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1.发明申请公开(公告)号：US20150235560A1
公开(公告)日：2015-08-20
申请号：US14181906
申请日：2014-02-17
Applicant: The Boeing Company
Inventor： Russell Enns , Bryan Kashawlic
IPC: G08G5/02
CPC classification number: G08G5/02 , G08G5/0086 , G08G5/025
Abstract: Systems and methods provide sloped landing exceedance warning and avoidance. One system includes a surface slope determination system configured to measure a plurality of distances between an aircraft and a surface. The system also includes an inertial navigation system configured to sense aircraft attitude information. A flight control system is communicatively coupled to the surface slope determination system and the inertial navigation system. The flight control system is configured to estimate a slope angle of the surface. The flight control system is also configured to determine one or more approach characteristics based on the slope angle and the aircraft attitude information. The flight control system is additionally configured to identify a warning condition and perform one or more avoidance measures when one or more of the approach characteristics exceeds a predetermined threshold. A pilot cuing device also generates a notification when the warning condition is identified.
Abstract translation: 系统和方法提供倾斜着陆超越警告和避免。 一个系统包括配置成测量飞行器和表面之间的多个距离的表面坡度确定系统。 该系统还包括被配置成感测飞机姿态信息的惯性导航系统。 飞行控制系统通信地耦合到表面坡度确定系统和惯性导航系统。 飞行控制系统被配置为估计表面的倾斜角度。 飞行控制系统还被配置为基于倾斜角度和飞机姿态信息来确定一个或多个接近特性。 飞行控制系统另外配置成识别警告状况，并且当一个或多个接近特性超过预定阈值时执行一个或多个避免措施。 当识别出警告条件时，飞行员监视设备也会生成通知。
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公开(公告)号：US11822349B2
公开(公告)日：2023-11-21
申请号：US17648563
申请日：2022-01-21
Applicant: THE BOEING COMPANY
Inventor： Bryan Kashawlic , Bryan C.H. Chu , Russell Enns , Alex Salem Bourreza , Stephen Alexander Mohammed , Erik Bellandi
CPC classification number: G05D1/104 , B64C39/024 , G05D1/0061 , G05D1/1064 , B64U2201/102
Abstract: An aircraft and method of operating an aircraft include a flight formation control unit configured to automatically transition the aircraft into an automatic flight formation mode in response to the aircraft being within one or both of a predetermined speed or a predetermined range in relation to at least one other aircraft flying within the automatic flight formation mode. The flight formation control unit can be further configured to automatically transition the aircraft out of the automatic flight formation mode in response to detection of a control signal received from one or more flight controls of the aircraft. The flight formation control unit can be further configured to automatically cycle the aircraft and the at least one other aircraft to different positions during the automatic flight formation mode.
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公开(公告)号：US11148785B2
公开(公告)日：2021-10-19
申请号：US16548118
申请日：2019-08-22
Applicant: The Boeing Company
Inventor： Jaheen Noor Ahmad , Bryan C. Chu , Russell Enns , Gary D. Klein
Abstract: A flight control system having a plurality of dual mode operator control inputs is disclosed and includes a plurality of active parallel actuators, one or more processors, and memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the flight control system to receive a signal indicating an airspeed of the compound aircraft and select between rotary and fixed wing modes of operation based on the airspeed. In response to selecting a mode of operation, the flight control system sends either a rotary or a fixed wing force feel profile to the plurality of active parallel actuators, where the force feel profile defines the respective detent force gradient, where the fixed wing detent force gradient is at least about two times greater than a rotary wing detent force gradient.
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公开(公告)号：US11059568B2
公开(公告)日：2021-07-13
申请号：US16298480
申请日：2019-03-11
Applicant: The Boeing Company
Inventor： Bryan C. Chu , Joseph G. Irwin , Russell Enns , Gary D. Klein , Jon F. Lenander
Abstract: A control system having a variable operator interface (VOI) is disclosed, and includes one or more processors and a memory coupled to the processors. The memory stores program code causing the control system to detect an existence and first direction of an operator control input to one or more active inceptors being backdriven from an operator on inceptor detector (OID). The control system is caused to compare the first direction of the operator control input with a second direction of one or more zero-force detent rates to determine a variance and interprets the operator control input as inadvertent based on the variance. In response to interpreting the operator control input as inadvertent, the control system is caused to limit the operator control input to reduce or substantially eliminate movement of the machine caused by inadvertent input by modifying the operator control input based on one or more command modifiers.
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公开(公告)号：US20210061444A1
公开(公告)日：2021-03-04
申请号：US16548118
申请日：2019-08-22
Applicant: The Boeing Company
Inventor： Jaheen Noor Ahmad , Bryan C. Chu , Russell Enns , Gary D. Klein
Abstract: A flight control system having a plurality of dual mode operator control inputs is disclosed and includes a plurality of active parallel actuators, one or more processors, and memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the flight control system to receive a signal indicating an airspeed of the compound aircraft and select between rotary and fixed wing modes of operation based on the airspeed. In response to selecting a mode of operation, the flight control system sends either a rotary or a fixed wing force feel profile to the plurality of active parallel actuators, where the force feel profile defines the respective detent force gradient, where the fixed wing detent force gradient is at least about two times greater than a rotary wing detent force gradient.
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Patent Agency Ranking
公开(公告)号：US20200290728A1
公开(公告)日：2020-09-17
申请号：US16298480
申请日：2019-03-11
Applicant: The Boeing Company
Inventor： Bryan C. Chu , Joseph G. Irwin , Russell Enns , Gary D. Klein , Jon F. Lenander
Abstract: A control system having a variable operator interface (VOI) is disclosed, and includes one or more processors and a memory coupled to the processors. The memory stores program code causing the control system to detect an existence and first direction of an operator control input to one or more active inceptors being backdriven from an operator on inceptor detector (OID). The control system is caused to compare the first direction of the operator control input with a second direction of one or more zero-force detent rates to determine a variance and interprets the operator control input as inadvertent based on the variance. In response to interpreting the operator control input as inadvertent, the control system is caused to limit the operator control input to reduce or substantially eliminate movement of the machine caused by inadvertent input by modifying the operator control input based on one or more command modifiers.
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公开(公告)号：US20220404843A1
公开(公告)日：2022-12-22
申请号：US17648563
申请日：2022-01-21
Applicant: THE BOEING COMPANY
Inventor： Bryan Kashawlic , Bryan C.H. Chu , Russell Enns , Alex Salem Bourreza , Stephen Alexander Mohammed , Erik Bellandi
Abstract: An aircraft and method of operating an aircraft include a flight formation control unit configured to automatically transition the aircraft into an automatic flight formation mode in response to the aircraft being within one or both of a predetermined speed or a predetermined range in relation to at least one other aircraft flying within the automatic flight formation mode. The flight formation control unit can be further configured to automatically transition the aircraft out of the automatic flight formation mode in response to detection of a control signal received from one or more flight controls of the aircraft. The flight formation control unit can be further configured to automatically cycle the aircraft and the at least one other aircraft to different positions during the automatic flight formation mode.
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公开(公告)号：US10908560B2
公开(公告)日：2021-02-02
申请号：US16298468
申请日：2019-03-11
Applicant: The Boeing Company
Inventor： Joseph G. Irwin , Bryan C. Chu , Russell Enns , Gary D. Klein , Jon F. Lenander
Abstract: A control system for a machine having variable rate damping based control (VRDC) is disclosed, and includes one or more processors and a memory coupled to the processors storing data comprising a database and program code that, when executed by the processors, causes the control system to receive an inceptor position from one or more active inceptors and calculate an operator command based on at least the inceptor position. The control system is caused to determine an amplitude of the operator command. The control system is caused to determine a variable gain based on the amplitude of the operator command and determines an actuation command based on the variable gain. The control system sends the inline actuators the actuation command. The inline actuators actuate into a total actuator position to variably damp movement of the machine as a function of the magnitude of the operator command.
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公开(公告)号：US20200293004A1
公开(公告)日：2020-09-17
申请号：US16298468
申请日：2019-03-11
Applicant: The Boeing Company
Inventor： Joseph G. Irwin , Bryan C. Chu , Russell Enns , Gary D. Klein , Jon F. Lenander
Abstract: A control system for a machine having variable rate damping based control (VRDC) is disclosed, and includes one or more processors and a memory coupled to the processors storing data comprising a database and program code that, when executed by the processors, causes the control system to receive an inceptor position from one or more active inceptors and calculate an operator command based on at least the inceptor position. The control system is caused to determine an amplitude of the operator command. The control system is caused to determine a variable gain based on the amplitude of the operator command and determines an actuation command based on the variable gain. The control system sends the inline actuators the actuation command. The inline actuators actuate into a total actuator position to variably damp movement of the machine as a function of the magnitude of the operator command.
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公开(公告)号：US09734726B2
公开(公告)日：2017-08-15
申请号：US14181906
申请日：2014-02-17
Applicant: The Boeing Company
Inventor： Russell Enns , Bryan Kashawlic
IPC: G08G5/02
CPC classification number: G08G5/02 , G08G5/0086 , G08G5/025
Abstract: Systems and methods provide sloped landing exceedance warning and avoidance. One system includes a surface slope determination system configured to measure a plurality of distances between an aircraft and a surface. The system also includes an inertial navigation system configured to sense aircraft attitude information. A flight control system is communicatively coupled to the surface slope determination system and the inertial navigation system. The flight control system is configured to estimate a slope angle of the surface. The flight control system is also configured to determine one or more approach characteristics based on the slope angle and the aircraft attitude information. The flight control system is additionally configured to identify a warning condition and perform one or more avoidance measures when one or more of the approach characteristics exceeds a predetermined threshold. A pilot cuing device also generates a notification when the warning condition is identified.
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