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    Variable directional thrust for helicopter tail anti-torque system
    33.
    发明授权
    Variable directional thrust for helicopter tail anti-torque system 有权

    公开(公告)号：US10377479B2

    公开(公告)日：2019-08-13

    申请号：US15172811

    申请日：2016-06-03

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Thomas Dewey Parsons ,  Carlos Alexander Fenny ,  Erik John Oltheten

    IPC: B64C27/00 ,  B64C27/82

    Abstract: The present invention includes an anti-torque assembly for a helicopter comprising a plurality of fixed blade pitch motors mounted on one or more pivots on the tail boom of the helicopter, wherein the plurality of fixed blade pitch motors on the one or more pivots are adapted to be oriented substantially in-plane with a tail boom of a helicopter during a first mode of operation that comprises a hover mode and wherein the fixed blade pitch motors are adapted to be oriented substantially off-plane from the tail boom of the helicopter during a second mode of helicopter operation that is different from the first mode.

    Aircraft having Radially Extendable Tailboom Assembly
    34.
    发明申请
    Aircraft having Radially Extendable Tailboom Assembly 审中-公开

    公开(公告)号：US20190225334A1

    公开(公告)日：2019-07-25

    申请号：US16371375

    申请日：2019-04-01

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Daniel Bryan Robertson ,  Kirk Landon Groninga ,  Carlos Alexander Fenny

    IPC: B64C29/02 ,  B64C25/32 ,  B64C25/24 ,  B64C11/00 ,  B64C9/02 ,  B64C25/52 ,  B64C25/16

    Abstract: A tail sitter aircraft includes a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis. At least two wings are supported by the forward portion of the fuselage. A distributed propulsion system includes at least one propulsion assembly operably associated with each fixed wing and is operable to provide forward thrust during forward flight and vertical thrust during vertical takeoff, hover and vertical landing. A tailboom assembly extends from the aft portion of the fuselage and includes a plurality of rotatably mounted tail arms having control surfaces and landing members. In a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces. In a landing configuration, the tail arms are radially extended relative to the fuselage axis to form a stable ground contact base with the landing members.

    FORWARD FOLDING ROTOR BLADES
    37.
    发明申请
    FORWARD FOLDING ROTOR BLADES 审中-公开

    公开(公告)号：US20180186445A1

    公开(公告)日：2018-07-05

    申请号：US15593521

    申请日：2017-05-12

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Carlos Alexander Fenny ,  Rohn Lee Olson ,  Andrew James Zahasky

    IPC: B64C11/28 ,  B64C29/00 ,  B64C39/06

    Abstract: A rotor blade rotation system includes two or more rotor blades, each rotor blade in mechanical communication with a hub and pivotable about an axis of rotation, a bearing plate comprising a rotating portion and a non-rotating portion, a fold linkage coupled to the rotating portion of the bearing plate and in mechanical communication with the rotor blade, and an actuator coupled to the non-rotating portion of the bearing plate and operable to reposition the bearing plate from a first position to a second position such that the folding links pivot the rotor blades from a deployed position to a forward folded position.

    Aircraft having Radially Extendable Tailboom Assembly
    38.
    发明申请
    Aircraft having Radially Extendable Tailboom Assembly 审中-公开

    公开(公告)号：US20180050792A1

    公开(公告)日：2018-02-22

    申请号：US15241436

    申请日：2016-08-19

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Daniel Bryan Robertson ,  Kirk Landon Groninga ,  Carlos Alexander Fenny

    IPC: B64C25/16 ,  B64C29/02 ,  B64C9/02 ,  B64C11/00 ,  B64C25/24

    CPC classification number: B64C25/16 ,  B64C9/02 ,  B64C11/006 ,  B64C13/503 ,  B64C25/24 ,  B64C29/02

    Abstract: A tail sitter aircraft includes a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis. A main lifting surface is supported by the forward portion of the fuselage. A propulsion system is operably associated with the main lifting surface and operable to provide thrust during forward flight, vertical takeoff, hover and vertical landing. A tailboom assembly extends from the aft portion of the fuselage. The tailboom assembly includes a plurality of rotatably mounted tail arms having control surfaces and landing members wherein, in a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces and, wherein, in a landing configuration, the tail arms are radially extended relative to one another about the fuselage axis to form a stable ground contact base with the landing members.

    Autorotative enhancement system
    40.
    发明授权
    Autorotative enhancement system 有权
    自动增强系统

    公开(公告)号：US09522730B2

    公开(公告)日：2016-12-20

    申请号：US14934477

    申请日：2015-11-06

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Dudley E. Smith ,  Cory M. Hitte ,  Bryan Marshall ,  Carlos Alexander Fenny

    IPC: B64C27/12 ,  B64D27/24 ,  B64C27/00 ,  B64D27/02

    CPC classification number: B64C27/006 ,  B64C27/12 ,  B64D27/24 ,  B64D2027/026 ,  Y10T29/49117

    Abstract: Embodiments refer generally to systems and methods for providing autorotative enhancement for helicopters using an autorotative assist unit coupled to the transmission of the helicopter. Methods of utilizing an autorotative assist unit as well as retrofitting an autorotative assist unit to an existing helicopter are also disclosed. By employing an autorotative assist unit, improved autorotation can be achieved without the need to increase the weight of the rotor.

    Abstract translation: 实施例总体上涉及用于使用耦合到直升机的传输的自动辅助单元来提供直升机的自动增强的系统和方法。 还公开了利用自动辅助单元以及将自动辅助单元改装到现有直升机的方法。 通过使用自动辅助单元，可以实现改进的自转，而不需要增加转子的重量。

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