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21. 发明授权

US4853861A Windshear measurement system 失效
标题翻译：风切变测量系统
公开(公告)号：US4853861A
公开(公告)日：1989-08-01
申请号：US92088
申请日：1987-09-01
申请人： Douglas W. Ford , Walter A. Johnson , Shahram Daneshmandi
发明人： Douglas W. Ford , Walter A. Johnson , Shahram Daneshmandi
IPC分类号： G01P5/00 , G01P15/00
CPC分类号： G01P15/00 , G01P5/00
摘要： The present invention comprises a system for detecting windshear and associated downdraft effects when they are encountered in flight by an aircraft. The system includes an input unit (12), a first processing unit (14), a second processing unit (16), an output unit (18), and a pilot warning device (20). The input unit receives aircraft performance data from the instruments and/or flight systems on the aircraft and preconditions this data to produce a set of signals corresponding to various aerodynamic and inertial input parameters. The first processing unit differences signals representing the aerodynamically derived and inertially derived accelerations of the aircraft in order to generate windshear signals. These windshear signals are then corrected for pitch rate induced coriolis acceleration effects. The corrected signals are used to form a signals representing longitudinal windshear along the horizontal heading axis of the aircraft and the change in aircraft climb gradient due to longitudinal windshear. The second processing unit difference aerodynamically derived and inertially derived flight path signals to generate a windshear type change in climb gradient signal corresponding to the effects of downdrafts. The output unit sums the change in climb gradient signals to produce an overall aircraft loss of performance signal which it then conditions for threshold detection purposes. This final conditioned signal is furnished to the pilot warning device which provides a visible or audible warning in order to advise the aircraft pilot of potentially hazardous flight conditions. In an alternate embodiment, coriolis acceleration effects are eliminated by forming a signal representing aerodynamically derived acceleration in the horizontal plane. The longitudinal windshear signal is then generated by forming an inertial acceleration signal in the horizontal plane and differencing the respective aerodynamic and inertial acceleration signals.
摘要翻译：本发明包括一种用于在飞机遇到飞行时检测风切变和相关的下降作用的系统。该系统包括输入单元（12），第一处理单元（14），第二处理单元（16），输出单元（18）和先导报警装置（20）。输入单元从飞机上的仪器和/或飞行系统接收飞机性能数据，并对该数据进行预处理，以产生对应于各种空气动力学和惯性输入参数的一组信号。第一处理单元将表示飞行器的空气动力学和惯性导出的加速度的信号区分开来，以产生风切变信号。然后将这些风切变信号校正为俯仰速率引起的科里奥利加速度效应。校正的信号用于形成沿着飞行器的水平航向轴线的纵向风切变信号和由于纵向风切变引起的飞机爬升梯度的变化的信号。第二个处理单元的空气动力学差异和惯性导出的飞行路径信号，以产生对应于下降影响的爬升梯度信号的风切变类型变化。输出单元将爬升梯度信号的变化相加，以产生总体飞机性能信号的损失，然后进行阈值检测。该最后的条件信号被提供给飞行员警告装置，其提供可见或可听见的警告，以向飞机飞行员通知潜在的危险飞行状况。在替代实施例中，通过在水平面中形成表示空气动力学推导的加速度的信号来消除科里奥利加速度效应。然后通过在水平面中形成惯性加速度信号并差分相应的空气动力学和惯性加速度信号来产生纵向风切变信号。

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