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205 条记录 (耗时 0.02 秒)

    Vertical Take-Off and Landing Aircraft
    51.
    发明申请
    Vertical Take-Off and Landing Aircraft 审中-公开

    公开(公告)号：US20180305005A1

    公开(公告)日：2018-10-25

    申请号：US15494780

    申请日：2017-04-24

    申请人： AFS-DV VTOL Technologies Corporation

    发明人： Robert W. Parks ,  Francesco Giannini ,  Diana Siegel ,  Jan D. Lienhard

    IPC分类号： B64C27/26 ,  B64C27/30 ,  B64D27/24 ,  B64C39/12 ,  B64C29/00

    CPC分类号： B64C27/26 ,  B64C27/30 ,  B64C29/0025 ,  B64C39/08 ,  B64C39/12 ,  B64D27/24

    摘要： Disclosed herein is a vertical take-off and landing (VTOL) aircraft having three lifting surfaces and separate lift and cruise systems. The VTOL aircraft may include a fuselage having a roll axis, a thrust rotor to produce a propulsion thrust, first and second rotor booms, first and second canard surfaces, first and second wing surfaces, first and second tail surfaces, and a plurality of lift rotors to produce a lifting thrust force. The plurality of lift rotors includes a first plurality of lift rotors positioned on the first rotor boom and a second plurality of lift rotors positioned on the second rotor boom. The first and second rotor booms may be substantially parallel to the roll axis of the fuselage, where the fuselage is positioned between the first and second rotor booms. Each of the first and second rotor booms may be secured to the aircraft at three locations.

    Bimodal propeller aircraft
    53.
    发明授权
    Bimodal propeller aircraft 有权

    公开(公告)号：US09957042B1

    公开(公告)日：2018-05-01

    申请号：US15447028

    申请日：2017-03-01

    申请人： Kitty Hawk Corporation

    发明人： Damon Vander Lind ,  Gregory Mainland Horn

    IPC分类号： B64C29/00 ,  B64C27/30 ,  B64C11/28

    CPC分类号： B64C29/0033 ,  B64C11/28 ,  B64C27/30

    摘要： A bimodal propeller aircraft is disclosed. In various embodiments, the aircraft is flown using a cruise propeller and a hover propeller. The hover propeller has one or more folding blades optimized to provide lift to the aircraft in a first flight mode. The cruise propeller is optimized to provide thrust in a second flight mode. In the second flight mode, the one or more folding blades of the hover propeller may remain in a stowed position.

    Tiltrotor Aircraft having Rotary and Non Rotary Flight Modes
    56.
    发明申请
    Tiltrotor Aircraft having Rotary and Non Rotary Flight Modes 审中-公开

    公开(公告)号：US20170144746A1

    公开(公告)日：2017-05-25

    申请号：US15428687

    申请日：2017-02-09

    申请人： Bell Helicopter Textron Inc.

    发明人： Troy Cyril Schank ,  Carlos Alexander Fenny ,  Andrew Maresh ,  Chyau-Song Tzeng

    IPC分类号： B64C11/28 ,  B64C27/30 ,  B64C11/32 ,  B64C29/00

    CPC分类号： B64C11/28 ,  B64C27/30 ,  B64C29/0033 ,  B64D27/20

    摘要： A mechanism for transitioning a tiltrotor aircraft between rotary and non rotary flight modes. The mechanism includes a gimbal lock positioned about a mast that is operable to selectively enable and disable a gimballing degree of freedom of a rotor assembly relative to the mast. A blade stop assembly, positioned about the mast, includes a plurality of arms having a radially contracted orientation and a radially extended orientation. A blade lock assembly is operably associated with each rotor blade assembly. Each blade lock assembly is operable to selectively enable and disable a folding degree of freedom and a pitching degree of freedom of the respective rotor blade assembly. A swash plate is operable to change the pitch of the rotor blade assemblies in the rotary flight mode and fold the rotor blade assemblies in the non rotary flight mode.

    Collapsible airfoil spooled retractable rotor
    57.
    发明授权
    Collapsible airfoil spooled retractable rotor 有权
    可折叠翼型卷轴可伸缩转子

    公开(公告)号：US09586674B2

    公开(公告)日：2017-03-07

    申请号：US14517641

    申请日：2014-10-17

    申请人： Kenneth A. Cote

    发明人： Kenneth A. Cote

    IPC分类号： B64C11/00 ,  B64C27/26 ,  B64C27/30 ,  B64C27/473

    CPC分类号： B64C11/003 ,  B64C27/26 ,  B64C27/30 ,  B64C27/473 ,  Y02T50/66

    摘要： A retractable rotor system for an aircraft includes a rotor blade with a leading edge, a trailing edge, and an internal collapsible web. The leading edge includes a flexible portion whose lower edge contacts but is not structurally joined to the lower skin. When the leading edge is peeled forward from the lower skin, the blade elastically collapses to the thickness of its constituent layers. The rotor blade extends through a support frame connectable to the aircraft to secure the rotor blade to a spool. Rotating the spool retracts the rotor blade through the support frame while pulling the rotor blade over a fixed actuating member, placing the rotor blade in the collapsed condition and winding the rotor blade onto the spool. Rotating the spool in the opposite direction unwinds the rotor blade from the spool, through the frame, causing the rotor blade to relax into the expanded condition.

    摘要翻译： 用于飞机的可伸缩转子系统包括具有前缘，后缘和内部可折叠腹板的转子叶片。 前缘包括其下边缘接触但不结构地连接到下皮肤的柔性部分。 当前缘从下部皮肤向前剥离时，刀片弹性地塌陷其构成层的厚度。 转子叶片延伸穿过可连接到飞行器的支撑框架，以将转子叶片固定到线轴上。 旋转卷轴将转子叶片通过支撑框架缩回，同时将转子叶片拉到固定的致动构件上，将转子叶片放置在折叠状态并将转子叶片卷绕到卷轴上。 沿相反方向旋转阀芯，使转子叶片从卷轴穿过框架，使转子叶片松弛进入膨胀状态。