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    HIGH EFFICIENCY STALL PROOF AIRFOIL AND MEANS OF CONTROL
    1.
    发明申请
    HIGH EFFICIENCY STALL PROOF AIRFOIL AND MEANS OF CONTROL 审中-公开

    公开(公告)号：US20190009890A1

    公开(公告)日：2019-01-10

    申请号：US15650861

    申请日：2017-07-15

    申请人： George Paul Baker, JR.

    发明人： George Paul Baker, JR.

    IPC分类号： B64C21/04 ,  B64C3/14 ,  B64C3/38

    CPC分类号： B64C21/04 ,  B64C3/141 ,  B64C3/385 ,  B64C29/0033 ,  B64C2003/143 ,  B64C2003/146

    摘要： A high-efficiency, stall-proof airfoil is an aircraft wing configuration whereby a motive force directly induces gaseous fluid flow across a lifting surface of the airfoil without requiring a movement of the wing through an air space. The airfoil is provided with means to control a pitch, a roll and a yaw motion and to control a position and stability of the aircraft. When not undergoing horizontal displacement, it provides highly efficient use of fuel resources, precluding the formation of drag and its incumbent power consumption. Air pressure at a bottom of the wing remains essentially ambient. Therefore, differential pressure between a lower surface of the wing and an upper surface of the wing maintains its maximum possible quantity. Virtually, all of the power consumed is utilized in a production of lift. Additionally, because lift is generated without regard to an angle-of-attack, forward speed, nor a configuration of a leading edge of the wing, the configuration is essentially stall proof.

    X-Tiltwing Aircraft
    2.
    发明申请
    X-Tiltwing Aircraft 审中-公开

    公开(公告)号：US20180354615A1

    公开(公告)日：2018-12-13

    申请号：US15619765

    申请日：2017-06-12

    申请人： Bell Helicopter Textron Inc.

    发明人： Kirk Landon Groninga ,  Daniel Bryan Robertson

    IPC分类号： B64C29/00 ,  B64C39/08 ,  B64D27/24 ,  B64C15/12

    CPC分类号： B64C29/0033 ,  B64C3/385 ,  B64C15/12 ,  B64C27/28 ,  B64C39/08 ,  B64D27/24 ,  B64D2027/026

    摘要： An aircraft having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes a fuselage and an X-tiltwing that is rotatable relative to the fuselage between a vertical lift orientation and a forward thrust orientation. The X-tiltwing has oppositely disposed V-wing members each having first and second wing sections. In the vertical lift orientation, the first and second wing sections of each V-wing member are generally in the same horizontal plane. In the forward thrust orientation, the first and second wing sections of each V-wing member are generally in the same vertical plane. A distributed propulsion system is attached to the X-tiltwing such that a plurality of propulsion assemblies is attached to each wing section. A flight control system is operably associated with the distributed propulsion system to independently control each of the propulsion assemblies.

    AIRCRAFT COMPRISING A WING FORMED BY A PLURALITY OF DISTRIBUTED AIRFOILS
    3.
    发明申请
    AIRCRAFT COMPRISING A WING FORMED BY A PLURALITY OF DISTRIBUTED AIRFOILS 审中-公开

    公开(公告)号：US20180334253A1

    公开(公告)日：2018-11-22

    申请号：US15773474

    申请日：2016-11-09

    申请人： Airbus SAS

    发明人： Jean-Francois GENESTE

    IPC分类号： B64C39/08 ,  B64C3/38 ,  B64C3/40

    CPC分类号： B64C39/08 ,  B64C3/385 ,  B64C3/40

    摘要： An aircraft including a fuselage and at least one wing comprising, on the aerodynamic plane, a plurality of distributed airfoils separated from one another, numbering more than 10, and arranged inside an enclosing space bearing on the airfoils. The shape and dimensions of the enclosing space correspond to the shape and dimensions of a simple wing of conventional structure, which is adapted to the aircraft taking account of the weight and flight speed of the aircraft. Advantageously, the airfoils are arranged such that the cross-section of the enclosing space in a vertical plane XZ of the aircraft matches the shape of the aerodynamic profile of the simple wing of conventional structure. The airfoils are arranged, for example, to produce a V formation in plan view, with the tip pointing forwards.

    TILT-WING AIRCRAFT
    5.
    发明申请
    TILT-WING AIRCRAFT 审中-公开

    公开(公告)号：US20180086448A1

    公开(公告)日：2018-03-29

    申请号：US15717716

    申请日：2017-09-27

    申请人： Kitty Hawk Corporation

    发明人： Ilan Kroo ,  Herve Martins-Rivas ,  Eric Allison

    IPC分类号： B64C29/00

    CPC分类号： B64C29/0033 ,  B64C3/385 ,  B64C11/001

    摘要： In various embodiments, a tilt-wing aircraft includes a fuselage; a first wing tiltably mounted at or near a forward end of the fuselage; and a second wing rotatably mounted to the fuselage at a position aft of the first wing. A first plurality of rotors is mounted on the first wing at locations on or near a leading edge of the first wing, with two or more rotors being mounted on wing portions on each side of the fuselage; and a second plurality of rotors mounted on the second wing at locations on or near a leading edge of the second wing, with two or more rotors being mounted on wing portions on each side of the fuselage. A flight control system generates a set of actuators and associated actuator parameters to achieve desired forces and moments.

    Rotorcraft with a fuselage and at least one main rotor
    9.
    发明授权
    Rotorcraft with a fuselage and at least one main rotor 有权
    转子陀飞轮与机身和至少一个主转子

    公开(公告)号：US09527577B2

    公开(公告)日：2016-12-27

    申请号：US14605097

    申请日：2015-01-26

    申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

    发明人： Martin Embacher

    IPC分类号： B64C5/16 ,  B64C3/38 ,  B64C27/04 ,  B64C27/82

    CPC分类号： B64C5/16 ,  B64C3/385 ,  B64C27/04 ,  B64C27/82 ,  B64C2027/8236 ,  Y02T50/14

    摘要： A rotorcraft with a fuselage and at least one main rotor, the at least one main rotor being drivable for controlling an associated pitch attitude of the rotorcraft in operation, and the fuselage being equipped with at least one passive wing-type aerodynamic device that is adapted for generating independently of the associated pitch attitude a lift force acting on the fuselage, the lift force being oriented perpendicular to an air flow that is directed in operation of the rotorcraft against the passive wing-type aerodynamic device.

    摘要翻译： 一种具有机身和至少一个主转子的旋翼航空器，所述至少一个主转子可驱动，用于控制所述旋翼航空器在运行中的相关俯仰姿态，并且所述机身装备有至少一个被动式翼型空气动力学装置， 为了独立于相关联的俯仰姿态产生作用在机身上的提升力，提升力垂直于在旋转航空器的操作中被引导以抵抗被动翼型空气动力学装置的空气流定向。