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Patent Agency Ranking
公开(公告)号：US09915925B2
公开(公告)日：2018-03-13
申请号：US14189247
申请日：2014-02-25
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Andrew Peter Vechart , Darryl Busch , Dale Frederick Enns
CPC classification number: G05B9/02 , G05B23/0256
Abstract: A system and method for verifying the response capabilities of a control effector include processing, in a test module, at least command data and sensor data associated with the control effector to generate control effector health data representative of control effector health. The control effector health data are processed in a reasoner to selectively indict and clear one or more faults, determine a failure is uncertain based on the one or more indicted faults, determine one or more test excitation signals to supply to the control effector to verify whether the uncertain failure is present or absent, and supply the one or more test excitation signals to a controller that is in operable communication with the control effector.
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公开(公告)号：US20160023776A1
公开(公告)日：2016-01-28
申请号：US14339206
申请日：2014-07-23
Applicant: Honeywell International Inc.
Inventor： Subhabrata Ganguli , Dale Frederick Enns , Xiahong Linda Li
Abstract: Systems and methods for airspeed estimation using actuation signals are provided. In one embodiment, an on-board avionics airspeed estimation system is provided. The system comprises: a flight control surface for an aircraft; a control surface actuator coupled to the flight control surface, wherein the control surface actuator receives an actuator control output signal from an actuator control system and drives the flight control surface into a position based on the actuator control output signal; a wind estimator coupled to a plurality of aircraft sensors, wherein the plurality of aircraft sensors output a set of aircraft measurements to the wind estimator and wherein the actuator control output signal is further provided to the wind estimator; wherein the wind estimator calculates a wind speed estimate by applying the actuator control output and the set of aircraft measurements to an onboard aircraft model.
Abstract translation: 提供使用致动信号进行空速估计的系统和方法。 在一个实施例中，提供了一种车载航空电子飞行速度估计系统。 该系统包括：飞机的飞行控制面; 控制表面致动器，其耦合到所述飞行控制表面，其中所述控制表面致动器接收来自致动器控制系统的致动器控制输出信号，并且基于所述致动器控制输出信号将所述飞行控制表面驱动到位置; 耦合到多个飞行器传感器的风力估计器，其中所述多个飞行器传感器将一组飞行器测量值输出到所述风力估计器，并且其中所述致动器控制输出信号进一步提供给所述风力估计器; 其中所述风力估计器通过将所述致动器控制输出和所述一组飞行器测量值应用于机载飞行器模型来计算风速估计。
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公开(公告)号：US20150241853A1
公开(公告)日：2015-08-27
申请号：US14189247
申请日：2014-02-25
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Andrew Peter Vechart , Darryl Busch , Dale Frederick Enns
IPC: G05B9/02
CPC classification number: G05B9/02 , G05B23/0256
Abstract: A system and method for verifying the response capabilities of a control effector include processing, in a test module, at least command data and sensor data associated with the control effector to generate control effector health data representative of control effector health. The control effector health data are processed in a reasoner to selectively indict and clear one or more faults, determine a failure is uncertain based on the one or more indicted faults, determine one or more test excitation signals to supply to the control effector to verify whether the uncertain failure is present or absent, and supply the one or more test excitation signals to a controller that is in operable communication with the control effector.
Abstract translation: 用于验证控制效应器的响应能力的系统和方法包括在测试模块中处理与控制效应器相关联的至少命令数据和传感器数据，以产生表示控制效应器健康的控制效应器健康数据。 控制效应器健康数据在推理器中被处理以选择性地指示和清除一个或多个故障，基于一个或多个被指示的故障确定故障是不确定的，确定一个或多个测试激励信号以供应给控制效应器以验证是否 存在或不存在不确定故障，并且将一个或多个测试激励信号提供给与控制执行器可操作地通信的控制器。
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公开(公告)号：US09428279B2
公开(公告)日：2016-08-30
申请号：US14339206
申请日：2014-07-23
Applicant: Honeywell International Inc.
Inventor： Subhabrata Ganguli , Dale Frederick Enns , Xiahong Linda Li
Abstract: Systems and methods for airspeed estimation using actuation signals are provided. In one embodiment, an on-board avionics airspeed estimation system is provided. The system comprises: a flight control surface for an aircraft; a control surface actuator coupled to the flight control surface, wherein the control surface actuator receives an actuator control output signal from an actuator control system and drives the flight control surface into a position based on the actuator control output signal; a wind estimator coupled to a plurality of aircraft sensors, wherein the plurality of aircraft sensors output a set of aircraft measurements to the wind estimator and wherein the actuator control output signal is further provided to the wind estimator; wherein the wind estimator calculates a wind speed estimate by applying the actuator control output and the set of aircraft measurements to an onboard aircraft model.
Abstract translation: 提供使用致动信号进行空速估计的系统和方法。 在一个实施例中，提供了一种车载航空电子飞行速度估计系统。 该系统包括：飞机的飞行控制面; 控制表面致动器，其耦合到所述飞行控制表面，其中所述控制表面致动器接收来自致动器控制系统的致动器控制输出信号，并且基于所述致动器控制输出信号将所述飞行控制表面驱动到位置; 耦合到多个飞行器传感器的风力估计器，其中所述多个飞行器传感器将一组飞行器测量值输出到所述风力估计器，并且其中所述致动器控制输出信号进一步提供给所述风力估计器; 其中所述风力估计器通过将所述致动器控制输出和所述一组飞行器测量值应用于机载飞行器模型来计算风速估计。
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5.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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