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    Flaps overspeed advisory system
    1.
    发明授权
    Flaps overspeed advisory system 有权
    襟翼超速咨询系统

    公开(公告)号：US08451144B2

    公开(公告)日：2013-05-28

    申请号：US12365778

    申请日：2009-02-04

    申请人： Yasuo Ishihara ,  Steve Johnson ,  Kevin J Conner

    发明人： Yasuo Ishihara ,  Steve Johnson ,  Kevin J Conner

    IPC分类号： G08B23/00

    CPC分类号： G01C23/00 ,  B64D43/02 ,  G05D1/0055

    摘要： A flap advisory system provides an advisory to a pilot informing that a speed of the aircraft should be attended to because of a current or desired flap setting. More specifically, the flap advisory system compares a measured airspeed of the aircraft either directly to a flap placard speed or to a marginal speed range set below the flap placard speed for a given flap setting. If the measured airspeed is determined to be excessive then the system provides an advisory indicating the airspeed is too fast. Further, the system may provide an advisory when a movement of a flap handle is detected such that continued movement of the flap handle would place the flaps in a setting that is inappropriate for the measured airspeed.

    摘要翻译： 襟翼咨询系统向飞行员提供通知，指示飞机的速度应由于当前或期望的襟翼设置而受到照顾。 更具体地，襟翼咨询系统将飞行器的测量空速直接与折翼标牌速度相比较，或者对于给定的襟翼设置，将设置在襟翼标牌速度下方的边缘速度范围进行比较。 如果测量的空速被确定为过高，则系统提供一个指示空速太快的建议。 此外，当检测到襟翼手柄的移动时，系统可以提供咨询，使得襟翼手柄的持续移动将襟翼置于不适于测量的空速的设置中。

    Stable approach monitor (SAM) system
    2.
    发明授权
    Stable approach monitor (SAM) system 有权
    稳定进场监视（SAM）系统

    公开(公告)号：US08600586B2

    公开(公告)日：2013-12-03

    申请号：US12365751

    申请日：2009-02-04

    申请人： Yasuo Ishihara ,  Kevin J Conner ,  Steve Johnson

    发明人： Yasuo Ishihara ,  Kevin J Conner ,  Steve Johnson

    IPC分类号： G05D1/00

    CPC分类号： G08G5/025 ,  G01C23/005 ,  G05D1/0676

    摘要： An improved stable approach monitor (SAM) system provides an audible advisory to a pilot when an aircraft is on a final landing approach. More specifically, the SAM system compares a measured airspeed of the aircraft to a predetermined flap placard speed. If the measured airspeed exceeds the predetermined flap placard speed then the improved SAM system provides an audible advisory indicating the airspeed of the aircraft is too fast. Advantageously, this audible advisory should prevent the pilot from attempting to deploy the flaps at an excessive airspeed and in turn focuses the pilot's attention on the problem at hand, which would be to reduce the airspeed of the aircraft. Once the airspeed is equal to or below the predetermined flap placard speed, the improved SAM system may provide another audible advisory informing the pilot to commence deployment of the flaps.

    摘要翻译： 改进的稳定进场监视（SAM）系统为飞行员在最终着陆方法时提供可听见的咨询。 更具体地，SAM系统将飞行器的测量空速与预定的挡板标示速度进行比较。 如果测量的空速超过预定的挡板标示速度，则改进的SAM系统提供了一个可听见的建议，指示飞机的空速太快。 有利的是，这种可听见的咨询应该防止飞行员试图以过高的空速来部署襟翼，从而将飞行员的注意力集中在手头的问题上，这将是减少飞机的空速。 一旦空速等于或低于预定的翼片标示速度，改进的SAM系统可以提供另一个可听见的建议，通知飞行员开始襟翼的展开。

    Method of detecting erroneous GPS ground speed on ground
    3.
    发明授权
    Method of detecting erroneous GPS ground speed on ground 有权
    检测地面上错误的GPS地面速度的方法

    公开(公告)号：US08271191B2

    公开(公告)日：2012-09-18

    申请号：US11426547

    申请日：2006-06-26

    申请人： Yasuo Ishihara ,  Kevin J Conner ,  Steve C. Johnson

    发明人： Yasuo Ishihara ,  Kevin J Conner ,  Steve C. Johnson

    IPC分类号： G01C23/00

    CPC分类号： G01S19/52 ,  G01S19/20 ,  G01S19/48

    摘要： Methods and systems for determining reliability of Global Positioning System (GPS) ground speed. An example system receives GPS track information and GPS ground speed, determines a change in GPS track information and determines reliability of the GPS ground speed based on the determined change in GPS track information relative to the GPS ground speed. The system sets a GPS ground speed based on the determined reliability. A GPS ground speed output is set to zero, if the GPS ground speed is determined unreliable and the GPS ground speed output is set to the GPS ground speed, if the GPS ground speed is determined reliable. The system sends the GPS ground speed output to a Runway Awareness and Advisory System (RAAS). Also, the system sets the GPS ground speed output to zero, if a received GPS ground speed validity signal or a received GPS track validity signal indicate invalid.

    摘要翻译： 确定全球定位系统（GPS）地面速度的可靠性的方法和系统。 示例系统接收GPS轨道信息和GPS地面速度，确定GPS轨道信息的变化，并且基于GPS轨迹信息相对于GPS地面速度确定的变化来确定GPS地面速度的可靠性。 系统根据确定的可靠性设置GPS地面速度。 如果GPS地面速度被确定为可靠，则GPS地面速度输出被设置为零，如果GPS地面速度被确定为不可靠，并且将GPS地面速度输出设置为GPS地面速度。 系统将GPS地面速度输出发送到跑道意识和咨询系统（RAAS）。 此外，如果接收的GPS地面速度有效信号或接收的GPS轨道有效信号指示无效，则系统将GPS地面速度输出设置为零。

    Cabin altitude alerting systems and methods
    5.
    发明授权
    Cabin altitude alerting systems and methods 有权

    公开(公告)号：US09809313B2

    公开(公告)日：2017-11-07

    申请号：US11625764

    申请日：2007-01-22

    申请人： Kevin J Conner ,  Yasuo Ishihara ,  Steve C. Johnson

    发明人： Kevin J Conner ,  Yasuo Ishihara ,  Steve C. Johnson

    IPC分类号： B64D13/02

    CPC分类号： B64D13/02

    摘要： Systems and methods for intelligently alerting the flight crew of a cabin depressurization. An example system includes a cabin altimeter that generates a cabin pressure value, an alerting device, such as a speaker system and a processing device in data communication with the cabin altimeter and the alerting device. The processing device determines if there is a problem with the cabin pressure received from the cabin altimeter, determines rate of change of the cabin pressure, and sets at least one of an alert volume or an alert frequency based on the cabin pressure and the rate of change of the cabin pressure if it was determined that a problem exists with the cabin pressure. The processing device also issues a cabin depressurization alert over the alerting device based on at least one of the set alert volume or alert frequency, if there is a problem with the cabin pressure value.

    Systems and methods for intelligent alerting for cabin altitude depressurization
    6.
    发明授权
    Systems and methods for intelligent alerting for cabin altitude depressurization 有权
    用于机舱高度减压的智能报警系统和方法

    公开(公告)号：US07670214B2

    公开(公告)日：2010-03-02

    申请号：US11469376

    申请日：2006-08-31

    申请人： Kevin J Conner ,  Yasuo Ishihara ,  Charles D. Bateman

    发明人： Kevin J Conner ,  Yasuo Ishihara ,  Charles D. Bateman

    IPC分类号： B64D13/02 ,  B64D13/00 ,  B60H1/00

    CPC分类号： B64D13/02

    摘要： Methods and systems for providing a depressurization alert. An example method includes receiving a cabin depressurization discrete signal, determining if the cabin depressurization discrete signal is valid, and issuing a cabin depressurization alert, if the cabin depressurization discrete signal was determined to be valid. In accordance with further aspects of the invention, a time delay is executed before the receiving, determining, and issuing steps are repeated. The cabin depressurization discrete signal is determined not valid if uncorrected pressure is not greater than a predefined altitude. The uncorrected pressure is a raw pressure value produced by a Pitot-Static system. Also, the cabin depressurization discrete signal is determined not valid if the aircraft's altitude above an intended runway is not greater than a first predefined value. Additionally, the cabin depressurization discrete signal is determined not valid if an aircraft's altitude above terrain is not greater than a second predefined value.

    摘要翻译： 提供减压警报的方法和系统。 一种示例性方法包括：如果客舱减压离散信号被确定为有效，则接收客舱减压离散信号，确定客舱减压离散信号是否有效，并发出机舱减压警报。 根据本发明的其它方面，在重复接收，确定和发出步骤之前执行时间延迟。 如果未校正的压力不大于预定高度，则舱室减压离散信号被确定为无效。 未校正的压力是由皮托静力系统产生的原始压力值。 此外，如果飞机在预期跑道上方的高度不大于第一预定值，则机舱减压离散信号被确定为无效。 此外，如果飞机在地形上方的高度不大于第二预定义值，则机舱减压离散信号被确定为无效。

    METHODS AND SYSTEMS FOR MONITORING APPROACH OF ROTARY WING AIRCRAFT
    7.
    发明申请
    METHODS AND SYSTEMS FOR MONITORING APPROACH OF ROTARY WING AIRCRAFT 审中-公开
    用于监控旋转飞机的方法和系统

    公开(公告)号：US20080173753A1

    公开(公告)日：2008-07-24

    申请号：US11625673

    申请日：2007-01-22

    申请人： Yasuo Ishihara ,  Steve C. Johnson ,  Kevin J Conner

    发明人： Yasuo Ishihara ,  Steve C. Johnson ,  Kevin J Conner

    IPC分类号： B64D45/04

    CPC分类号： G05B23/0235

    摘要： Systems and methods for generating an alert if a rotary wing aircraft is approaching a hazardous situation. In an example method a processor receives a wind value and a rate of descent value. An alert signal is generated if the received wind value is greater than a tailwind threshold value and the rate of descent value is greater than a rate of descent threshold value. The generated alert is outputted to an output device, such as a display device or speakers. The alert signal is further generated if the rotary wing aircraft is on approach to landing, a rate of change of heading is less than a predefined value, or a rate of change in speed is less than a predefined value.

    摘要翻译： 如果旋翼飞机正在接近危险情况，产生警报的系统和方法。 在示例性方法中，处理器接收风值和下降速率值。 如果接收到的风值大于顺风阈值并且下降速率值大于下降阈值的速率，则产生报警信号。 生成的警报被输出到诸如显示装置或扬声器的输出装置。 如果旋转翼飞机正在着陆，则航向变化率小于预定值，或速度变化率小于预定值，进一步产生报警信号。

    Systems and methods for automatic detection of QFE operations
    8.
    发明授权
    Systems and methods for automatic detection of QFE operations 有权
    自动检测QFE操作的系统和方法

    公开(公告)号：US07389164B1

    公开(公告)日：2008-06-17

    申请号：US11625714

    申请日：2007-01-22

    申请人： Kevin J Conner ,  Steve C. Johnson ,  Yasuo Ishihara

    发明人： Kevin J Conner ,  Steve C. Johnson ,  Yasuo Ishihara

    IPC分类号： G01C5/00

    CPC分类号： G01C5/005

    摘要： Systems and methods for determining if an aircraft is approaching a atmospheric pressure at field elevation (QFE) airport and for alerting if any errors that might affect the production of an accurate altitude value. In an example method a global positioning system (GPS) altitude value is compared to a corrected barometric altitude, if an airport that the aircraft is proximate to (approaching) is a QFE airport. The field elevation of the proximate airport is added to the corrected barometric altitude to generate an adjusted barometric altitude, if the comparison between the GPS altitude and the corrected barometric altitude is greater than a predefined threshold. The adjusted barometric altitude is sent to relevant aircraft systems, such as an Enhanced Ground Proximity Warning System.

    摘要翻译： 用于确定飞机是否在场高程（QFE）机场接近大气压力的系统和方法，以及是否有可能影响准确高度值生产的错误的警报。 在示例性方法中，如果飞机靠近（接近）的机场是QFE机场，则将全球定位系统（GPS）高度值与校正的气压高度进行比较。 如果GPS高度与校正气压高度之间的比较大于预定义的阈值，则将邻近机场的场高程添加到校正的气压高度以产生调整的气压高度。 调整后的气压高度被发送到相关飞机系统，例如增强型地面接近警告系统。

    Passive aircraft wingtip strike detection system and method
    10.
    发明授权
    Passive aircraft wingtip strike detection system and method 有权

    公开(公告)号：US09805610B2

    公开(公告)日：2017-10-31

    申请号：US14561920

    申请日：2014-12-05

    申请人： Kevin J Conner ,  Yasuo Ishihara

    发明人： Kevin J Conner ,  Yasuo Ishihara

    IPC分类号： G08G5/04 ,  G08G1/16 ,  G08G5/00 ,  G08G5/06

    CPC分类号： G08G5/04 ,  G08G5/0021 ,  G08G5/065

    摘要： A system and method for passively detecting aircraft wingtip strikes includes generating a digital base map represented by a plurality of aerodrome cells. A numeric value representative of the specific wingtip is assigned to each of the aerodrome cells. An index count array is generated that has a separate entry for each numeric value. A digital aircraft structure representative of an aircraft is generated, and is represented by a plurality of aircraft cells. A determination is made as to whether a portion of the aerodrome cells are or would be replaced with the plurality of aircraft cells. Each numeric value of the aerodrome cells that are or would be replaced is counted to determine a replacement count associated therewith and that is entered into the separate entry in the index count array for that numeric value. One or more potential aircraft wingtip strikes are detected based on the replacement counts.