公开(公告)号：US06640165B1

公开(公告)日：2003-10-28

申请号：US10304720

申请日：2002-11-26

申请人： Kirk W. Hayward ,  Larry G. Stephenson

发明人： Kirk W. Hayward ,  Larry G. Stephenson

IPC分类号： G02B2310

CPC分类号： G01C5/005

摘要： A method of determining an altitude of a flying object. A Blanchard altitude of a flying object is computed. A non-Blanchard reference altitude and a trajectory of the flying object are measured and input to a Kalman filter. In the Kalman filter, the non-Blanchard reference altitude and the trajectory are processed to derive a radius of jet stream curvature. A gradient wind correction factor is then computed as a function of the radius of jet stream curvature. The Blanchard altitude is then corrected in response to the gradient wind correction factor.

摘要翻译： 确定飞行物体高度的方法。 计算飞行物体的Blanchard高度。 测量非布兰查德参考高度和飞行物体的轨迹，并将其输入卡尔曼滤波器。 在卡尔曼滤波器中，非布兰查德参考高度和轨迹被处理以得出射流曲率的半径。 然后计算梯度风修正因子作为射流曲率半径的函数。 然后响应于梯度风修正系数校正布兰查德高度。

公开(公告)号：US06813586B1

公开(公告)日：2004-11-02

申请号：US09657111

申请日：2000-09-07

申请人： Curtis A. Vock ,  Perry Youngs ,  Adrian Larkin ,  Timothy Ryan

发明人： Curtis A. Vock ,  Perry Youngs ,  Adrian Larkin ,  Timothy Ryan

IPC分类号： G02B2310

CPC分类号： A63B71/0605 ,  A63B5/00 ,  A63B69/18

摘要： A digital camera system is provided to measure a moving sportsman, for example to determine peak altitude, spin ratio and airtime. A wireless triangulation system is provided to track a moving sportsman to determine metrics such as peak altitude, rotation, drop distance and airtime. A stride-rate system is provided to determine stride-rate or assist in training for sports such as roller-blading.

摘要翻译： 提供数字照相机系统来测量移动的运动员，例如以确定峰值高度，旋转比和通话时间。 提供无线三角测量系统来跟踪移动的运动员以确定诸如峰值高度，旋转，下降距离和通话时间的度量。 提供了一个步幅系统，用于确定步幅或协助训练如滚轮溜冰运动。

公开(公告)号：US06173220B2

公开(公告)日：2001-01-09

申请号：US09416577

申请日：1999-10-12

申请人： John M. Schmitt

发明人： John M. Schmitt

IPC分类号： G02B2310

CPC分类号： G01C23/00 ,  G02B23/10

摘要： An attitude direction indicator (ADI) display includes a horizon line that divides an upper colored portion, which represents the sky, from a lower colored portion, which represents the Earth. The ADI display includes indicia incorporated into the upper and/or lower portions for enhancing the operator's situational awareness of the vehicle. The indicia may be configured as a texturing of the colored portions and/or as a gradient color scheme associated with the colored portions. The texturing scheme or gradient color scheme may be utilized to convey viewable information related to the vehicle's altitude or position relative to a reference such as a runway. Furthermore, the texturing scheme or the gradient color scheme may be utilized to render a directional marker that indicates a direction toward the horizon line.

摘要翻译： 姿态方向指示器（ADI）显示器包括从代表地球的较低色彩部分划分代表天空的上色部分的水平线。 ADI显示器包括并入上部和/或下部的标记，用于增强操作者对车辆的状态意识。 标记可以被配置为着色部分的纹理化和/或与着色部分相关联的梯度色彩方案。 纹理方案或梯度颜色方案可以用于传送与车辆的高度或位置相关的可见信息相对于诸如跑道的参考。 此外，纹理化方案或梯度配色方案可以用于渲染指示朝向水平线的方向的方向标记。

公开(公告)号：US06583862B1

公开(公告)日：2003-06-24

申请号：US10018051

申请日：2001-12-10

申请人： Andreas Perger

发明人： Andreas Perger

IPC分类号： G02B2310

CPC分类号： G01S7/4812 ,  F41G3/065 ,  G01S17/023 ,  G01S17/08 ,  G02B23/14

摘要： The invention relates to a combined telescope and telemeter device comprising a telescopic sight (1) having a housing (2), one end of which receives an objective lens (3) while the other end receives an eyepiece (4), said housing defining a beam path (5) between the objective lens and the eyepiece. The device also includes an opto-electronic telemeter (12) with emitter-receiver optics (14) for optical measuring beams (15) and evaluation electronics (24) for timing the interval between an emitted measuring beam and a received measuring beam and for determining the distance on the basis thereof. The device further comprises a beam splitter (17) in the beam path (5) of the housing (2), which couples and decouples the measuring beams (15) in the part of the beam path (5) extending in the direction of the objective lens (3), wherein the housing (2) has a hole (16) in a side wall and a telemeter (12) is contained in a separate measuring housing (13) but can be mounted in said side wall, wherein the emitter-receiver optics (14) is directed at the above-mentioned hole (16).

摘要翻译： 本发明涉及一种组合望远镜和遥测仪装置，其包括具有壳体（2）的伸缩瞄准器（1），其一端接收物镜（3），而另一端容纳目镜（4），所述壳体限定 物镜和目镜之间的光束路径（5）。 该装置还包括一个光电遥测仪（12），其具有用于光学测量光束（15）的发射器 - 接收器光学器件（14）和用于定时发射的测量光束和接收的测量光束之间的间隔的评估电子器件（24） 基于其距离。 该装置还包括在壳体（2）的光束路径（5）中的分束器（17），其将梁（5）的沿着该方向的方向延伸的部分中的测量光束（15） 物镜（3），其中所述壳体（2）在侧壁中具有孔（16），并且遥测仪（12）容纳在单独的测量壳体（13）中，但可安装在所述侧壁中，其中所述发射器 - 接收器光学器件（14）指向上述孔（16）。

公开(公告)号：US06266583B1

公开(公告)日：2001-07-24

申请号：US09539268

申请日：2000-03-30

申请人： Daniel A. Tazartes ,  Brian T. Lottman ,  Dean E. Lottman ,  John G. Mark

发明人： Daniel A. Tazartes ,  Brian T. Lottman ,  Dean E. Lottman ,  John G. Mark

IPC分类号： G02B2310

CPC分类号： G01C5/005 ,  G01C21/165

摘要： A system and method for improving the accuracy of altitude determinations in an inertial navigation system. Pressure measurements available to the inertial navigation system are used to initially calculate an estimated pressure altitude using the standard day model for the atmosphere. Temperature measurements are further utilized in the physical relationship between temperature, pressure, and altitude to compute a second computed altitude. A change between subsequent second computed altitudes is calculated and compared with a respective change in the computed pressure altitude in order to generate a correction value. The correction value is then used to modify the computed pressure altitude to generate a more accurate determination of the absolute altitude of the inertial navigation system. The correction value is utilized to account for changes in atmospheric conditions which may be encountered by an aircraft and to further reduce the effects of erroneous temperature and pressure measurements in subsequent altitude determinations. Thus, the system and method of the present invention provides an absolute altitude determination having improved stability and improved accuracy over prior systems.

摘要翻译： 一种用于提高惯性导航系统中高度确定精度的系统和方法。 用于惯性导航系统的压力测量用于使用大气的标准日模型来初始计算估计的压力高度。 温度测量进一步用于温度，压力和高度之间的物理关系，以计算第二个计算的高度。 计算随后的第二计算高度之间的变化，并与计算出的压力高度的相应变化进行比较，以便产生校正值。 然后使用校正值来修改计算的压力高度，以产生对惯性导航系统的绝对高度的更准确的确定。 校正值被用于考虑飞机可能遇到的大气条件的变化，并进一步减少随后的高度测定中错误的温度和压力测量的影响。 因此，本发明的系统和方法提供了相对于现有系统具有改进的稳定性和改进的精度的绝对高度确定。