a closed position, and a latch shaft extending through a clevis of the pressure panel. The latch shaft is configured to rotate about a latch shaft rotational axis extending through the latch shaft. The pressure panel is rotatable between the closed position and an open position about the latch shaft rotational axis. The latch shaft is a portion of a latch assembly configured to allow or prevent unlatching the aircraft door.
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公开(公告)号：US10974816B2
公开(公告)日：2021-04-13
申请号：US15719393
申请日：2017-09-28
申请人： The Boeing Company
发明人： Michael T. Mortland
摘要： Example high-fowler flap actuation apparatus and related methods are disclosed. An example apparatus includes a control surface operatively coupled to a wing of an aircraft via a first support arm and a drive arm, the drive arm linearly extendible from a retracted position to a deployed position, the deployed position including the control surface extended away from the wing at a first angle with respect to the wing.
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