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    Airplane Position Assurance Monitor
    23.
    发明申请
    Airplane Position Assurance Monitor 有权
    飞机位置保证监视器

    公开(公告)号：US20140100720A1

    公开(公告)日：2014-04-10

    申请号：US14100245

    申请日：2013-12-09

    Applicant: THE BOEING COMPANY

    Inventor： Steven L. Fleiger-Holmes ,  Timothy Allen Murphy ,  Jean Marie Crane

    IPC: G08G5/02 ,  B64D45/04 ,  B64D43/00 ,  G01C5/00

    CPC classification number: G08G5/02 ,  B64D43/00 ,  B64D45/04 ,  G01C5/005 ,  G01S1/18 ,  G01S19/15 ,  G01S19/20 ,  G05D1/0676 ,  G08G5/0021 ,  G08G5/0026 ,  G08G5/025

    Abstract: An onboard monitor that ensures the accuracy of data representing the calculated position of an airplane during final approach to a runway. This airplane position assurance monitor is a software function that uses dissimilar sources of airplane position and runway data to ensure the accuracy of the respective data from those dissimilar sources. ILS data and GPS or GPS/Baro data are the dissimilar sources of airplane position data used by this function. This function will calculate the airplane's angular deviations from the runway centerline and from the glide slope with onboard equipment and then compare those angular deviations to the ILS angular deviation information.

    Abstract translation: 一个车载显示器，确保在最后接近跑道时表示飞机计算位置的数据的准确性。 该飞机位置保证监视器是使用不同的飞机位置和跑道数据源的软件功能，以确保来自这些不同来源的各自数据的准确性。 ILS数据和GPS或GPS / Baro数据是该功能使用的飞机位置数据的不同来源。 该功能将计算飞机从跑道中心线和与车载设备的滑行斜率的角度偏差，然后将这些角度偏差与ILS角度偏差信息进行比较。

    ILS-based altitude data generation system, device, and method
    24.
    发明授权
    ILS-based altitude data generation system, device, and method 有权
    基于ILS的高度数据生成系统，设备和方法

    公开(公告)号：US08498758B1

    公开(公告)日：2013-07-30

    申请号：US13685218

    申请日：2012-11-26

    Applicant: Rockwell Collins, Inc.

    Inventor： Douglas A Bell ,  James H. Doty ,  Sarah Barber ,  Felix B. Turcios

    IPC: G05D1/00

    CPC classification number: G01C5/005 ,  G01C23/005

    Abstract: Present novel and non-trivial system, device, and method for generating altitude data and/or height data are disclosed. A processor receives navigation data from an external source such as a global positioning system (“GPS”); receives navigation data from multiple internal sources; receives object data representative of terrain or surface feature elevation; determines an instant measurement of aircraft altitude as a function of these inputs; and generates aircraft altitude data responsive to such determination. In an additional embodiment, the processor receives reference point data representative of the elevation of the stationary reference point (e.g., a landing threshold point); determines an instant measurement of aircraft height as a function of this input and the instant measurement of aircraft altitude; and generates aircraft height data responsive to such determination.

    Abstract translation: 公开了用于产生高度数据和/或高度数据的新颖和非平凡的系统，装置和方法。 处理器从诸如全球定位系统（“GPS”）的外部源接收导航数据; 从多个内部来源接收导航数据; 接收表示地形或表面特征高程的物体数据; 确定飞机高度的即时测量作为这些输入的函数; 并响应于这种确定生成飞机高度数据。 在另外的实施例中，处理器接收表示静止参考点的升高的参考点数据（例如，着陆阈值点）; 确定飞机高度的即时测量作为该输入和飞机高度的即时测量的函数; 并响应于这种确定产生飞机高度数据。

    PRESSURE ALTITUDE STABILIZATION
    25.
    发明申请
    PRESSURE ALTITUDE STABILIZATION 审中-公开
    压力高度稳定

    公开(公告)号：US20130190951A1

    公开(公告)日：2013-07-25

    申请号：US13746003

    申请日：2013-01-21

    Applicant: Sandel Avionics, Inc.

    Inventor： Gerald J. Block ,  William J. Warkany

    IPC: G01C5/00

    CPC classification number: G01S19/41 ,  G01C5/005

    Abstract: A method and apparatus is provided for determining the altitude of an aircraft. In accordance with the method, Global Positioning Satellite (GPS) data is received from a plurality of GPS satellites and a GPS altitude value is determined from the GPS data. In addition, a pressure altitude value is determined. An altitude difference is determined between the GPS altitude value and the pressure altitude value. At least one of the GPS altitude value and the pressure altitude value is adjusted using the altitude difference.

    Abstract translation: 提供了一种用于确定飞机高度的方法和装置。 根据该方法，从多个GPS卫星接收全球定位卫星（GPS）数据，并根据GPS数据确定GPS高度值。 另外，确定压力高度值。 在GPS高度值和压力高度值之间确定高度差。 使用高度差来调整GPS高度值和压力高度值中的至少一个。

    Altitude data generation system, device, and method
    26.
    发明授权
    Altitude data generation system, device, and method 有权
    海拔数据生成系统，设备和方法

    公开(公告)号：US08321074B1

    公开(公告)日：2012-11-27

    申请号：US13566350

    申请日：2012-08-03

    Applicant: Douglas A. Bell ,  James H. Doty

    Inventor： Douglas A. Bell ,  James H. Doty

    IPC: G05D1/00

    CPC classification number: G01C5/005 ,  G01C23/00

    Abstract: Present novel and non-trivial system, device, and method for generating altitude data and/or height data are disclosed. A processor receives navigation data from an external source such as a global positioning system (“GPS”); receives navigation data from multiple internal sources; receives object data representative of terrain or surface feature elevation; determines an instant measurement of aircraft altitude as a function of these inputs; and generates aircraft altitude data responsive to such determination. In an additional embodiment, the processor receives reference point data representative of the elevation of the stationary reference point (e.g., a landing threshold point); determines an instant measurement of aircraft height as a function of this input and the instant measurement of aircraft altitude; and generates aircraft height data responsive to such determination.

    Abstract translation: 公开了用于产生高度数据和/或高度数据的新颖和非平凡的系统，装置和方法。 处理器从诸如全球定位系统（GPS）的外部源接收导航数据; 从多个内部来源接收导航数据; 接收表示地形或表面特征高程的物体数据; 确定飞机高度的即时测量作为这些输入的函数; 并响应于这种确定生成飞机高度数据。 在另外的实施例中，处理器接收表示静止参考点的升高的参考点数据（例如，着陆阈值点）; 确定飞机高度的即时测量作为该输入和飞机高度的即时测量的函数; 并响应于这种确定产生飞机高度数据。

    Airplane Position Assurance Monitor
    27.
    发明申请
    Airplane Position Assurance Monitor 有权
    飞机位置保证监视器

    公开(公告)号：US20120265376A1

    公开(公告)日：2012-10-18

    申请号：US13085310

    申请日：2011-04-12

    Applicant: Steven L. Fleiger-Holmes ,  Timothy Allen Murphy ,  Jean Marie Crane

    Inventor： Steven L. Fleiger-Holmes ,  Timothy Allen Murphy ,  Jean Marie Crane

    IPC: G05D1/00 ,  G05D1/04 ,  G05D1/10 ,  G06F19/00

    CPC classification number: G08G5/02 ,  B64D43/00 ,  B64D45/04 ,  G01C5/005 ,  G01S1/18 ,  G01S19/15 ,  G01S19/20 ,  G05D1/0676 ,  G08G5/0021 ,  G08G5/0026 ,  G08G5/025

    Abstract: An onboard monitor that ensures the accuracy of data representing the calculated position of an airplane during final approach to a runway. This airplane position assurance monitor is a software function that uses dissimilar sources of airplane position and runway data to ensure the accuracy of the respective data from those dissimilar sources. ILS data and GPS or GPS/Baro data are the dissimilar sources of airplane position data used by this function. This function will calculate the airplane's angular deviations from the runway centerline and from the glide slope with onboard equipment and then compares those angular deviations to the ILS angular deviation information.

    Abstract translation: 一个车载显示器，确保在最后接近跑道时表示飞机计算位置的数据的准确性。 该飞机位置保证监视器是使用不同的飞机位置和跑道数据源的软件功能，以确保来自这些不同来源的各自数据的准确性。 ILS数据和GPS或GPS / Baro数据是该功能使用的飞机位置数据的不同来源。 该功能将计算飞机与跑道中心线的角度偏差以及与车载设备的滑行斜率，然后将这些角度偏差与ILS角度偏差信息进行比较。

    Integrated barometric altitude and satellite altitude-based vertical navigation system
    28.
    发明授权
    Integrated barometric altitude and satellite altitude-based vertical navigation system 有权
    综合气压高度和卫星高度垂直导航系统

    公开(公告)号：US07962253B1

    公开(公告)日：2011-06-14

    申请号：US11657874

    申请日：2007-01-24

    Applicant: Gary L. Owen ,  James A. Young, Jr.

    Inventor： Gary L. Owen ,  James A. Young, Jr.

    IPC: G01C23/00

    CPC classification number: G01C5/005

    Abstract: A flight management system (FMS) for an aircraft, that includes an integrated barometric altitude and satellite altitude-based vertical navigation (VNAV) system. The integrated barometric altitude and satellite altitude-based vertical navigation system, includes an altitude blending component for providing a smooth transition from a barometric altimetry source to a satellite altimetry source; and, a satellite altitude containment component operatively connected to the altitude blending component for limiting the difference of a barometric altitude path deviation to within a desired margin of a satellite altitude path deviation.

    Abstract translation: 航空器的飞行管理系统（FMS），包括一体化气压高度和基于卫星高度的垂直导航（VNAV）系统。 综合气压高度和基于卫星高度的垂直导航系统包括一个高度混合组件，用于提供从气压高度测量源到卫星测高源的平稳过渡; 以及与海拔高度混合部件可操作地连接的卫星高度保持部件，用于将气压高度路径偏差的差异限制在卫星高度路径偏差的期望余量内。

    Doppler beam-sharpened radar altimeter
    29.
    发明授权
    Doppler beam-sharpened radar altimeter 有权
    多普勒波束锐化雷达高度计

    公开(公告)号：US07911375B2

    公开(公告)日：2011-03-22

    申请号：US12476682

    申请日：2009-06-02

    Applicant: Benjamin J. Winstead ,  Thomas W. Heidemann

    Inventor： Benjamin J. Winstead ,  Thomas W. Heidemann

    IPC: G01S13/08

    CPC classification number: G01C5/005 ,  G01S13/585 ,  G01S13/60 ,  G01S13/70 ,  G01S13/882

    Abstract: Systems and methods for Doppler beam sharpening in a radar altimeter are provided. In one embodiment, a method comprises receiving a return signal at a radar altimeter receiver and applying a first gate to the return signal to select at least a first component of the return signal. Spectral analysis is performed on the first component of the return signal to generate a plurality of frequency bins, wherein each frequency bin is centered around a different frequency across a Doppler shift frequency spectrum for the first component of the return signal. The method further comprises tracking the first component of the return signal, selecting a first frequency bin of the plurality of frequency bins based on the Doppler shift frequency of the first component of the return signal, and outputting a portion of the first component of the return signal falling within the first frequency bin for further processing.

    Abstract translation: 提供雷达高度计中多普勒波束锐化的系统和方法。 在一个实施例中，一种方法包括在雷达高度计接收器处接收返回信号，并向返回信号施加第一门以选择返回信号的至少第一分量。 对返回信号的第一分量执行频谱分析以产生多个频率仓，其中每个频率仓以用于返回信号的第一分量的多普勒频移频谱为中心。 该方法还包括跟踪返回信号的第一分量，基于返回信号的第一分量的多普勒频移选择多个频率仓的第一频率仓，并输出返回信号的第一分量的一部分 信号落在第一频率仓内，用于进一步处理。

    Optical system for detecting and displaying aircraft position and environment during landing and takeoff
    30.
    发明授权
    Optical system for detecting and displaying aircraft position and environment during landing and takeoff 有权
    用于在着陆和起飞期间检测和显示飞机位置和环境的光学系统

    公开(公告)号：US07898435B2

    公开(公告)日：2011-03-01

    申请号：US12085310

    申请日：2008-02-25

    Applicant: Philip L. Rogers ,  Priyavadan Mamidipudi ,  Peter A. Gatchell

    Inventor： Philip L. Rogers ,  Priyavadan Mamidipudi ,  Peter A. Gatchell

    IPC: G01C21/00

    CPC classification number: G01C5/005 ,  G01C23/00 ,  G01S13/913 ,  G01S17/58 ,  G01S17/88 ,  G01S17/95 ,  Y02A90/19

    Abstract: A system and method uses light signals to detect and display the position of an airborne vehicle, such as a helicopter, during takeoff or landing or low speed, low altitude operation. A transmitter on the vehicle emits light signals while an optical receiver retrieves reflected light signals. Using light detection and ranging techniques, various parameters, such as altitude, ground speed and relative wind, are calculated based on the Doppler shift within the reflected light signals. The signals are transmitted in three different directions to facilitate the measurements of different Doppler shifts. The parameters are also displayed on a screen or other visual device within the vehicle.

    Abstract translation: 系统和方法使用光信号来检测和显​​示起飞或着陆或低速，低空作业期间诸如直升机的空中载客的位置。 当光接收器检索反射光信号时，车辆上的发射器发射光信号。 使用光检测和测距技术，基于反射光信号内的多普勒频移计算各种参数，如高度，地面速度和相对风。 信号在三个不同的方向传输，以便于测量不同的多普勒频移。 这些参数也显示在车辆内的屏幕或其他视觉设备上。

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