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    Flight control system for an aircraft
    1.
    发明授权
    Flight control system for an aircraft 有权

    公开(公告)号：US11745852B2

    公开(公告)日：2023-09-05

    申请号：US18071469

    申请日：2022-11-29

    Applicant: EnExSys Research Inc.

    Inventor： James Henke

    IPC: B64C9/04 ,  B64C9/06 ,  B64C9/18 ,  B64C27/06 ,  B64C27/82 ,  B64C3/54 ,  B64C1/26 ,  B64C3/18

    CPC classification number: B64C3/546 ,  B64C1/26 ,  B64C3/185 ,  B64C9/04 ,  B64C9/06 ,  B64C9/18 ,  B64C27/06 ,  B64C27/82 ,  B64C2027/8272

    Abstract: A simple, safe, and inexpensive flight control system in an aircraft. An anti-torque system for a rotary-wing aircraft has an airfoil with a first surface extending from a first trailing edge and a leading edge, and a second surface extending from a second trailing edge to join the first surface at the leading edge. The airfoil has a first moveable deflector panel pivotally coupled to the first trailing edge, and a second moveable deflector panel pivotally coupled to the second trailing edge. Means are provided to pivot the deflector panels in unison about their respective pivot axes to alter the direction of travel of the airflow downstream of the pivot axes over the surfaces of the deflector panels, thereby producing a lift in a direction perpendicular to the airflow to counteract the torque applied on the aircraft. The flight control system may be arranged within a fixed-wing aircraft.

    Rotary wing aircraft with a shrouded tail propeller
    3.
    发明授权
    Rotary wing aircraft with a shrouded tail propeller 有权

    公开(公告)号：US11697493B2

    公开(公告)日：2023-07-11

    申请号：US17574734

    申请日：2022-01-13

    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

    Inventor： Rupert Pfaller ,  Tobias Ries

    IPC: B64C27/82 ,  B64C27/06

    CPC classification number: B64C27/82 ,  B64C27/06 ,  B64C2027/8236 ,  B64C2027/8254 ,  B64C2027/8272

    Abstract: A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a propeller that is at least configured to propel the rotary wing aircraft in forward flight condition, wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and a shrouded duct that is arranged in the aft region and that forms an inner air duct which accommodates at least partly the propeller, wherein the shrouded duct comprises a yaw and pitch stability enhancement unit for improving yaw and pitch stability of the rotary wing aircraft in the forward flight condition.

    METHOD OF OPTIMIZING SECTIONS OF A TAIL BOOM FOR A ROTARY WING AIRCRAFT
    9.
    发明申请
    METHOD OF OPTIMIZING SECTIONS OF A TAIL BOOM FOR A ROTARY WING AIRCRAFT 审中-公开

    公开(公告)号：US20180029702A1

    公开(公告)日：2018-02-01

    申请号：US15662335

    申请日：2017-07-28

    Applicant: AIRBUS HELICOPTERS

    Inventor： David ALFANO ,  Guillaume LEGRAS ,  Debbie LEUSINK

    IPC: B64C27/82 ,  B64F5/00 ,  B64C27/06

    CPC classification number: B64C27/82 ,  B64C1/0009 ,  B64C27/06 ,  B64F5/00 ,  G06F17/5009 ,  G06F2217/46 ,  Y02T90/50

    Abstract: A method of optimizing sections of a tail boom for a rotary wing aircraft, and also to a tail boom including such sections. The method comprises the step of creating a database characterizing standard sections for a tail boom that give precedence to minimizing a negative lift and/or to increasing a lateral force generated by the air stream from the main rotor of the aircraft flowing over the tail boom, a step of establishing looked-for aerodynamic and structural characteristics for said tail boom, and a step of defining the sections of the tail boom as a function of the standard sections and of the looked-for aerodynamic and structural characteristics. The tail boom as defined in this way optimizes the reduction in the negative lift and/or the increase in the lateral force generated by the air stream from the main rotor.

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