| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | METHOD OF ALERT CALCULATION FOR AN AIRCRAFT GROUND PROXIMITY WARNING SYSTEM | US12900747 | 2010-10-08 | US20110251741A1 | 2011-10-13 | Stéphane FLEURY; Laurent FLOTTE; Nicolas MARTY; Erick RAKOTOARISOA |
| The invention relates to a method of alert calculation for an aircraft obstruction proximity warning system including a step for detecting a hazardous flight situation capable of triggering an alert as a function of a data signal representing the change in height below the aircraft, including, prior to the step of detection, a step for converting the data signal representing the change in height as a function of information representative of the vertical profile of the obstructions below the aircraft. | ||||||
| 62 | Positioning and ground proximity warning method and system thereof for vehicle | US241164 | 1999-02-01 | US6157891A | 2000-12-05 | Ching-Fang Lin |
| A positioning and ground proximity warning method for vehicle includes the steps of outputting global positioning system signals to an integrated positioning/ground proximity warning system processor; outputting an inertial navigation solution to an integrated positioning/ground proximity warning processor; measuring air pressure, and computing barometric measurements which is output to the integrated positioning/ground proximity warning processor; measuring time delay between transmission and reception a radio signal from a terrain surface, and computing radio altitude measurement which is output to the integrated positioning/ground proximity warning processor; accessing a terrain database for obtaining current vehicle position and surrounding terrain height data which is output to the integrated positioning/ground proximity warning processor; and receiving the position, velocity and time information or said pseudorange and delta range measurements of said global positioning system, the inertial navigation solution, the radio altitude measurement, the radio altitude measurement, and the current vehicle position and surrounding terrain height data, and computing optimal positioning solution data and optimal ground proximity warning solution data. | ||||||
| 63 | Ground proximity warning system utilizing radio and barometric altimeter combination | US3715718D | 1970-08-11 | US3715718A | 1973-02-06 | ASTENGO R |
| A ground proximity warning system for an aircraft which produces a warning signal when the rate of descent of the aircraft exceeds a limiting value determined by the aircraft altitude. The rate of descent of the aircraft is calculated from a combination of measurements of the altitude of the aircraft above ground and the barometric altitude of the aircraft. A signal representing the rate of change of the altitude of the aircraft above ground is limited, to minimize false warnings as a result of surface irregularities. The barometric portion of the system is disabled during take-off run and the initial portion of the aircraft climb-out to avoid a false warning resulting from an increased barometric pressure condition during this maneuver. The limits on the aircraft altitude rate signal are modified in accordance with the flight mode of the aircraft, to reduce the sensitivity of the warning system during the final stage of a landing approach. The warning system provides an alarm to the pilot which is an audio tone modulated at a low frequency repetition rate. A soft warning is actuated when the sink rate of the aircraft exceeds a desired level for the altitude at which the aircraft is operating. If the aircraft is also below a limiting altitude, a hard warn signal is provided. The repetition rate of the warning signal, while in a soft warn condition, is a function of the difference between the altitude of the aircraft and the altitude at which the sink rate would be proper. A complementary filter with which the altitude rate signals are combined, includes an operational amplifier connected in an unloading amplifier configuration with a resistive circuit connecting one input signal with the amplifier and a capacitive circuit connecting the other input signal with the amplifier, the resistive and capacitive input circuits forming a low pass filter for the first signal and a high pass filter for the second signal.
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| 64 | Ground proximity warning system having modified terrain closure rate warning on glide slope approach | US512208 | 1983-07-08 | US4684948A | 1987-08-04 | Charles D. Bateman |
| An aircraft ground proximity warning system having an excessive terrain closure warning mode and a below glide slope warning mode monitors the glide slope signal and modifies the terrain closure warning envelope to accept a lesser terrain clearance when the aircraft is within the glide slope beam. | ||||||
| 65 | System for real-time logging of aircraft sensor data received from an Enhanced Ground Proximity Warning System | EP11176489.0 | 2011-08-03 | EP2418625A1 | 2012-02-15 | Conner, Kevin J.; Ostrom, Gary A.; Bateman, C. Don |
Systems and methods for performing efficient, inexpensive data logging of aircraft sensor data. An example system (20) on board an aircraft (18) includes a plurality of data sources (34) that provide sensor data associated with a plurality of avionic components, a line replaceable processing unit (24) that is in signal communication with the plurality of data sources via one or more databuses (32), a wireless router (26) connected to the line replaceable processing unit via a data cable and a portable data unit (28) in wireless data communication with the wireless router. The wireless router receives at least a portion of the sensor data from the line replaceable processing unit and sends the received sensor data to the portable data unit.
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| 66 | ROTARY WING AIRCRAFT PROXIMITY WARNING SYSTEM WITH A GEOGRAPHICALLY BASED AVOIDANCE SYSTEM | US11608267 | 2006-12-08 | US20080140267A1 | 2008-06-12 | David G. Matuska; Donald S. Anttila |
| A safety enhancement warning system includes an avoidance system which communicates with a multiple of geographical positional systems. A geographic algorithm of the avoidance system utilizes a recursive algorithmic to determine if the aircraft will enter a sensitive area. If the aircraft distance to a sensitive area decreases below a predefined minimum threshold, then an audible and/or visual warning is issued. For certain sensitive areas, aircraft RF emissions are silenced or reduced in power when the predetermined minimum threshold breaches the sensitive area. The use of the avoidance system enables usage of relatively inexpensive UWB radar for the proximity sensor suite to assure avoidance of interference with particular delicate instruments and thereby meet regulations such as those propagated by the FCC. | ||||||
| 67 | System and method for ground proximity warning with enhanced obstacle depiction | US10907934 | 2005-04-21 | US07330147B2 | 2008-02-12 | Ratan Khatwa |
| Systems and methods for displaying ground obstructions on a visual display are disclosed. In an embodiment, a ground proximity warning system includes at least one aircraft sensor system operable to acquire aircraft data and a ground proximity warning computer coupled to the aircraft sensor system to process the aircraft data that generates ground proximity warning data corresponding to a sensed ground obstruction. An indicating system including a visual display device then presents an image of a visual symbol corresponding to the sensed ground obstruction. At least one of the computer and the visual display device is controllable to selectively display the visual symbol. | ||||||
| 68 | Pitch alerting angle for enhanced ground proximity warning system (EGPWS) | US10114883 | 2002-04-01 | US06940427B2 | 2005-09-06 | Peter J. Bateman |
| A ground proximity warning system including a pitch angle alerting device, the pitch angle alerting device including warning logic having an input that is structured to receive a signal that is representative of the indicated pitch angle of the aircraft, the warning logic being structured to determine a difference between a pitch angle signal received on the input and a predetermined threshold, the warning logic being structured also to output a signal representative of the difference between the two signals; and an advisory indication generator coupled to accept the output of the warning logic, the advisory indication generator being structured to generate an advisory indication signal as a function of the difference between the two signals. | ||||||
| 69 | Detecting a low performance takeoff condition for aircraft for use with ground proximity warning systems | US09912093 | 2001-07-23 | US06437707B1 | 2002-08-20 | Steven C. Johnson |
| The present invention includes a system, method and computer program product for reducing nuisance warnings during low performance takeoff conditions. The system includes a first component that determines aircraft current climb rate and potential climb rate based on aircraft vertical speed data and velocity information and a second component that adds the determined current climb rate and potential climb rate. The system also includes a third component that disables alerts, if the sum of the current climb rate and potential climb rate differ from a predetermined climb rate by a threshold amount and if the aircraft is supposed to be in a maximum thrust condition (e.g. takeoff, missed approach). | ||||||
| 70 | SYSTEM AND METHOD FOR GROUND PROXIMITY WARNING WITH ENHANCED OBSTACLE DEPICTION | US10907934 | 2005-04-21 | US20060238402A1 | 2006-10-26 | Ratan Khatwa |
| Systems and methods for displaying ground obstructions on a visual display are disclosed. In an embodiment, a ground proximity warning system includes at least one aircraft sensor system operable to acquire aircraft data and a ground proximity warning computer coupled to the aircraft sensor system to process the aircraft data that generates ground proximity warning data corresponding to a sensed ground obstruction. An indicating system including a visual display device then presents an image of a visual symbol corresponding to the sensed ground obstruction. At least one of the computer and the visual display device is controllable to selectively display the visual symbol. | ||||||
| 71 | Ground proximity warning system with means for altering warning threshold in accordance with wind shear | US901537 | 1978-05-01 | US4189777A | 1980-02-19 | Daryal Kuntman |
| An aircraft air speed signal is differentiated to provide a signal related to rate of change of air speed. This signal is added to a signal related to aircraft barometric altitude change with the sum signal being compared against aircraft radio altitude to generate warning if the aircraft rate of descent is excessive for the conditions encountered. | ||||||
| 72 | Pitch alerting angle for enhanced ground proximity warning system (EGPWS) | US10114883 | 2002-04-01 | US20030016145A1 | 2003-01-23 | Peter J. Bateman |
| A ground proximity warning system including a pitch angle alerting device, the pitch angle alerting device including warning logic having an input that is structured to receive a signal that is representative of the indicated pitch angle of the aircraft, the warning logic being structured to determine a difference between a pitch angle signal received on the input and a predetermined threshold, the warning logic being structured also to output a signal representative of the difference between the two signals; and an advisory indication generator coupled to accept the output of the warning logic, the advisory indication generator being structured to generate an advisory indication signal as a function of the difference between the two signals. | ||||||
| 73 | Ground proximity warning system, method and computer program product for controllably altering the base width of an alert envelope | US10231886 | 2002-08-30 | US06826459B2 | 2004-11-30 | Kevin J. Conner; Steven C. Johnson |
| A ground proximity warning system, method and computer program product are provided that controllably alter the base width of the alert envelope in order to accommodate uncertainties associated with the current position of the aircraft. In one embodiment, the ground proximity warning system, method and computer program product controllably alter the base width of the alert envelope depending upon an error value, i.e., an uncertainty, associated with the current position of the aircraft. Since the error value associated with the current position of the aircraft is largely dependent upon the type of navigation equipment onboard the aircraft, the ground proximity warning system, method and computer program product of another embodiment controllably alter the base width of the alert envelope depending upon the type of navigation equipment that provides the current position of the aircraft. | ||||||
| 74 | Ground proximity warning system, method and computer program product for controllably altering the base width of an alert envelope | US09496297 | 2000-02-01 | US06484071B1 | 2002-11-19 | Kevin J Conner; Steven C. Johnson |
| A ground proximity warning system, method and computer program product are provided that controllably alter the base width of the alert envelope in order to accommodate uncertainties associated with the current position of the aircraft. In one embodiment, the ground proximity warning system, method and computer program product controllably alter the base width of the alert envelope depending upon an error value, i.e., an uncertainty, associated with the current position of the aircraft. Since the error value associated with the current position of the aircraft is largely dependent upon the type of navigation equipment onboard the aircraft, the ground proximity warning system, method and computer program product of another embodiment controllably alter the base width of the alert envelope depending upon the type of navigation equipment that provides the current position of the aircraft. | ||||||
| 75 | 用于车辆的危险警告系统 | CN201180056798.6 | 2011-10-30 | CN103338974A | 2013-10-02 | 菲力浦·本苏桑; 尚塔尔·伯尼森 |
| 一种系统，经调整以将附近危险的警告提供给车辆操作者，例如附近的车辆已经发生碰撞或者不可操作。实施方式包括可操作以检测危险的检测器，发送警告信号的发送器，接收所发送的警告信号的接收器，以及向接近的车辆的操作者警告危险的显示器。某些实施方式结合车辆安全气囊展开电路的反馈以提供有效地播送警告信号的触发器。可向接近的车辆的操作者提供视觉和/或声音警告信号，例如通过移动电话。特定的实施方式通过发送的警告信号以及在接近的车辆中所承载的显示器和/或扬声器来将这样的警告提供给接近的车辆。声音和视觉警告可以从撞车车辆直接发送。 | ||||||
| 76 | 车辆接近警告系统、便携式警告终端及车载通信装置 | CN201010576538.9 | 2010-12-02 | CN102085841A | 2011-06-08 | 大岛弘充; 中村敏 |
| 公开了一种车辆接近警告系统。所述车辆接近警告系统包括要被安装在车辆(3)上的车载通信装置(5)以及要由行人(2)携带的便携式警告终端(4)，所述车载通信装置(5)被配置为将车辆行驶数据无线地发送到所述车辆(3)的周围；以及所述便携式警告终端(4)被配置为响应于接收到从所述车载通信装置(5)无线发送的车辆行驶数据，如果在接收到所述车辆行驶数据时的电场强度大于第一阈值(P)，则以听觉刺激之外的方式向所述行人(2)发出关于所述车辆(3)接近的警告。 | ||||||
| 77 | 车辆接近警告系统、便携式警告终端及车载通信装置 | CN201010576538.9 | 2010-12-02 | CN102085841B | 2013-10-02 | 大岛弘充; 中村敏 |
| 本发明公开了一种车辆接近警告系统。所述车辆接近警告系统包括要被安装在车辆(3)上的车载通信装置(5)以及要由行人(2)携带的便携式警告终端(4)，所述车载通信装置(5)被配置为将车辆行驶数据无线地发送到所述车辆(3)的周围；以及所述便携式警告终端(4)被配置为响应于接收到从所述车载通信装置(5)无线发送的车辆行驶数据，如果在接收到所述车辆行驶数据时的电场强度大于第一阈值(P)，则以听觉刺激之外的方式向所述行人(2)发出关于所述车辆(3)接近的警告。 | ||||||
| 78 | 用于提供大气状况信息的移动终端 | CN200510092254.1 | 2005-06-28 | CN1758657A | 2006-04-12 | 金姬贞 |
| 提供了一种用于提供UV辐射信息的移动终端。移动终端提供邻近地区的UV辐射指标，并且如果UV值超过预先确定的值则警告用户。用户被允许检查其中他当前位于的区域和周围区域的详细UV值，由此提供精确的并且有效的服务，允许用户识别具有高UV值的区域。移动终端还包括警告系统，当移动终端靠近或者处于如果UV指标超过预先确定值的区域时警告用户。 | ||||||
| 79 | 用于提供大气状况信息的移动终端 | CN200510092254.1 | 2005-06-28 | CN100548005C | 2009-10-07 | 金姬贞 |
| 提供了一种用于提供UV辐射信息的移动终端。移动终端提供邻近地区的UV辐射指标，并且如果UV值超过预先确定的值则警告用户。用户被允许检查其中他当前位于的区域和周围区域的详细UV值，由此提供精确的并且有效的服务，允许用户识别具有高UV值的区域。移动终端还包括警告系统，当移动终端靠近或者处于如果UV指标超过预先确定值的区域时警告用户。 | ||||||
| 80 | 一种便于查找的光纤跳线 | CN201110028084.6 | 2011-01-26 | CN102087389B | 2014-06-18 | 赖又诚 |
| 本发明公开了一种便于查找的光纤跳线，其包括光纤线和设于光纤线两端的光纤接头。在靠近两端光纤接头的光纤线上分别设有一警告器，而两个警告器通过与所述光纤线一体设置的并形成回路的两条导线连接，当其中一个警告器接通电源时，这两个警告器会同时发出警示信号。那么人们安装和维护时，对于大量大光纤跳线，只要接通光纤跳线的一个警告器的电源，则该条光纤跳线两端的警告器就会发亮或发出声音,人们就可以轻易地识别出哪是同一条光纤跳线，从而减少人为的疏忽及安装时间。本发明结构简单、制作方便，还可以大大的提高光纤系统的安装、调制和维护的工作效率。 | ||||||
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