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公开(公告)号：US11275388B2
公开(公告)日：2022-03-15
申请号：US16189228
申请日：2018-11-13
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Ratan Khatwa , Yasuo Ishihara
Abstract: Alerting systems and methods for an enhanced approach monitor are provided. The system is configured to: determine a missed approach altitude (MAA), an intended configuration, and target approach speed, each being related to the intended approach procedure and aircraft specific data. At a decision point defined as a co-occurrence of (a) the RT distance is substantially equal to or less than a distance threshold, and (b) the RT altitude is substantially equal to the MAA, the system identifies go-around scenarios, such as when (i) the RT speed exceeds the target approach speed, or (ii) the RT configuration is not equal to the intended configuration, or (iii) an RT approach path angle exceeds the target angle. The system issues a go-around alert based on whether the aircraft can perform a go-around operation, as determined based on aircraft performance data and terrain data.
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公开(公告)号：US10583845B1
公开(公告)日：2020-03-10
申请号：US16175574
申请日：2018-10-30
Applicant: Honeywell International Inc.
Inventor： James Alexander Nicholls , John Stokely , Dereck Clark , Yasuo Ishihara
Abstract: Systems and methods are disclosed for detecting security threats during vehicle operations. For instance, retrieving a route plan for a route of a vehicle from a database of the vehicle; identifying either a portion of the route or a portion of the route plan as a security threat based on an analysis of the route plan; and in response to identifying the portion of the route or the portion of the route plan as the security threat, transmitting an alert of the security threat.
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公开(公告)号：US20190323856A1
公开(公告)日：2019-10-24
申请号：US16014017
申请日：2018-06-21
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Glen Burlingame , Yasuo Ishihara , Steve Johnson , James Ehlers , Esko Mannisto
Abstract: Methods and apparatus are provided for generating a runway landing alert for an aircraft. The method comprises establishing a Runway Awareness Advisory System (RAAS) envelope for the designated target runway of the aircraft. A track of the aircraft is monitored with reference to a centerline of the target runway. Any deviation by the aircraft from the centerline of the target runway is detected and determined if it is within a margin of error. If the deviation is within the margin of error, an altitude parameter of the RAAS envelope is increased. If the aircraft is determined to still be maneuvering with respect to the centerline of the target runway, the altitude parameter of the RAAS envelope is decreased. Otherwise, an alert is generated if the aircraft is outside of the RAAS envelope.
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公开(公告)号：US09916765B2
公开(公告)日：2018-03-13
申请号：US14932492
申请日：2015-11-04
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Yasuo Ishihara , Steve Johnson
CPC classification number: G08G5/025 , G01S1/02 , G01S1/022 , G01S1/08 , G01S13/913 , G08G5/0021 , G08G5/0026 , G08G5/0073
Abstract: A method is provided for monitoring a landing approach of an aircraft. The method includes receiving instrument landing system (ILS) signals; determining a glideslope deviation from the ILS signals; disabling, when the glideslope deviation is less than a first predetermined threshold, at least one glideslope alert function; evaluating a current glideslope condition by comparing a designated glideslope angle to a glideslope check value; and re-enabling the at least one glideslope alert function when the glideslope check value differs from the designated glideslope angle by more than a second predetermined threshold.
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公开(公告)号：US20170124886A1
公开(公告)日：2017-05-04
申请号：US14932492
申请日：2015-11-04
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Yasuo Ishihara , Steve Johnson
CPC classification number: G08G5/025 , G01S1/02 , G01S1/022 , G01S1/08 , G01S13/913 , G08G5/0021 , G08G5/0026 , G08G5/0073
Abstract: A method is provided for monitoring a landing approach of an aircraft. The method includes receiving instrument landing system (ILS) signals; determining a glideslope deviation from the ILS signals; disabling, when the glideslope deviation is less than a first predetermined threshold, at least one glideslope alert function; evaluating a current glideslope condition by comparing a designated glideslope angle to a glideslope check value; and re-enabling the at least one glideslope alert function when the glideslope check value differs from the designated glideslope angle by more than a second predetermined threshold.
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Patent Agency Ranking
36.发明申请METHODS AND APPARATUS FOR DETERMINING AND USING A LANDING SURFACE FRICTION CONDITION 审中-公开用于确定和使用着陆表面摩擦条件的方法和装置公开(公告)号：US20160140854A1
公开(公告)日：2016-05-19
申请号：US14223579
申请日：2014-03-24
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Dale Frederick Enns , Yasuo Ishihara , Donald Carl Kauffman , Kenneth R. Jongsma , Christine Marie Haissig
CPC classification number: G08G5/025 , G01S13/74 , G08G5/0008 , G08G5/0013 , G08G5/0021 , G08G5/0086 , G08G5/0091
Abstract: A diagnostic method performed onboard an aircraft is provided. The method obtains aircraft state data during landing of the aircraft, via a plurality of avionics and aircraft systems; and determines a landing surface friction condition based on the aircraft state data, using at least one of the plurality of avionics and aircraft systems. A method of evaluating landing surface data onboard an aircraft is also provided. The method receives landing surface friction condition data, prior to landing; computes a required landing distance, based on the received landing surface friction condition data; and when the required landing distance is more than a predetermined threshold, performs a designated task.
Abstract translation: 提供了一种在飞机上执行的诊断方法。 该方法通过多个航空电子设备和飞行器系统在飞机着陆期间获得飞行器状态数据; 并且使用所述多个航空电子设备和飞行器系统中的至少一个来确定基于飞行器状态数据的着陆面摩擦条件。 还提供了一种评估飞机上的着陆面数据的方法。 该方法在着陆前接收着陆面摩擦条件数据; 基于所接收的着陆面摩擦条件数据计算所需的着陆距离; 并且当所需的着陆距离大于预定阈值时，执行指定的任务。
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公开(公告)号：US20150321748A1
公开(公告)日：2015-11-12
申请号：US14272738
申请日：2014-05-08
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Steve Johnson , Yasuo Ishihara , Kevin J. Conner
CPC classification number: B64C9/323 , B64D45/00 , B64D45/0005 , Y02T50/32
Abstract: A system and method is provided for controlling the speed of an aircraft with a speed brake during landing. The system includes a speed brake control system and a speed brake controller coupled to the speed brake control system for arming the speed brake. An alert generator is coupled to the speed brake controller for generating an alert when the speed brake is not armed.
Abstract translation: 提供了一种用于在着陆期间用速度制动器控制飞行器的速度的系统和方法。 该系统包括速度制动控制系统和与制动控制系统相连的速度制动控制器，用于制动速度制动器。 警报发生器耦合到速度制动控制器，用于当速度制动器未布防时产生警报。
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38.发明申请公开(公告)号：US20150298821A1
公开(公告)日：2015-10-22
申请号：US14258515
申请日：2014-04-22
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Yasuo Ishihara , Steve Johnson , Kevin J. Conner
Abstract: A system and method are provided for modifying the position or shape of a premature descent protection envelope with regard to a runway when an aircraft making an approach to the runway is below the nominal approach path and has a flight path angle greater than the nominal approach path angle.
Abstract translation: 提供了一种系统和方法，用于当飞机进入跑道时低于标称进场路径并且具有大于标称进场路径的飞行路径角度时，修改关于跑道的过早下降保护外壳的位置或形状 角度。
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39.发明申请公开(公告)号：US20150213721A1
公开(公告)日：2015-07-30
申请号：US14258839
申请日：2014-04-22
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Kevin J. Conner , Yasuo Ishihara , Steve Johnson , Ray Berry
CPC classification number: G08G5/04 , G05D1/0083 , G08G5/0021 , G08G5/0078 , G08G5/0086 , G08G5/06 , G08G5/065 , G09B9/052 , G09B29/006 , G09B29/007
Abstract: 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 is assigned to each of the aerodrome cells that is representative of the specific wingtip strike threat associated with that aerodrome cell. An index count array is generated that has a separate entry for each numeric value. A digital aircraft structure is generated that is representative of an aircraft, and is represented by a plurality of aircraft cells. A portion of the aerodrome cells are replaced with the plurality of aircraft cells. Each numeric value of the aerodrome cells that are 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.
Abstract translation: 用于被动地检测飞行器翼尖撞击的系统和方法包括生成由多个机场小区表示的数字基地图。 每个机场细胞都分配一个数字值，这些单元格代表与该机场细胞相关的特定的机翼罢工威胁。 生成索引计数数组，每个数值都有一个单独的条目。 产生代表飞行器的数字飞机结构，并且由多个飞机单元表示。 机场细胞的一部分被多个飞行器细胞代替。 对所替换的机场细胞的每个数值进行计数，以确定与之相关联的替换计数，并将其输入到该数值的索引计数数组中的单独条目中。 基于替换计数检测到一个或多个潜在的飞机翼尖撞击。
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公开(公告)号：US20150112517A1
公开(公告)日：2015-04-23
申请号：US14060768
申请日：2013-10-23
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Kevin J. Conner , Yasuo Ishihara , Steve Johnson
IPC: G08G5/02
CPC classification number: G08G5/0021 , G05D1/0077 , G05D1/0676 , G08G5/0065 , G08G5/025
Abstract: A system and method provide an alert to a pilot of an aircraft aurally with a given volume and inflection, and/or visually with a text message which includes color, font, and pitch (size). The alert is rendered in distinct fashion for the expected and unexpected cases, e.g., an intended runway and an unintended runway. In a preferred embodiment, the alert for the intended runway is changed to a confirmation level, or one that is less likely to interfere with other information flow, while the alert for the unintended runway would be provided in a more conspicuous manner.
Abstract translation: 一种系统和方法向具有给定音量和拐点的声音的飞行员提供警报，和/或以视觉方式提供包括颜色，字体和音调（大小）的文本消息的警报。 对于预期和意想不到的情况，例如预期的跑道和非预期的跑道，警报以不同的方式呈现。 在优选实施例中，预期跑道的警报改变为确认级别，或者更不可能干扰其他信息流的警报，同时将以更显眼的方式提供非预期跑道的警报。
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