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    Systems and methods for controlling aircraft electrical power
    1.
    发明授权
    Systems and methods for controlling aircraft electrical power 有权
    用于控制飞机电力的系统和方法

    公开(公告)号：US08155876B2

    公开(公告)日：2012-04-10

    申请号：US11518379

    申请日：2006-09-07

    申请人： Jeffrey J. White ,  David K. Toy ,  J. Everett Groat

    发明人： Jeffrey J. White ,  David K. Toy ,  J. Everett Groat

    IPC分类号： B64C13/38

    CPC分类号： B64D41/00 ,  B64D2221/00 ,  H02J4/00

    摘要： Systems and methods for controlling aircraft electrical power are disclosed. A system in accordance with one embodiment includes an electric motor, an aircraft load coupled to the electric motor and powered by the electric motor, and a motor controller coupled to the electric motor to vary an output of the electric motor. The motor controller is changeable among a fixed number of preset controller modes, with individual controller modes corresponding to an operation mode of the aircraft and a non-zero output level of the electric motor. In further embodiments, motor controllers can be substituted for each other, e.g., in the event one motor controller becomes unoperational.

    摘要翻译： 公开了用于控制飞机电力的系统和方法。 根据一个实施例的系统包括电动机，耦合到电动机并由电动机供电的飞行器负载以及耦合到电动机以改变电动机的输出的电动机控制器。 电机控制器可以在固定数量的预设控制器模式之间变化，其中各个控制器模式对应于飞行器的操作模式和电动机的非零输出电平。 在另外的实施例中，电动机控制器可以彼此替代，例如在一个电动机控制器变得不可操作的情况下。

    Systems and methods for controlling aircraft electrical power
    2.
    发明申请
    Systems and methods for controlling aircraft electrical power 有权
    用于控制飞机电力的系统和方法

    公开(公告)号：US20090118874A1

    公开(公告)日：2009-05-07

    申请号：US11518379

    申请日：2006-09-07

    申请人： Jeffrey J. White ,  David K. Toy ,  J. Everett Groat

    发明人： Jeffrey J. White ,  David K. Toy ,  J. Everett Groat

    IPC分类号： G06F17/00 ,  B64C3/38 ,  B64D31/00 ,  B64D41/00

    CPC分类号： B64D41/00 ,  B64D2221/00 ,  H02J4/00

    摘要： Systems and methods for controlling aircraft electrical power are disclosed. A system in accordance with one embodiment includes an electric motor, an aircraft load coupled to the electric motor and powered by the electric motor, and a motor controller coupled to the electric motor to vary an output of the electric motor. The motor controller is changeable among a fixed number of preset controller modes, with individual controller modes corresponding to an operation mode of the aircraft and a non-zero output level of the electric motor. In further embodiments, motor controllers can be substituted for each other, e.g., in the event one motor controller becomes unoperational.

    摘要翻译： 公开了用于控制飞机电力的系统和方法。 根据一个实施例的系统包括电动机，耦合到电动机并由电动机供电的飞行器负载以及耦合到电动机以改变电动机的输出的电动机控制器。 电机控制器可以在固定数量的预设控制器模式之间变化，其中各个控制器模式对应于飞行器的操作模式和电动机的非零输出电平。 在另外的实施例中，电动机控制器可以彼此替代，例如在一个电动机控制器变得不可操作的情况下。

    SYSTEMS AND METHODS FOR CONTROLLING AIRCRAFT ELECTRICAL POWER
    3.
    发明申请
    SYSTEMS AND METHODS FOR CONTROLLING AIRCRAFT ELECTRICAL POWER 有权
    用于控制飞机电力的系统和方法

    公开(公告)号：US20120161676A1

    公开(公告)日：2012-06-28

    申请号：US13408629

    申请日：2012-02-29

    申请人： Jeffrey J. White ,  David K. Toy ,  J. Everett Groat

    发明人： Jeffrey J. White ,  David K. Toy ,  J. Everett Groat

    IPC分类号： H02P7/00 ,  H02P5/00

    CPC分类号： B64D41/00 ,  B64D2221/00 ,  H02J4/00

    摘要： Systems and methods for controlling aircraft electrical power are disclosed. A system in accordance with one embodiment includes an electric motor, an aircraft load coupled to the electric motor and powered by the electric motor, and a motor controller coupled to the electric motor to vary an output of the electric motor. The motor controller is changeable among a fixed number of preset controller modes, with individual controller modes corresponding to an operation mode of the aircraft and a non-zero output level of the electric motor. In further embodiments, motor controllers can be substituted for each other, e.g., in the event one motor controller becomes unoperational.

    摘要翻译： 公开了用于控制飞机电力的系统和方法。 根据一个实施例的系统包括电动机，耦合到电动机并由电动机供电的飞行器负载以及耦合到电动机以改变电动机的输出的电动机控制器。 电机控制器可以在固定数量的预设控制器模式之间变化，其中各个控制器模式对应于飞行器的操作模式和电动机的非零输出电平。 在另外的实施例中，电动机控制器可以彼此替代，例如在一个电动机控制器变得不可操作的情况下。

    Systems and methods for controlling aircraft electrical power
    5.
    发明授权
    Systems and methods for controlling aircraft electrical power 有权

    公开(公告)号：US08527180B2

    公开(公告)日：2013-09-03

    申请号：US13408629

    申请日：2012-02-29

    申请人： Jeffrey J. White ,  David K. Toy ,  J. Everett Groat

    发明人： Jeffrey J. White ,  David K. Toy ,  J. Everett Groat

    IPC分类号： B64C13/38

    CPC分类号： B64D41/00 ,  B64D2221/00 ,  H02J4/00

    摘要： Systems and methods for controlling aircraft electrical power are disclosed. A system in accordance with one embodiment includes an electric motor, an aircraft load coupled to the electric motor and powered by the electric motor, and a motor controller coupled to the electric motor to vary an output of the electric motor. The motor controller is changeable among a fixed number of preset controller modes, with individual controller modes corresponding to an operation mode of the aircraft and a non-zero output level of the electric motor. In further embodiments, motor controllers can be substituted for each other, e.g., in the event one motor controller becomes unoperational.

    Alternate ventilation system
    7.
    发明授权
    Alternate ventilation system 失效
    备用通风系统

    公开(公告)号：US6159091A

    公开(公告)日：2000-12-12

    申请号：US437773

    申请日：1999-11-01

    申请人： Raymond H. Horstman ,  Dennis D. Chung ,  Thomas R. Hasenoehrl ,  Quy Lam ,  Luc Tu Kha ,  J. Everett Groat

    发明人： Raymond H. Horstman ,  Dennis D. Chung ,  Thomas R. Hasenoehrl ,  Quy Lam ,  Luc Tu Kha ,  J. Everett Groat

    IPC分类号： B64D13/00

    CPC分类号： B64D13/00

    摘要： An alternate ventilation system for an aircraft having a body structure and a plurality of electronic devices is provided. The ventilation system includes a ventilation conduit, an inboard supply valve, a first outflow valve and a second outflow valve. The ventilation conduit is adapted to be coupled to the body structure for directing a ventilation flow of air along a predetermined flow path. The inboard supply valve is coupled to the ventilation conduit and adapted for drawing air from the cabin into the ventilation conduit when positioned in the open condition. The first outflow valve is coupled to the ventilation conduit and adapted for discharging at least a portion of the ventilation flow from the ventilation conduit to a point outside the body structure when positioned in the open condition. The second outflow valve is coupled to the body structure and operable in a first mode and a second mode. The first mode is adapted to selectively enable a discharge airflow from the cabin and the second mode is adapted to selectively enable an input airflow into the cabin. A method for ventilating an aircraft is also provided herein.

    摘要翻译： 提供一种用于具有车体结构和多个电子设备的飞行器的替代通风系统。 通风系统包括通气导管，内侧供气阀，第一流出阀和第二流出阀。 通风管道适于联接到主体结构，用于沿着预定的流动路径引导空气的通风流。 内侧供应阀联接到通风管道，适于当处于打开状态时将空气从舱室吸入通风管道。 第一流出阀联接到通气管道，并且适于在定位在打开状态时将来自通气导管的通气流的至少一部分排放到身体结构外部的点。 第二流出阀联接到主体结构并且可在第一模式和第二模式中操作。 第一模式适于选择性地启用来自舱室的排出气流，并且第二模式适于选择性地使得进入舱室的输入气流。 本文还提供了一种用于通风飞机的方法。