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    Rotorcraft configuration
    1.
    发明申请
    Rotorcraft configuration 审中-公开

    公开(公告)号：US20180319487A1

    公开(公告)日：2018-11-08

    申请号：US15589709

    申请日：2017-05-08

    申请人： Ruben Maier

    发明人： Ruben Maier

    IPC分类号： B64C27/10 ,  B64C27/32 ,  B64C27/18

    CPC分类号： B64C27/10 ,  B64C27/18 ,  B64C27/325 ,  B64C27/57

    摘要： This invention is about a rotorcraft that possesses a configuration made up of the join of three technologies Know separately as “Jet Tip”, “Circulation Control” and “Advancing Blade Concept”. These three technologies synergizes of unusual form allowing the embodiment of a rotorcraft with advantages qualitative and quantitative in fields as flight characteristics, manufacturing, maintenance, security in flight and operational costs.

    NOZZLES FOR A REACTION DRIVE BLADE TIP WITH TURNING VANES
    2.
    发明申请
    NOZZLES FOR A REACTION DRIVE BLADE TIP WITH TURNING VANES 审中-公开

    公开(公告)号：US20170197708A1

    公开(公告)日：2017-07-13

    申请号：US15417595

    申请日：2017-01-27

    申请人： David J. White

    发明人： David J. White

    IPC分类号： B64C27/18 ,  B64C27/46 ,  F01D1/32

    CPC分类号： B64C27/18 ,  B64C27/463 ,  B64C27/473 ,  F01D1/32 ,  F05D2240/242

    摘要： A nozzle for use with a rotor blade for a reaction drive type helicopter includes a first wall, a second wall opposing the first wall, and sidewalls extending between the first wall and the second wall enclosing a cavity having an upstream end and a downstream end. The nozzle includes an inlet section for receiving a gasflow at the upstream end. The distance between the first wall and the second wall reduces to a throat downstream of the inlet section. An expansion section extending from the throat, downstream thereof.

    DEFLECTION CONE IN A REACTION DRIVE HELICOPTER
    6.
    发明申请
    DEFLECTION CONE IN A REACTION DRIVE HELICOPTER 有权
    反应驱动直升机中的偏转锥

    公开(公告)号：US20160272311A1

    公开(公告)日：2016-09-22

    申请号：US14723175

    申请日：2015-05-27

    申请人： David J. White

    发明人： David J. White

    IPC分类号： B64C27/18 ,  B64C27/473

    CPC分类号： B64C27/18 ,  B64C27/473 ,  B64C2027/8245

    摘要： A rotor hub for a reaction drive type helicopter includes a cylindrical sidewall having a top and an open bottom which defines an interior volume. A top plate closes the top of the cylindrical sidewall, and at least two pipe sections extend outwardly from the cylindrical sidewall. Each pipe section extends through the sidewall in communication with the interior volume. A horizontal vane is carried in an inlet of the pipe section and extends horizontally across the inlet. A three dimensional body extends downwardly from a central axis of the top plate into the interior volume.

    摘要翻译： 用于反应驱动型直升机的转子轮毂包括具有顶部和限定内部体积的敞开的底部的圆柱形侧壁。 顶板封闭圆柱形侧壁的顶部，并且至少两个管段从圆柱形侧壁向外延伸。 每个管段延伸通过与内部容积连通的侧壁。 水平叶片承载在管道的入口处，水平延伸穿过入口。 三维体从顶板的中心轴线向下延伸到内部体积中。

    Low speed autogyro yaw control apparatus and method
    7.
    发明授权
    Low speed autogyro yaw control apparatus and method 有权
    低速自动偏航控制装置及方法

    公开(公告)号：US09278754B2

    公开(公告)日：2016-03-08

    申请号：US14288957

    申请日：2014-05-28

    申请人： GROEN BROTHERS AVIATION, INC.

    发明人： Walter Gerd Oskar Sonneborn

    IPC分类号： B64C27/82 ,  B64C27/02 ,  B64C27/18 ,  B64C27/26

    CPC分类号： B64C27/027 ,  B64C27/025 ,  B64C27/18 ,  B64C27/26 ,  B64C27/82 ,  B64C2027/8272

    摘要： Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion device, such as an air jet or a fan may be used. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. Apparatus for generating horizontal lift imbalance induced a tail boom positioned within the downwash of a rotor may also be used, including compressed air vents or lateral or trailing edge flaps.

    摘要翻译： 公开了在低空速和发动机故障中的一个或两个情况下控制旋翼航空器的偏航的装置和方法。 可以使用偏航推进装置，例如空气喷射器或风扇。 气动风扇可以被释放到围绕风扇外部的通道的压缩空气驱动。 用于偏航推进装置和其它系统的动力可由与转子接合的液压泵和/或发电机提供。 低速偏航控制可以由位于支柱的流管内的辅助方向舵提供。 辅助方向舵可以在不使用时向下折叠并与方向舵控制器脱离。 用于产生水平升降机不平衡的装置也可以使用定位在转子的下冲液内的尾臂，包括压缩空气通风口或横向或后缘翼片。

    SYSTEM FOR OPERATING HELICOPTER BLADES WITH COMPRESSED AIR
    8.
    发明申请
    SYSTEM FOR OPERATING HELICOPTER BLADES WITH COMPRESSED AIR 审中-公开
    用压缩空气操作直升机叶片的系统

    公开(公告)号：US20160046368A1

    公开(公告)日：2016-02-18

    申请号：US14780405

    申请日：2014-03-24

    申请人： AIRI RE SRL UNIPERSONALE

    发明人： Riccardo Aichner ,  Pasquale De Rosa

    IPC分类号： B64C27/12 ,  B64C27/48

    CPC分类号： B64C27/12 ,  B64C27/18 ,  B64C27/48

    摘要： A system for operating helicopter blades with compressed air includes at least a first machine having an engine and configured for generating mechanical power to lift the helicopter; at least a second machine having a compressor and configured for generating compressed air for operating the hollow blades, the first machine being coupled with the second machine; and a rotor having a hollow shaft and an oscillating hollow head supporting the blades. The hollow shaft of the rotor internally including a conduit connecting the hollow shaft of the rotor to the hollow head. The oscillating hollow head is an elastic head and comprises an elastomeric flexible and deformable channel connecting the conduit with the blades and having a shape as at least one “V” and a number of branches equal to the number of the blades, the branches being able to guide the compressed air towards nozzles of the blades.

    摘要翻译： 用于使用压缩空气操作直升机叶片的系统包括至少第一机器，其具有发动机并被配置用于产生用于提升直升机的机械动力; 至少第二机器具有压缩机并且被配置用于产生用于操作所述中空叶片的压缩空气，所述第一机器与所述第二机器耦合; 以及具有空心轴和支撑叶片的摆动空心头的转子。 转子的空心轴内部包括将转子的中空轴连接到中空头部的导管。 振荡中空头部是弹性头部，并且包括弹性体柔性且可变形的通道，其将导管与叶片连接，并具有与叶片数量相等的至少一个“V”和多个分支的形状，分支能够 以将压缩空气引导到叶片的喷嘴。

    Oil lubricated swashplate
    9.
    发明授权
    Oil lubricated swashplate 有权
    油润滑斜盘

    公开(公告)号：US09260186B1

    公开(公告)日：2016-02-16

    申请号：US13199712

    申请日：2011-09-07

    申请人： Jacob Johannes van der Westhuizen

    发明人： Jacob Johannes van der Westhuizen

    IPC分类号： B64C27/605 ,  F16C33/66 ,  F01M5/00 ,  B64C27/18

    CPC分类号： B64C27/605 ,  B64C27/025 ,  B64C27/18 ,  B64C27/26 ,  F01M5/005 ,  F16C19/525 ,  F16C33/667 ,  F16C37/007 ,  F16C2229/00 ,  F16C2326/43

    摘要： A rotor system for a reactive drive rotary wing maintains the rigidity of the rotor and eliminates play between flight controls and the rotor by mounting swashplate actuators to a flange rigidly secured to the mast. Apparatus and methods perform thermal management of the rotor in order to avoid bearing failure or loss of bearing preload. Methods include modulating the temperature of oil pumped over one or more of the mast bearing, swashplate bearing, and spindle bearing. The temperature of air passively or actively drawn through rotor may also be modulated to maintain bearing temperature within a predetermined range. The rotor includes structures for reducing pressure losses and drag on components due to air flow through the rotor. A rotor facilitates thermal management by oil and air flow.

    摘要翻译： 用于无功驱动旋转翼的转子系统保持转子的刚度，并且通过将斜盘致动器安装到刚性地固定到桅杆的凸缘上来消除飞行控制器和转子之间的游隙。 装置和方法对转子进行热管理，以避免轴承故障或轴承预载的损失。 方法包括调节在一个或多个桅杆轴承，斜盘轴承和主轴轴承上泵送的油温。 无源或主动地通过转子吸入的空气的温度也可被调制以将轴承温度保持在预定范围内。 转子包括用于减少由于空气流过转子而导致的部件上的压力损失和阻力的结构。 转子有助于通过油和空气流进行热管理。

    Heliplane rotor thermal management for maintaining dimensional stability
    10.
    发明授权
    Heliplane rotor thermal management for maintaining dimensional stability 有权
    Heliplane转子热管理，用于维持尺寸稳定性

    公开(公告)号：US08950699B1

    公开(公告)日：2015-02-10

    申请号：US13199681

    申请日：2011-09-07

    申请人： Jacob Johannes van der Westhuizen

    发明人： Jacob Johannes van der Westhuizen

    IPC分类号： B64C27/18 ,  B64C27/32 ,  B64C27/02

    CPC分类号： B64C27/32 ,  B64C13/12 ,  B64C27/025 ,  B64C27/18 ,  B64C27/26 ,  B64C27/48 ,  B64C27/56 ,  B64C27/605 ,  B64C27/72 ,  B64C2027/4736 ,  B64D31/04 ,  F16C33/667 ,  Y10T74/20612

    摘要： A rotor system is disclosed for a reactive drive rotary wing aircraft. Apparatus and methods are disclosed for maintaining the rigidity of the rotor and eliminating play between flight controls and the rotor by mounting swashplate actuators to a flange rigidly secured to the mast. Apparatus and methods are disclosed for thermal management of the rotor in order to avoid bearing failure or loss of bearing preload. Methods include modulating the temperature of oil pumped over one or more of the mast bearing, swashplate bearing, and spindle bearing. The temperature of air passively or actively drawn through rotor may also be modulated to maintain bearing temperature within a predetermined range. Structures for reducing pressure losses and drag on components due to air flow through the rotor are also disclosed. A rotor facilitating thermal management by oil and air flow is also disclosed.

    摘要翻译： 公开了一种用于无功驱动旋翼飞机的转子系统。 公开了用于维持转子的刚性并且通过将斜盘致动器安装到刚性地固定到桅杆的凸缘上来消除飞行控制器和转子之间的作用的装置和方法。 公开了用于转子的热管理的装置和方法，以避免轴承故障或轴承预载的损失。 方法包括调节在一个或多个桅杆轴承，斜盘轴承和主轴轴承上泵送的油温。 无源或主动地通过转子吸入的空气的温度也可被调制以将轴承温度保持在预定范围内。 还公开了用于减少由于通过转子的气流引起的部件上的压力损失和阻力的结构。 还公开了通过油和空气流促进热管理的转子。