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    SYSTEM AND METHOD FOR USING AIRPORT INFORMATION BASED ON FLYING ENVIRONMENT
    11.
    发明申请
    SYSTEM AND METHOD FOR USING AIRPORT INFORMATION BASED ON FLYING ENVIRONMENT 审中-公开
    使用基于飞行环境的机场信息的系统和方法

    公开(公告)号：US20060080008A1

    公开(公告)日：2006-04-13

    申请号：US11161346

    申请日：2005-07-29

    申请人： Yasuo Ishihara ,  Steve Johnson ,  Kevin Conner

    发明人： Yasuo Ishihara ,  Steve Johnson ,  Kevin Conner

    IPC分类号： G01C23/00

    CPC分类号： G08G5/025 ,  G08G5/0065 ,  G08G5/0078

    摘要： Methods, systems, and computer program products for using airport information based on the flying environment. In one embodiment, a method of using airport information based on the flying environment includes determining height, ground speed, and if a helicopter is taking off based on determined height, determined ground speed, a takeoff height value and a takeoff speed value. In one embodiment, the helicopter is determined to be taking off when the determined height is less than the takeoff height value and when the determined ground speed is less than the takeoff speed value.

    摘要翻译： 基于飞行环境使用机场信息的方法，系统和计算机程序产品。 在一个实施例中，基于飞行环境使用机场信息的方法包括确定高度，地面速度，以及如果直升机基于确定的高度，确定的地面速度，起飞高度值和起飞速度值起飞。 在一个实施例中，当确定的高度小于起飞高度值时以及当确定的地面速度小于起飞速度值时，确定直升机正在起飞。

    Glideslope monitor for aircraft
    14.
    发明授权
    Glideslope monitor for aircraft 失效

    公开(公告)号：US06600977B2

    公开(公告)日：2003-07-29

    申请号：US09916633

    申请日：2001-07-27

    申请人： Steve C. Johnson ,  Yasuo Ishihara

    发明人： Steve C. Johnson ,  Yasuo Ishihara

    IPC分类号： G08G500

    CPC分类号： G08G5/025 ,  G01C5/005 ,  G01S1/022 ,  G01S1/18 ,  G05D1/0676

    摘要： A system, method, and computer program product for alerting an aircraft flight crew of an inconsistency during an instrument landing system (ILS) approach to a selected runway. The system includes a component configured to receive glideslope and localizer signals, and a component configured to determine aircraft approach angle to runway end. Also, a component configured to alert the aircraft flight crew of an approach inconsistency, if the determined aircraft approach angle to runway end is less than a threshold angular value and one or more parameters based on aircraft position and the received glideslope and localizer signals are met. The component configured to determine aircraft approach angle to runway end determines the aircraft approach angle to runway end based on aircraft geometric altitude, a vertical figure of merit, a horizontal figure of merit, runway elevation, and aircraft distance to runway threshold.

    Dry etching process for semiconductor
    15.
    发明授权
    Dry etching process for semiconductor 失效
    半导体干蚀刻工艺

    公开(公告)号：US5871659A

    公开(公告)日：1999-02-16

    申请号：US665545

    申请日：1996-06-18

    申请人： Yoshikazu Sakano ,  Kenji Kondo ,  Hajime Soga ,  Yasuo Ishihara ,  Yoshifumi Okabe

    发明人： Yoshikazu Sakano ,  Kenji Kondo ,  Hajime Soga ,  Yasuo Ishihara ,  Yoshifumi Okabe

    IPC分类号： H01L21/302 ,  H01L21/3065 ,  B44C1/22

    CPC分类号： H01L21/3065

    摘要： A process for dry etching a silicon substrate, in which a mask exposing a region of the surface of the silicon substrate is formed, and the exposed region is dry etched. The dry etching is performed with a gas mixture including chlorine or a chlorine-containing gas, an oxygen-containing gas, and a fluorine-containing gas in which a ratio of a flow rate of oxygen gas to a flow rate of chlorine gas, O.sub.2 /Cl.sub.2, is selected to be from 0.6 to 3. The gas mixture may also contain a fluorine-containing gas and helium. Preferably, the gas mixture excludes carbon-containing gases. The dry etching process allows for an increased etch rate, as well as a high etch selectivity compared to that of SiO.sub.2 gas. The trench formed in the substrate by this process can be made of a larger depth with high reproducibility and good configuration. The sidewall profile angle of the trench is maintained slightly tapered, with a sidewall profile angle of approximately 90 degrees. Also, by mixing HBr gas into the gas mixture, it is possible to better control the formation of the trench. Thus, this process makes it possible to form, in a silicon substrate, a regularly configured and very deep trench with high accuracy and high etch rate.

    摘要翻译： 一种用于干蚀刻硅衬底的方法，其中形成露出硅衬底表面的区域的掩模，并且暴露区域被干蚀刻。 干蚀刻用包括氯或含氯气体，含氧气体和含氟气体的气体混合物进行，其中氧气流量与氯气流量的比例为O 2 / Cl2被选择为0.6至3.气体混合物还可含有含氟气体和氦气。 优选地，气体混合物不包括含碳气体。 与SiO 2气体相比，干蚀刻工艺允许提高蚀刻速率，以及高蚀刻选择性。 通过该工艺在衬底中形成的沟槽可以由更大的深度制成，具有高的再现性和良好的配置。 沟槽的侧壁轮廓角保持略微渐缩，侧壁轮廓角度约为90度。 此外，通过将HBr气体混入气体混合物中，可以更好地控制沟槽的形成。 因此，该方法使得可以在硅衬底中形成具有高精度和高蚀刻速率的规则构造和非常深的沟槽。

    Passive aircraft wingtip strike detection system and method
    16.
    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.

    SYSTEMS AND METHODS FOR ADJUSTING SINK RATE ALERT ENVELOPE FOR SPECIAL LANDING ZONES
    17.
    发明申请
    SYSTEMS AND METHODS FOR ADJUSTING SINK RATE ALERT ENVELOPE FOR SPECIAL LANDING ZONES 有权
    用于调整特殊土地区的波动警报信号的系统和方法

    公开(公告)号：US20130106623A1

    公开(公告)日：2013-05-02

    申请号：US13286141

    申请日：2011-10-31

    申请人： Yasuo Ishihara ,  Steve Johnson ,  Gary A. Ostrom

    发明人： Yasuo Ishihara ,  Steve Johnson ,  Gary A. Ostrom

    IPC分类号： G08B23/00

    CPC分类号： G01C23/00 ,  B64D45/04 ,  G01C21/00 ,  G05D1/0676 ,  G08G5/0021 ,  G08G5/0086 ,  G08G5/025

    摘要： Systems and methods for improving sink rate alerting for rotary wing aircraft. In one example, the system includes a radio altimeter that produces an altitude value, a processor that is in signal communication with the user interface device and the radio altimeter. The processor receives an altitude value, a position value for the aircraft and landing zone (LZ) information. The processor determines if the aircraft is on an approach to land at an LZ that is raised above surrounding terrain based on the received position value and LZ information. The processor receives sink rate information for the aircraft and generates a sink rate alert based on the received sink rate information and the aircraft altitude value if the sink rate information is greater than a sink rate value adjusted according to the LZ information. An output device outputs the generated sink rate alert. The LZ information includes an altitude value.

    摘要翻译： 用于改善旋翼飞机的下沉速率警报的系统和方法。 在一个示例中，系统包括产生高度值的无线电高度计，与用户接口设备和无线电高度计信号通信的处理器。 处理器接收高度值，飞机和着陆区（LZ）信息的位置值。 处理器根据接收到的位置值和LZ信息确定飞机是否处于在周围地形以上升起的LZ的地面上。 处理器接收飞行器的汇率信息，并且如果汇率信息大于根据LZ信息调整的汇率值，则基于接收的汇率信息和飞机高度值，生成汇率报警。 输出设备输出生成的下降速率警报。 LZ信息包括高度值。

    Stabilized approach monitor
    18.
    发明授权
    Stabilized approach monitor 有权
    稳定的进场监视器

    公开(公告)号：US08116923B2

    公开(公告)日：2012-02-14

    申请号：US12621794

    申请日：2009-11-19

    申请人： Yasuo Ishihara ,  Steve Johnson

    发明人： Yasuo Ishihara ,  Steve Johnson

    IPC分类号： B64D45/04 ,  G06F19/00 ,  G01C23/00 ,  B64D45/00

    CPC分类号： G05D1/0676 ,  G08G5/0021 ,  G08G5/02 ,  G08G5/025

    摘要： Systems and methods for suppressing an unstable alert when the aircraft is in the process of landing on a temporarily displaced threshold. In an example process, a processor on the aircraft determines the aircraft is on an approach to landing on a runway based on information received from one or more data sources on the aircraft, then retrieves predefined glideslope information for the runway from a memory device that is in signal communication with the processor. Next, the processor determines whether position of the aircraft is above the predefined glideslope by a first threshold amount. If the aircraft is determined to be above the predefined glideslope by the first threshold amount, the processor issues an unstable alert only if a flight path angle of the aircraft is greater than an angle of the predefined glideslope by a second threshold amount.

    摘要翻译： 当飞机正在临时移动的阈值上着陆的过程中用于抑制不稳定警报的系统和方法。 在示例过程中，飞行器上的处理器基于从飞机上的一个或多个数据源接收到的信息来确定飞行器正在着陆在跑道上，然后从存储器设备中检索用于跑道的预定滑翔信息， 与处理器进行信号通信。 接下来，处理器确定飞行器的位置是否高于预定滑行边界第一阈值量。 如果飞行器被确定为高于预定滑翔道第一阈值量，则只有当飞行器的飞行路径角度大于预定滑翔坡的角度达到第二阈值量时，处理器才发出不稳定的警报。

    Tailwind alerting system to prevent runway overruns
    19.
    发明授权
    Tailwind alerting system to prevent runway overruns 有权
    尾风警报系统防止跑道超限

    公开(公告)号：US07394402B2

    公开(公告)日：2008-07-01

    申请号：US11161368

    申请日：2005-08-01

    申请人： Yasuo Ishihara ,  Steve C. Johnson

    发明人： Yasuo Ishihara ,  Steve C. Johnson

    IPC分类号： G08B23/00

    CPC分类号： G05D1/0676 ,  G01C5/005

    摘要： Systems, methods and computer program products for alerting a flight crew during landing that the tailwind exceeds acceptable limits. The system determines a base tailwind threshold speed for a candidate runway based on a performance constant associated with an aircraft and candidate runway information and determines present tailwind speed. If the tailwind speed is greater than the base tailwind threshold speed, a tailwind alert is generated. Also, the system determines if the aircraft is in a tailwind alerting mode based on configuration of the aircraft and activates tailwind alerting, if it is determined that the aircraft is in the tailwind alerting mode.

    摘要翻译： 系统，方法和计算机程序产品，用于在着陆期间提醒飞行机组人员，后排超过可接受的限制。 系统基于与飞行器和候选跑道信息相关联的性能常数来确定候选跑道的基本倒带阈值速度，并确定当前的顺风速度。 如果顺风速度大于基本的倒档门限速度，则会产生顺风警报。 此外，如果确定飞行器处于顺风警报模式，则系统基于飞行器的配置来确定飞行器是否处于顺风警报模式，并启动顺风警报。

    SYSTEMS AND METHODS FOR BROADCASTING AN UNKNOWN AIRPORT ADVISORY
    20.
    发明申请
    SYSTEMS AND METHODS FOR BROADCASTING AN UNKNOWN AIRPORT ADVISORY 有权
    广播未知机场咨询的系统和方法

    公开(公告)号：US20080059010A1

    公开(公告)日：2008-03-06

    申请号：US11469802

    申请日：2006-09-01

    申请人： Kevin J. Conner ,  Yasuo Ishihara

    发明人： Kevin J. Conner ,  Yasuo Ishihara

    IPC分类号： G01C23/00 ,  G06F19/00

    CPC分类号： G01C23/005 ,  G08G5/0021 ,  G08G5/025

    摘要： Systems and methods for advising a flight crew member that an enhanced ground proximity warning system (EGPWS), for example, may continue to provide terrain alerts, cautions, warnings, or the like because an intended landing site for the aircraft is not recognized within a database of airports. An unknown airport advisory is generated and broadcast after the aircraft is in a landing configuration, when the aircraft is greater than a threshold distance from the nearest landing site in the database, but before the terrain alerts are broadcast. The pilot may actuate a “terrain inhibit” selection device after receiving the advisory. The inhibit device may deactivate or mute subsequent alerts generated by the EGPWS during that particular landing sequence.

    摘要翻译： 为飞行机组成员提供建议的系统和方法，例如，增强的地面接近警告系统（EGPWS）可能会继续提供地形警报，警告，警告等，因为飞机的预定着陆点在 机场数据库 在飞机处于着陆配置之后，当飞行器大于距离数据库中最近的着陆点的阈值距离之前，但在广播地形警报之前，将产生一个未知的机场咨询。 飞行员可以在收到建议书后启动“地形禁止”选择装置。 禁止装置可以在该特定着陆序列期间停用或静音由EGPWS产生的后续警报。