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公开(公告)号：US11138892B2
公开(公告)日：2021-10-05
申请号：US15847147
申请日：2017-12-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： James Alexander Nicholls , Michael Duane Mead , Erik Ringnes , Ratan Khatwa , Michael McSharry , Jon Bartling
Abstract: An enhanced flight control system and method providing a technological improvement over a conventional flight control systems. A control module employs rules to determine whether or not a received traffic collision avoidance system (TCAS) evasive maneuver is automatically implemented. Specifically, the control module effectively couples the TCAS to the FMS, allowing access to the flight plan and to the navigation database and the approach procedures and runway data therein. An algorithm determines when there is a co-occurrence of the conditions (1) a flight plan uploaded in the FMS, (2) autopilot is engaged, (3) VNAV is engaged. Upon co-occurrence of (1) and (2) and (3), and an evasive maneuver is received from a TCAS, the control module determines whether or not to automatically implement the evasive maneuver. Look ahead algorithms may also analyse and modify the flight plan to preclude TCAS alerts and evasive procedures being required.
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公开(公告)号：US20170043861A1
公开(公告)日：2017-02-16
申请号：US14823128
申请日：2015-08-11
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Pablo Bandera , Jon Bartling , Dean Wilkens
CPC classification number: B64C13/36 , B64C13/16 , B64C13/44 , B64C27/57 , B64C27/605 , B64C27/64 , F15B7/001
Abstract: A hydrostatic automatic flight servo system is provided. The automatic flight servo system includes a manifold that defines a first fluid chamber, and a hydraulic fluid is received in the first fluid chamber. The first fluid chamber includes a first bellows and a second bellows. The automatic flight servo system includes a stick received at least partially within the manifold and pivotally coupled to the manifold. The stick includes a control arm fixedly coupled to the first bellows, and the stick is to receive an input. The automatic flight servo system includes a flight output system pivotally coupled to the manifold. The flight output system includes a second control arm received at least partially within the manifold and coupled to the second bellows such that the pivotal movement of the stick pivots the flight output system relative to the manifold.
Abstract translation: 提供静液压自动飞行伺服系统。 自动飞行伺服系统包括限定第一流体室的歧管，并且液压流体容纳在第一流体室中。 第一流体室包括第一波纹管和第二波纹管。 自动飞行伺服系统包括至少部分地容纳在歧管内并且枢转地联接到歧管的杆。 该棒包括固定地联接到第一波纹管的控制臂，并且该杆用于接收输入。 自动飞行伺服系统包括枢转地联接到歧管的飞行输出系统。 飞行输出系统包括第二控制臂，该第二控制臂至少部分地容纳在歧管内并且联接到第二波纹管，使得该杆的枢转运动相对于歧管枢转飞行输出系统。
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公开(公告)号：US20190189017A1
公开(公告)日：2019-06-20
申请号：US15847147
申请日：2017-12-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： James Alexander Nicholls , Michael Duane Mead , Erik Ringnes , Ratan Khatwa , Michael McSharry , Jon Bartling
CPC classification number: G08G5/045 , G05D1/0061 , G08G5/0008 , G08G5/0039
Abstract: An enhanced flight control system and method providing a technological improvement over a conventional flight control systems is provided. A control module employs rules to determine whether or not a received traffic collision avoidance system (TCAS) evasive maneuver is automatically implemented. Specifically, the control module effectively couples the TCAS to the FMS, allowing access to the flight plan and to the navigation database and the approach procedures and runway data therein. An algorithm in the control module determines when there is a co-occurrence of the conditions (1) a flight plan uploaded in the FMS, (2) autopilot is engaged, (3) VNAV is engaged. Upon co-occurrence of (1) and (2) and (3), and an evasive maneuver is received from a TCAS, the control module determines whether or not to automatically implement the evasive maneuver. Look ahead algorithms may also analyse and modify the flight plan to preclude TCAS alerts and evasive procedures being required.
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公开(公告)号：US10118689B2
公开(公告)日：2018-11-06
申请号：US14823128
申请日：2015-08-11
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Pablo Bandera , Jon Bartling , Dean Wilkens
Abstract: A hydrostatic automatic flight servo system is provided. The automatic flight servo system includes a manifold that defines a first fluid chamber, and a hydraulic fluid is received in the first fluid chamber. The first fluid chamber includes a first bellows and a second bellows. The automatic flight servo system includes a stick received at least partially within the manifold and pivotally coupled to the manifold. The stick includes a control arm fixedly coupled to the first bellows, and the stick is to receive an input. The automatic flight servo system includes a flight output system pivotally coupled to the manifold. The flight output system includes a second control arm received at least partially within the manifold and coupled to the second bellows such that the pivotal movement of the stick pivots the flight output system relative to the manifold.
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