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217 条记录 (耗时 0.022 秒)

    DETERMINING BENDING STATE OF AIRCRAFT WING
    1.
    发明公开
    DETERMINING BENDING STATE OF AIRCRAFT WING 审中-公开

    公开(公告)号：US20240174372A1

    公开(公告)日：2024-05-30

    申请号：US18522340

    申请日：2023-11-29

    申请人： Airbus Operations Limited

    发明人： Dylan Vignola

    IPC分类号： B64D37/00 ,  B64C3/34

    CPC分类号： B64D37/005 ,  B64C3/34

    摘要： An aircraft including a wing, a first pressure sensor and a second pressure sensor, wherein each pressure sensor is configured to measure pressure of a liquid within the wing and has a known position within the wing. The aircraft includes a processing system configured to receive first pressure data from the first pressure sensor, receive second pressure data from the second pressure sensor, and determine a bending state of the wing based on the first pressure data, the second pressure data, and the known positions of the first and second pressure sensors within the wing.

    Wingbox with removable fuel tank
    4.
    发明授权
    Wingbox with removable fuel tank 有权

    公开(公告)号：US11834169B2

    公开(公告)日：2023-12-05

    申请号：US17652355

    申请日：2022-02-24

    申请人： Airbus Operations Limited

    发明人： William Tulloch

    IPC分类号： B64C3/34 ,  B64C3/18 ,  B64D37/30

    CPC分类号： B64C3/34 ,  B64C3/185 ,  B64D37/30

    摘要： An aircraft wingbox assembly is disclosed having a wingbox with an upper cover, a lower cover and a pair of spars; a plurality of ribs in the wingbox. The ribs divide the wingbox into bays. A fuel tank is in a first one of the bays. One of the spars includes a spar hole which is configured to enable the fuel tank to be removed from the first one of the bays through the spar hole.

    AIRCRAFT FUEL TANK JOINTS AND METHODS OF ASSEMBLING THE SAME
    6.
    发明申请
    AIRCRAFT FUEL TANK JOINTS AND METHODS OF ASSEMBLING THE SAME 有权

    公开(公告)号：US20230081133A1

    公开(公告)日：2023-03-16

    申请号：US17473701

    申请日：2021-09-13

    申请人： The Boeing Company

    发明人： Justin Albright

    IPC分类号： B64C3/34 ,  B64C3/18 ,  B64C3/26 ,  B64D37/32

    摘要： Aircraft fuel tank joints and related methods. The aircraft fuel tank joints comprise a first structural member comprising a first joint face, a second structural member comprising a second joint face that is spaced apart from the first joint face by a gap, a sealant dam compressed between the first and second joint faces and defining the gap, a first sealant zone on a first side of the sealant dam within the gap, and a second sealant zone on a second side of the sealant dam within the gap. The sealant dam and the first and second zones of sealant substantially fill, and form three independent seals within, the gap. The methods comprise substantially filling the gap with the sealant dam, the first zone of sealant, and the second zone of sealant, and compressing the sealant dam between the first and second faces to the compressed thickness.

    Aircraft Airframes having Integral Fuel Tanks
    7.
    发明申请
    Aircraft Airframes having Integral Fuel Tanks 有权

    公开(公告)号：US20220388628A1

    公开(公告)日：2022-12-08

    申请号：US17340837

    申请日：2021-06-07

    申请人： Textron Innovations Inc.

    发明人： Bradley P. Regnier ,  Zachary E. Dailey ,  Aaron Alexander Acee ,  Brian J. Cox

    IPC分类号： B64C3/34 ,  B64C29/00 ,  B64C3/18 ,  B64D37/30 ,  B64D37/04 ,  B64C1/06 ,  B64C1/18

    摘要： An aircraft includes a fuselage airframe and a wing airframe that is subject to flight loads. The fuselage airframe includes fore/aft floor beams having a plurality of floor intercostals laterally extending therebetween and fore/aft roof beams with a plurality of roof intercostals laterally extending therebetween. Each of a plurality of cabin frames extends generally vertically between respective floor and roof beams. The wing airframe includes forward and aft wing spars with a plurality of wing ribs extending therebetween. At least one fuel tank, that is configured to contain a pressurized fuel such as pressurized hydrogen fuel, integrally forms at least a portion of one of the beams, the intercostals, the frames, the spars and/or the ribs such that the fuel tank is subject to the flight loads.

    Electrical isolator fitting
    8.
    发明授权
    Electrical isolator fitting 有权

    公开(公告)号：US11352147B2

    公开(公告)日：2022-06-07

    申请号：US16533239

    申请日：2019-08-06

    申请人： SHORT BROTHER PLC

    发明人： Stephen Walters ,  David Chivers

    IPC分类号： B64D37/32 ,  H01B17/38 ,  B64C3/34

    摘要： An isolator fitting for an opening in a metallic rib of an aircraft wing. The isolator fitting has first isolator mountable to the rib to position a first isolator opening in alignment with the opening of the rib. A second isolator is mountable to the rib and has a nut housing segment defining a second isolator opening to be positioned in alignment with the opening of the rib. A conduit extends between a first end and a second end, and a nut is mountable about an outer surface of the conduit to abut against the first isolator and mount the conduit thereto. The conduit is positionable to extend through the opening of the rib and through the first and second isolator openings to position the nut within the nut housing segment of the second isolator such that the nut housing segment is positioned between the nut and the rib.

    SYSTEMS, METHODS, AND AIRCRAFT FOR MANAGING CENTER OF GRAVITY
    9.
    发明申请
    SYSTEMS, METHODS, AND AIRCRAFT FOR MANAGING CENTER OF GRAVITY 有权

    公开(公告)号：US20220024589A1

    公开(公告)日：2022-01-27

    申请号：US17403175

    申请日：2021-08-16

    申请人： ZSM HOLDINGS LLC

    发明人： Etan D. KARNI ,  Scott David REWERTS ,  Mark Emil LUNDSTROM

    IPC分类号： B64D9/00 ,  B64C1/22 ,  B64C1/14 ,  B64C17/08 ,  B64C3/34 ,  B64C3/32 ,  B64D37/04 ,  B64C1/20

    摘要： Systems, methods, and aircraft for managing center of gravity (CG) while transporting large cargo are described. Management of CG is achieved in many ways. In some instances, the aircraft itself is designed to assist in managing CG by providing fuel tanks that minimize the impact of fuel on the net CG of the aircraft. The fuel tanks utilize only a small amount of available volume in the wings for fuel. Disclosures related to properly managing CG while loading wind turbines onto cargo aircraft are also provided. The CG management techniques provided for herein allow for the transportation of wind turbine blades via aircraft, running counter to the typical rail or truck transportation of the same. One such management technique includes accounting for how a rotation of the blades when loading impacts the CG of the blades, and thus taking this into account when placing the blades in the aircraft.