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    Aircraft adapter
    1.
    发明授权
    Aircraft adapter 有权

    公开(公告)号：US10800526B2

    公开(公告)日：2020-10-13

    申请号：US15591705

    申请日：2017-05-10

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Alan Carl Ewing ,  Antonio Cardenas Munguia

    IPC: B64D7/00 ,  B64D7/06 ,  B64D37/04 ,  B64D37/12

    Abstract: An adapter is disclosed for use with an aircraft including wingtip stations defining mounting surfaces. The adapter is configured and dimensioned for connection to the wingtip stations on either wing of the aircraft to facilitate the connection of a weapons rack to the aircraft. The adapter includes a backing plate, and a body connected to the backing plate that is configured and dimensioned to support the weapons rack. The backing plate is configured and dimensioned in correspondence with the mounting surfaces defined by the wingtip stations. The body includes a base extending outwardly from the backing plate along a first axis, and a support member extending outwardly from the base along a second axis. In one particular embodiment of the adapter, the first and second axes define an angle of 45° therebetween.

    Aircraft Adapter
    2.
    发明申请
    Aircraft Adapter 审中-公开

    公开(公告)号：US20180327094A1

    公开(公告)日：2018-11-15

    申请号：US15591705

    申请日：2017-05-10

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Alan Carl Ewing ,  Antonio Cardenas Munguia

    IPC: B64D7/00 ,  B64D37/04

    Abstract: An adapter is disclosed for use with an aircraft including wingtip stations defining mounting surfaces. The adapter is configured and dimensioned for connection to the wingtip stations on either wing of the aircraft to facilitate the connection of a weapons rack to the aircraft. The adapter includes a backing plate, and a body connected to the backing plate that is configured and dimensioned to support the weapons rack. The backing plate is configured and dimensioned in correspondence with the mounting surfaces defined by the wingtip stations. The body includes a base extending outwardly from the backing plate along a first axis, and a support member extending outwardly from the base along a second axis. In one particular embodiment of the adapter, the first and second axes define an angle of 45° therebetween.

    Extended Range Quad Tiltrotor Aircraft
    6.
    发明申请
    Extended Range Quad Tiltrotor Aircraft 审中-公开

    公开(公告)号：US20190144109A1

    公开(公告)日：2019-05-16

    申请号：US15815411

    申请日：2017-11-16

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Alan Carl Ewing ,  Eric Ricardo Gonzalez ,  Mark Loring Isaac ,  Frank Bradley Stamps

    IPC: B64C29/00 ,  B64C27/26 ,  B64C27/28 ,  G05D1/08

    Abstract: A quad tiltrotor aircraft has a longitudinally extending fuselage with forward and aft stations. A forward wing having first and second outboard ends extends laterally from the forward station. An aft wing having first and second outboard ends extends laterally from the aft station. First and second forward rotors are respectively coupled proximate the first and second outboard ends of the forward wing and are tiltable relative to the forward wing between vertical lift and forward thrust orientations. First and second aft rotors are respectively coupled proximate the first and second outboard ends of the aft wing and are tiltable relative to the aft wing between vertical lift and forward thrust orientations. The forward rotors are higher disk-loading rotors than the aft rotors. The aft rotors are foldable in the forward flight mode to provide extended range for the quad tiltrotor aircraft.

    Method and apparatus for aircraft sensor and actuator failure protection using reconfigurable flight control laws
    7.
    发明授权
    Method and apparatus for aircraft sensor and actuator failure protection using reconfigurable flight control laws 有权

    公开(公告)号：US10183743B2

    公开(公告)日：2019-01-22

    申请号：US15646680

    申请日：2017-07-11

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Shyhpyng Jack Shue ,  John James Corrigan ,  Eric Thomas Bird ,  Tommie Lynn Wood ,  Alan Carl Ewing

    IPC: B64C27/54 ,  G05D1/00 ,  G05D1/08 ,  G05B19/042 ,  G05B23/02 ,  B64C19/00

    Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators. An exemplary aircraft for using the method and apparatus of a reconfigurable flight control system is a quad tilt rotor. The quad tilt rotor provides a variety of redundant and back-actuators, as such, having a robust and highly qualified reconfigurable flight control system is very desirable.

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