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    VERTICAL STABILIZER
    2.
    发明申请
    VERTICAL STABILIZER 审中-公开

    公开(公告)号：US20190291848A1

    公开(公告)日：2019-09-26

    申请号：US15933106

    申请日：2018-03-22

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Sebastien Duval ,  Guillaume Noiseux-Boucher ,  Aaron Alexander Acee

    IPC: B64C5/06 ,  B64C27/82

    Abstract: Systems and methods include providing an aircraft with a vertical stabilizer system having a vertical stabilizer operatively coupled to a tail boom, tail rotor gearbox, or other component of the aircraft at a forward attachment and an aft attachment. The vertical stabilizer is selectively rotatable to adjust an angle of attack of the vertical stabilizer with respect to a forward flight direction of the aircraft. The vertical stabilizer is rotatable between a forward flight position having a substantially small degree angle of attack and a hover or lateral movement position having a substantially ninety degree angle of attack.

    Vertical stabilizer
    5.
    发明授权
    Vertical stabilizer 有权

    公开(公告)号：US11046417B2

    公开(公告)日：2021-06-29

    申请号：US15933106

    申请日：2018-03-22

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Sebastien Duval ,  Guillaume Noiseux-Boucher ,  Aaron Alexander Acee

    IPC: B64C5/06 ,  B64C27/82 ,  B64C5/12

    Abstract: Systems and methods include providing an aircraft with a vertical stabilizer system having a vertical stabilizer operatively coupled to a tail boom, tail rotor gearbox, or other component of the aircraft at a forward attachment and an aft attachment. The vertical stabilizer is selectively rotatable to adjust an angle of attack of the vertical stabilizer with respect to a forward flight direction of the aircraft. The vertical stabilizer is rotatable between a forward flight position having a substantially small degree angle of attack and a hover or lateral movement position having a substantially ninety degree angle of attack.

    FLEXIBLE RADIAL INLET PLENUM
    6.
    发明申请
    FLEXIBLE RADIAL INLET PLENUM 审中-公开

    公开(公告)号：US20190276157A1

    公开(公告)日：2019-09-12

    申请号：US15915632

    申请日：2018-03-08

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Marc Ouellet ,  Guillaume Noiseux-Boucher

    IPC: B64D29/04 ,  B64D33/02

    Abstract: A radial inlet plenum a forward panel, an aft panel, and a cowling extending therebetween. The forward and aft panels are coupled between the cowling and an engine. The forward and aft panels include flexible sections to allow the engine to translate radially and axially, as well as rotate, relative to the cowling.

    Aircraft Restraint Systems with Fixed Default Mode
    7.
    发明申请
    Aircraft Restraint Systems with Fixed Default Mode 审中-公开

    公开(公告)号：US20190168878A1

    公开(公告)日：2019-06-06

    申请号：US15832689

    申请日：2017-12-05

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Eric A. Sinusas ,  Olivier Andre Boisvert ,  Guillaume Noiseux-Boucher ,  Steve Loveland ,  Sebastien Duval

    IPC: B64D11/06

    Abstract: A modal restraint system for an occupant of a seat of an aircraft includes a strap feeder unit and a strap selectively retractable into and extendable from the strap feeder unit. The strap is positionable adjacent to the occupant so as to dispose the occupant between the strap and the seat. The strap feeder unit is adapted to switch between a plurality of modes including a fixed mode and an unfixed mode. The strap is substantially unextendable from the strap feeder unit in the fixed mode. The strap is extendable from and retractable into the strap feeder unit in the unfixed mode. The strap feeder unit is in the fixed mode by default. The strap feeder unit is operable to switch to the unfixed mode in response to a user input, thereby increasing freedom of movement of the occupant relative to the seat of the aircraft.

    Aircraft Door Structure
    9.
    发明申请
    Aircraft Door Structure 审中-公开

    公开(公告)号：US20200283119A1

    公开(公告)日：2020-09-10

    申请号：US16293890

    申请日：2019-03-06

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Pier-Alexandre Pelletier ,  Guillaume Noiseux-Boucher

    IPC: B64C1/14 ,  E05B83/40 ,  E05B85/04 ,  E05B85/12 ,  E05B79/12

    Abstract: A door structure and method of assembling same. The door structure includes a door frame delimiting a door opening. The door frame has a latch housing portion defining a latch housing cavity extending along a length of the door frame. A door is mounted to the door frame and displaceable between an open position and a closed position. The door has a peripheral portion with an outer wall and an inner wall delimiting a cavity of the peripheral portion. A door latch assembly has a first latch member fixedly mounted to the door, and a door manipulator mounted to one of the door and the fuselage and coupled to a second latch member within the latch housing cavity of the door frame. The door manipulator is configured to be manipulated to displace the second latch member to engage and disengage the first latch member.

    HIGH-VISIBILITY IMPACT DETECTION SYSTEM AND METHOD OF PREPARING THE SAME
    10.
    发明申请
    HIGH-VISIBILITY IMPACT DETECTION SYSTEM AND METHOD OF PREPARING THE SAME 审中-公开

    公开(公告)号：US20200094994A1

    公开(公告)日：2020-03-26

    申请号：US16138865

    申请日：2018-09-21

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Guillaume Noiseux-Boucher

    IPC: B64F5/60 ,  B64C1/12 ,  B64C27/00 ,  G01N21/88

    Abstract: A component equipped with a high-visibility impact detection system. The component includes a composite layer with a minimum impact energy level known to potentially cause damage to the composite layer, a high-visibility layer covering at least a portion of the composite layer, and a top layer covering the high-visibility layer. The top layer is configured to fracture, and expose the high-visibility layer, when subjected to an impact energy level greater than or equal to the minimum impact energy level known to potentially cause damage to the composite layer.

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