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    Rotor blade component cooling
    1.
    发明授权
    Rotor blade component cooling 有权
    转子叶片部件冷却

    公开(公告)号：US09090343B2

    公开(公告)日：2015-07-28

    申请号：US13272781

    申请日：2011-10-13

    申请人： Mark W. Scott

    发明人： Mark W. Scott

    IPC分类号： B64C27/473 ,  B64C27/72

    CPC分类号： B64C27/473 ,  B64C2027/7205 ,  Y02T50/34

    摘要： A rotor blade for a rotary wing aircraft includes a component bay located substantially enclosed in the rotor blade and one or more components positioned in the component bay. An airflow is located at the component bay and an airflow outlet is located at the component bay radially outboard of the airflow inlet. The airflow inlet and airflow outlet allow a continuous airflow through the component bay via centrifugal forces of rotation of the rotor blade, the continuous airflow cooling the one or more components disposed at the component bay.

    摘要翻译： 用于旋转飞行器飞行器的转子叶片包括基本上包围在转子叶片中的部件舱和位于部件舱中的一个或多个部件。 气流位于组件隔间，气流出口位于空气流入口径向外侧的组件隔间。 气流入口和气流出口允许通过转子叶片的旋转离心力使连续气流穿过部件间隔，连续气流冷却设置在部件间隔处的一个或多个部件。

    ROTOR BLADE COMPONENT COOLING
    2.
    发明申请
    ROTOR BLADE COMPONENT COOLING 有权
    转子叶片组件冷却

    公开(公告)号：US20130094959A1

    公开(公告)日：2013-04-18

    申请号：US13272781

    申请日：2011-10-13

    申请人： Mark W. Scott

    发明人： Mark W. Scott

    IPC分类号： B64C11/24 ,  B64C27/32

    CPC分类号： B64C27/473 ,  B64C2027/7205 ,  Y02T50/34

    摘要： A rotor blade for a rotary wing aircraft includes a component bay located substantially enclosed in the rotor blade and one or more components positioned in the component bay. An airflow is located at the component bay and an airflow outlet is located at the component bay radially outboard of the airflow inlet. The airflow inlet and airflow outlet allow a continuous airflow through the component bay via centrifugal forces of rotation of the rotor blade, the continuous airflow cooling the one or more components disposed at the component bay.

    摘要翻译： 用于旋转飞行器飞行器的转子叶片包括基本上包围在转子叶片中的部件舱和位于部件舱中的一个或多个部件。 气流位于组件隔间，气流出口位于空气流入口径向外侧的组件隔间。 气流入口和气流出口允许通过转子叶片的旋转离心力使连续气流穿过部件间隔，连续气流冷却设置在部件间隔处的一个或多个部件。

    System and method for improved rotary-wing aircraft performance with interior/external loads
    3.
    发明申请
    System and method for improved rotary-wing aircraft performance with interior/external loads 有权
    改进旋翼飞机性能与内部/外部载荷的系统和方法

    公开(公告)号：US20100222993A1

    公开(公告)日：2010-09-02

    申请号：US11455482

    申请日：2006-06-19

    申请人： Steven J. Brainard ,  David R. Houy ,  Anthony Z. Stobiecki ,  Mark W. Scott ,  Steven D. Weiner

    发明人： Steven J. Brainard ,  David R. Houy ,  Anthony Z. Stobiecki ,  Mark W. Scott ,  Steven D. Weiner

    IPC分类号： G06F19/00

    CPC分类号： B64D1/22 ,  G01D7/02 ,  G01M1/127 ,  G05D1/0858

    摘要： An interactive aircraft load management system automates calculation and provides simulation capability to changes in an aircraft C.G. limit for display on a three-dimensional aircraft symbology. The aircraft load management system also communicates with a fly by wire (FBW) flight control system wherein the aircraft's control system is programmed to automatically compensate for C.G. excursions and to alter control laws. The aircraft load management system also selectively reels-in and reels out sling lines as the aircraft pitches and rolls to maintain a load vector from a slung load along the aircraft centerline. Load vector travel is accomplished by coupling a winch control system into the flight control system.

    摘要翻译： 交互式飞机负载管理系统自动计算并提供对飞机C.G.的变化的模拟能力。 限制在三维飞机符号系统上显示。 飞机负载管理系统还与飞行（FBW）飞行控制系统进行通信，其中飞行器的控制系统被编程为自动补偿C.G. 游览和改变控制法。 航空器负载管理系统还可以选择性地卷起并卷起吊索，因为飞机的间距和滚动以沿着飞机中心线从静止载荷维持载荷矢量。 通过将绞盘控制系统连接到飞行控制系统来实现负载矢量行驶。

    Rotor hub fairing system for a counter-rotating, coaxial rotor system
    6.
    发明授权
    Rotor hub fairing system for a counter-rotating, coaxial rotor system 有权
    转子轮毂整流罩系统，用于反转，同轴转子系统

    公开(公告)号：US07229251B2

    公开(公告)日：2007-06-12

    申请号：US11141246

    申请日：2005-05-31

    申请人： Fabio P. Bertolotti ,  Mark W. Scott ,  Brian E. Wake ,  T. Alan Egolf ,  Duane C. McCormick

    发明人： Fabio P. Bertolotti ,  Mark W. Scott ,  Brian E. Wake ,  T. Alan Egolf ,  Duane C. McCormick

    IPC分类号： B64C27/50

    CPC分类号： B64C27/12 ,  B64C1/00 ,  B64C7/00 ,  B64C27/04 ,  B64C27/10 ,  B64C27/14 ,  B64C27/20

    摘要： A rotor hub fairing system includes an upper hub fairing, a lower hub fairing and a shaft fairing therebetween. The rotor hub fairing system is sized and configured to reduce the overall drag on a dual, counter-rotating, coaxial rotor system. Preferably, the rotor hub fairing is fully integrated. The shaft fairing preferably includes a minimal thickness at the midsection to reduce drag with an increasing thickness adjacent the upper and lower hub fairings to reduce the flow separation on the hub fairing surfaces without overly excessive drag. Other aerodynamic structures, such as a horizontal splitter and/or a plurality of turning vanes may be mounted to the shaft fairing to facilitate flow around the upper and lower hub fairings to reduce flow separation and drag.

    摘要翻译： 转子轮毂整流罩系统包括上部轮毂整流罩，下部轮毂整流罩和在其间的整流装置。 转子轮毂整流罩系统的尺寸和构造可以减少双重反向旋转同轴转子系统的整体阻力。 优选地，转子毂整流罩完全集成。 轴整流罩优选地包括在中部的最小厚度，以减小邻近上部和下部轮毂整流罩的增加的厚度的阻力，以减少轮毂整流面上的流动分离，而不会过度的过大阻力。 其他空气动力学结构，例如水平分流器和/或多个转向叶片可以安装到轴整流罩上，以便于围绕上部和下部轮毂整流罩流动以减少流动分离和阻力。

    Flight control system for a hybrid aircraft in the yaw axis
    7.
    发明授权
    Flight control system for a hybrid aircraft in the yaw axis 有权
    飞行控制系统用于混合飞机在偏航轴上

    公开(公告)号：US06478262B1

    公开(公告)日：2002-11-12

    申请号：US09907068

    申请日：2001-07-17

    申请人： W. Douglas Kinkead ,  Mark W. Scott

    发明人： W. Douglas Kinkead ,  Mark W. Scott

    IPC分类号： G05D100

    CPC分类号： B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/162 ,  B64C2201/165 ,  G05D1/0858

    摘要： A flight control system includes a blending algorithm which evaluates the current flight regime and determines the effectiveness of the flight controls to effect the rotational moment of a hybrid vehicle about the yaw axis. Gain schedules for both differential collective and rudder control provide a quantitative measure of control effectiveness. Based on the respective gain schedules, the algorithm determines how much of the control commands should be sent to each control surface. The result is that for a given control command, the same amount of yaw moment will be generated regardless of flight regime. This simplifies the underlying flight control law since the commands it generates are correct regardless of flight regime.

    摘要翻译： 飞行控制系统包括混合算法，其评估当前飞行状态并且确定飞行控制器实现混合动力车辆绕偏转轴线的旋转力矩的有效性。 差异集体和方向舵控制的增益时间表提供了控制有效性的定量测量。 基于相应的增益计划，该算法确定应将多少控制命令发送到每个控制表面。 结果是对于给定的控制命令，将产生与飞行状态无关的相同量的横摆力矩。 这简化了潜在的飞行控制规则，因为它产生的命令是正确的，无论飞行情况如何。