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    AERIAL VEHICLE
    41.
    发明公开
    AERIAL VEHICLE 审中-公开

    公开(公告)号：US20230271699A1

    公开(公告)日：2023-08-31

    申请号：US18303498

    申请日：2023-04-19

    申请人： Unmanned Aerospace LLC

    发明人： Gad Shaanan

    IPC分类号： B64C29/00 ,  B64C27/32 ,  B64C27/57 ,  B64C27/59 ,  B64C27/625 ,  B64C27/64 ,  B64C27/82 ,  B64D27/24 ,  B64D31/00 ,  B64D35/02

    CPC分类号： B64C29/0033 ,  B64C27/32 ,  B64C27/57 ,  B64C27/59 ,  B64C27/625 ,  B64C27/64 ,  B64C27/82 ,  B64D27/24 ,  B64D31/00 ,  B64D35/02 ,  G05D1/102

    摘要： Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.

    Aerial vehicle
    42.
    发明授权
    Aerial vehicle 有权

    公开(公告)号：US11661182B2

    公开(公告)日：2023-05-30

    申请号：US17662217

    申请日：2022-05-05

    申请人： Unmanned Aerospace LLC

    发明人： Gad Shaanan

    IPC分类号： B64C29/00 ,  B64C27/32 ,  B64C27/57 ,  B64C27/59 ,  B64C27/625 ,  B64C27/64 ,  B64C27/82 ,  B64D27/24 ,  B64D31/00 ,  B64D35/02 ,  G05D1/10

    CPC分类号： B64C29/0033 ,  B64C27/32 ,  B64C27/57 ,  B64C27/59 ,  B64C27/625 ,  B64C27/64 ,  B64C27/82 ,  B64D27/24 ,  B64D31/00 ,  B64D35/02 ,  G05D1/102

    摘要： Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.

    AERIAL VEHICLE
    44.
    发明申请
    AERIAL VEHICLE 有权

    公开(公告)号：US20220119102A1

    公开(公告)日：2022-04-21

    申请号：US17461719

    申请日：2021-08-30

    申请人： Unmanned Aerospace LLC

    发明人： Gad Shaanan

    IPC分类号： B64C29/00 ,  B64C27/32 ,  B64C27/57 ,  B64C27/59 ,  B64C27/64 ,  B64C27/82 ,  B64C27/625 ,  B64D27/24 ,  B64D31/00 ,  B64D35/02

    摘要： Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.

    Torque Path Coupling Assemblies for Tiltrotor Aircraft
    46.
    发明申请
    Torque Path Coupling Assemblies for Tiltrotor Aircraft 审中-公开

    公开(公告)号：US20190276142A1

    公开(公告)日：2019-09-12

    申请号：US16212045

    申请日：2018-12-06

    申请人： Bell Helicopter Textron Inc.

    发明人： Mark Alan Przybyla

    IPC分类号： B64C27/28 ,  B64C29/00 ,  B64C27/26 ,  B64C27/625 ,  B64C27/68 ,  B64C11/28 ,  F16D41/069 ,  F16D23/04 ,  F16D47/04

    摘要： A rotary propulsion system for a tiltrotor aircraft operable to transition between rotary and non rotary flight modes. The rotary propulsion system includes an engine coupled to a freewheeling unit. A gear system positioned between the freewheeling unit and a proprotor assembly has a torque path coupling assembly disposed between an engine side gear assembly and a rotor side gear assembly. In a disengaged position, the torque path coupling assembly interrupts the torque path between the engine and the proprotor assembly. In an engaged position, the torque path coupling assembly completes the torque path between the engine and the proprotor assembly. A hybrid power unit is configured to accelerate the engine side gear assembly to match the output rotating speed to the input rotating speed enabling the torque path coupling assembly to shift from the disengaged position to the engaged position.

    Main rotor system for helicopters
    47.
    发明授权
    Main rotor system for helicopters 失效
    直升机主转子系统

    公开(公告)号：US5906476A

    公开(公告)日：1999-05-25

    申请号：US855202

    申请日：1997-05-12

    申请人： Paul E. Arlton

    发明人： Paul E. Arlton

    IPC分类号： B64C27/39 ,  B64C1/08 ,  B64C25/52 ,  B64C27/00 ,  B64C27/04 ,  B64C27/10 ,  B64C27/32 ,  B64C27/46 ,  B64C27/467 ,  B64C27/605 ,  B64C27/625 ,  B64C27/82

    CPC分类号： A63H27/12

    摘要： A swashplate is provided for use in helicopters having a vertical main rotor axis. The swashplate includes a bearing, a first race member including a channel, a second race member including a channel, and a third race member including a channel. The channels of the first, second, and third race members cooperate to form a bearing-receiving slot. The bearing is positioned to lie in the bearing-receiving slot. The first and second race members are adjustably coupled to change the respective positions of their channels.

    摘要翻译： 提供斜盘，用于具有垂直主转子轴线的直升机。 斜盘包括轴承，包括通道的第一座圈构件，包括通道的第二座圈构件和包括通道的第三座圈构件。 第一，第二和第三座圈构件的通道协作以形成承载槽。 轴承定位成位于轴承接收槽中。 第一和第二种族构件可调节地联接以改变其通道的各自的位置。

    Yaw control and stabilization system for helicopters
    48.
    发明授权
    Yaw control and stabilization system for helicopters 失效
    直升机的控制和稳定系统

    公开(公告)号：US5597138A

    公开(公告)日：1997-01-28

    申请号：US292719

    申请日：1994-08-18

    申请人： Paul E. Arlton ,  David J. Arlton

    发明人： Paul E. Arlton ,  David J. Arlton

    IPC分类号： B64C1/08 ,  B64C25/52 ,  B64C27/00 ,  B64C27/04 ,  B64C27/10 ,  B64C27/32 ,  B64C27/39 ,  B64C27/467 ,  B64C27/605 ,  B64C27/625 ,  B64C27/82 ,  B64C27/78

    CPC分类号： B64C27/32 ,  A63H27/12 ,  B64C27/10 ,  B64C27/467 ,  B64C27/82

    摘要： A device for stabilizing yaw motion is provided for use on a helicopter having a main rotor rotatable about a main rotor axis, a power source, and a tail rotor boom with a longitudinal axis. The device includes a tail rotor and a gyroscopic mechanism. The tail rotor is mounted to the tail boom of a helicopter and is rotated about a tail rotor axis by the power source to generate a thrust force transverse to the tail boom and offset from the main rotor axis. The gyroscopic mechanism automatically varies the thrust force generated by the tail rotor to oppose yaw motions. The gyroscopic mechanism includes first and second variable pitch gyro arms extending along first and second gyro arm pitch axes, respectively, a support mechanism, and a pitch adjustor linkage. The support mechanism is configured to support the variable pitch gyro arms for pivotable movement about a gyro pivot axis between a nominal orientation and a tilted orientation so that the variable pitch gyro arms pivot about the gyro pivot axis from the nominal orientation toward the tilted orientation in response to yaw motion encountered by the gyro arms during flight to vary the thrust generated by the tail rotor. The pitch adjustor linkage is appended to the first gyro arm to adjust the pitch of the first gyro arm about the first gyro arm pitch axis.

    摘要翻译： 提供一种用于稳定偏转运动的装置，用于具有可绕主转子轴线旋转的主转子的直升机，具有纵向轴线的动力源和尾转子悬臂。 该装置包括尾部转子和陀螺仪机构。 尾部转子安装在直升机的尾臂上，并通过动力源围绕尾部转子轴线旋转，以产生横向于尾臂的推力并从主转子轴线偏移。 陀螺仪机构自动地改变由尾部转子产生的反作用力与偏航运动的反作用力。 陀螺仪机构包括分别沿着第一和第二陀螺仪俯仰轴延伸的第一和第二可变俯仰陀螺臂，支撑机构和俯仰调节器连杆。 支撑机构被配置为支撑可变俯仰陀螺臂，用于在标称方向和倾斜方向之间围绕陀螺仪枢转轴线的可枢转运动，使得可变俯仰陀螺臂围绕陀螺仪枢转轴线从标称方位向倾斜方向枢转 响应于在飞行期间由陀螺仪臂遇到的偏航运动，以改变由尾部转子产生的推力。 俯仰调节器联动装置附加到第一陀螺仪臂以调整第一陀螺仪臂围绕第一陀螺仪俯仰轴的俯仰。