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    Vertical stabilizer
    1.
    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.

    Power Allocation Systems for Aircraft
    5.
    发明申请
    Power Allocation Systems for Aircraft 审中-公开

    公开(公告)号：US20190225349A1

    公开(公告)日：2019-07-25

    申请号：US15876298

    申请日：2018-01-22

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Eric A. Sinusas ,  Bradley Paul Regnier ,  Aaron Alexander Acee ,  Charles Hubert Speller ,  Marc Ouellet

    IPC: B64D47/00 ,  H02J4/00

    Abstract: A power system for an aircraft includes a plurality of power consumers each operable to consume power in a range from zero to maximum power demand and collectively capable of consuming a combined maximum power demand, a power source operable to output power to the power consumers and a power allocation system operable to allocate power from the power source to the power consumers based on an operational parameter of the aircraft. The power allocated by the power allocation system is less than the combined maximum power demand of the power consumers, thereby allowing the power source to have a maximum power output less than the combined maximum power demand of the power consumers.

    Ducted rotor stators
    6.
    发明授权
    Ducted rotor stators 有权

    公开(公告)号：US11220329B2

    公开(公告)日：2022-01-11

    申请号：US16266086

    申请日：2019-02-03

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Aaron Alexander Acee ,  Andrew Paul Haldeman

    IPC: B64C27/12 ,  B64D33/08 ,  B64C27/20 ,  F04D29/58 ,  B64C27/82

    Abstract: Systems and methods include providing an aircraft with a ducted rotor assembly. The ducted rotor assembly includes a housing having a duct, a rotor drive mechanism coupled to a rotor system, and a plurality of stators that both structurally support the rotor drive mechanism within the duct of the housing and carry a fluid through internal fluid passages in the plurality of stators to provide cooling to the rotor drive mechanism. Some of the stators carry fluid to the rotor drive mechanism, where the fluid absorbs heat from the rotor drive mechanism, and some of the stators carry fluid away from the rotor drive mechanism. The rotor system generates an airflow over the stators carrying fluid away from the rotor drive mechanism to effect transfer between the fluid and the airflow.

    TAIL ROTOR HOUSING
    7.
    发明申请
    TAIL ROTOR HOUSING 审中-公开

    公开(公告)号：US20190308722A1

    公开(公告)日：2019-10-10

    申请号：US15949660

    申请日：2018-04-10

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Dalton T. Hampton ,  Andrew Paul Haldeman ,  Aaron Alexander Acee ,  Matthew John Hill

    IPC: B64C27/82 ,  B64C27/06

    Abstract: Systems and methods include providing an aircraft with a tail rotor system having a tail rotor housing that forms a cambered airfoil between an upper cambered surface and an lower cambered surface of the tail rotor housing. The cambered airfoil design of the tail rotor housing is capable of providing sufficient lifting force of an aircraft to offload the tail rotor during forward flight, thereby eliminating the need for a traditional vertical stabilizer or fin. The tail rotor blades of the tail rotor system are disposed within an aperture in the tail rotor housing, which minimizes or preferably eliminates exposure of the tail rotor blades to edgewise airflow typically encountered during forward flight, thereby allowing rigid rotor hubs, both in-plane and out-of-plane, to be used in the tail rotor system while also reducing noise output of the tail rotor system.

    ENGAGEMENT AND DISENGAGEMENT OF TAIL ROTOR
    10.
    发明申请
    ENGAGEMENT AND DISENGAGEMENT OF TAIL ROTOR 审中-公开

    公开(公告)号：US20200324884A1

    公开(公告)日：2020-10-15

    申请号：US16382052

    申请日：2019-04-11

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Matthew Michael Wilcox ,  Aaron Alexander Acee

    IPC: B64C27/12 ,  B64D35/02 ,  B64D35/04 ,  B60L7/18 ,  F16D3/06

    Abstract: An exemplary rotorcraft includes a propulsion system including a prime mover and a drive shaft coupled to the prime mover, the drive shaft including a coupling separating the drive shaft into an input shaft and an output shaft, the coupling operable between an engaged position rotationally coupling the input shaft and the output shaft and a disengaged position rotationally disengaging the output shaft from the input shaft, a main rotor coupled to the prime mover, a secondary rotor attached to the output shaft, and a motor coupled to the output shaft.

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