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公开(公告)号：US11383829B2
公开(公告)日：2022-07-12
申请号：US16054937
申请日：2018-08-03
Applicant: Bell Helicopter Textron Inc.
Abstract: The system is configured for automation of rotorcraft entry into autorotation. The system can provide a means to assist the flight crew of a rotorcraft in maintaining rotor speed following loss of engine power. The system can automatically adjust control positions, actuator positions or both to prevent excessive loss of rotor speed upon initial loss of engine power before the flight crew is able to react. The system uses model matching to provide axis decoupling and yaw anticipation; it includes pitch control initially to assist in preventing rotor deceleration; and it makes use of collective, pitch, roll and yaw trim functions to provide tactile cueing to the pilot to assist when the pilot is in the loop. The system can reduce workload by assisting the crew with controlling rotor speed and forward speed during stabilized autorotation.
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公开(公告)号：US10239610B2
公开(公告)日：2019-03-26
申请号：US15062375
申请日：2016-03-07
Applicant: Bell Helicopter Textron Inc.
Inventor： Carlos A. Fenny , Carl T. Elving , Rodney M. Cahoon , Charles Eric Covington
IPC: B64C27/64 , B64C27/605 , F15B15/14
Abstract: In some embodiments, an actuator includes a chamber, a piston disposed within the chamber, and a tube. The chamber has a first port and a second port. The piston comprises a first surface, a second surface, and an elongated conduit coupling the first surface to the second surface. The first surface is disposed between the first port and the second port. The second surface is offset from the first surface. The tube is disposed at least partially within the elongated conduit of the piston. The tube comprises a third port disposed within the elongated conduit of the piston and a fourth port disposed outside of the elongated conduit of the piston.
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公开(公告)号：US20180222597A1
公开(公告)日：2018-08-09
申请号：US15424801
申请日：2017-02-04
Applicant: Bell Helicopter Textron Inc.
Inventor： Charles Eric Covington , Joseph Schaeffer , Robert Earl Worsham, II
CPC classification number: B64D35/00 , B64C13/503 , B64C27/04 , B64D31/06 , F02C9/28 , F05D2220/323 , F05D2270/313 , G05B13/00
Abstract: A power demand anticipation system for a rotorcraft includes an engine subsystem having an engine with a power output. The power demand anticipation system also includes one or more sensors including a cyclic control sensor. The one or more sensors are operable to detect one or more flight parameters of the rotorcraft to form sensor data including a cyclic control position. A power demand anticipation module is in data communication with the engine subsystem and the one or more sensors. The power demand anticipation module is operable to anticipate a power demand of the engine using the sensor data to form a power demand anticipation signal. The engine subsystem is operable to adjust the power output of the engine based on the power demand anticipation signal received from the power demand anticipation module.
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公开(公告)号：US09783290B2
公开(公告)日：2017-10-10
申请号：US14038182
申请日：2013-09-26
Applicant: Bell Helicopter Textron Inc.
Inventor： Charles Eric Covington , Carlos A. Fenny
CPC classification number: B64C27/64 , B64C27/605 , H01F7/066 , H01F7/122 , H02K7/003
Abstract: According to one embodiment, a linear control motor includes a first permanent magnet, a coil, a shaft, a first non-magnetic material, and a joint coupled between the shaft and a spool operable to convert rotations of the shaft into axial movements of the spool. The first non-magnetic material is disposed between at least one of the movable components and at least one of the static components and operable to prevent physical contact between at least one of the movable components and at least one of the static components.
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公开(公告)号：US20160221672A1
公开(公告)日：2016-08-04
申请号：US14609905
申请日：2015-01-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Geoffrey C. Latham , Carlos A. Fenny , Jean-Sébastian Plante , Brady Atkins , Guifré Julio , Marc Denninger , Charles Eric Covington , Paul Wilson
Abstract: According to one embodiment, a trim actuator for a pilot input device includes a driven member and a driving member configured to receive mechanical energy from a power source. A magnetorheological (MR) fluid is disposed between the driving member and the driven member and configured to transmit a variable amount of mechanical energy from the driving member to the driven member. An output member configured to be coupled between the driven member and the pilot input device. A magnetic circuit configured to deliver a magnetic field towards the MR fluid. The magnetic circuit is configured to control movement of the pilot input device by varying the strength of the magnetic field delivered towards the first MR fluid.
Abstract translation: 根据一个实施例，用于先导输入装置的修整致动器包括从动构件和构造成从动力源接收机械能的驱动构件。 磁流变（MR）流体设置在驱动构件和从动构件之间，并且构造成将可变量的机械能从驱动构件传递到从动构件。 输出构件，被配置为联接在从动构件和导向输入装置之间。 磁路，被配置为向MR流体传送磁场。 磁路被配置为通过改变朝向第一MR流体传送的磁场的强度来控制先导输入装置的运动。
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Patent Agency Ranking
公开(公告)号：US09227738B2
公开(公告)日：2016-01-05
申请号：US13731974
申请日：2012-12-31
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： John R. Wittmaak, Jr. , Jayme Gonzalez , Charles Eric Covington , Carlos Fenny
CPC classification number: B64F5/0045 , B64F5/60 , G05B23/0256
Abstract: A system and method to diagnosis an actuator of a flight control system. The system and method includes interfacing a diagnostic computer to the flight control system, commanding movement of an actuator with the diagnostic computer via the flight control system, measuring performance of the actuator via the diagnostic computer, and comparing the measured performance of the actuator with allowable performance values.
Abstract translation: 一种用于诊断飞行控制系统的执行器的系统和方法。 该系统和方法包括将诊断计算机连接到飞行控制系统，通过飞行控制系统命令致动器与诊断计算机的运动，通过诊断计算机测量致动器的性能，并将执行器的测量性能与允许的 性能价值。
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公开(公告)号：US20140188332A1
公开(公告)日：2014-07-03
申请号：US13731974
申请日：2012-12-31
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： John R. Wittmaak, JR. , Jayme Gonzalez , Charles Eric Covington , Carlos Fenny
IPC: B64F5/00
CPC classification number: B64F5/0045 , B64F5/60 , G05B23/0256
Abstract: A system and method to diagnosis an actuator of a flight control system. The system and method includes interfacing a diagnostic computer to the flight control system, commanding movement of an actuator with the diagnostic computer via the flight control system, measuring performance of the actuator via the diagnostic computer, and comparing the measured performance of the actuator with allowable performance values.
Abstract translation: 一种用于诊断飞行控制系统的执行器的系统和方法。 该系统和方法包括将诊断计算机连接到飞行控制系统，通过飞行控制系统命令致动器与诊断计算机的运动，通过诊断计算机测量致动器的性能，并将执行器的测量性能与允许的 性能价值。
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公开(公告)号：US09656746B2
公开(公告)日：2017-05-23
申请号：US14609905
申请日：2015-01-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Geoffrey C Latham , Carlos A Fenny , Jean-Sébastien Plante , Brady Atkins , Guifré Julio , Marc Denninger , Charles Eric Covington , Paul Wilson
Abstract: According to one embodiment, a trim actuator for a pilot input device includes a driven member and a driving member configured to receive mechanical energy from a power source. A magnetorheological (MR) fluid is disposed between the driving member and the driven member and configured to transmit a variable amount of mechanical energy from the driving member to the driven member. An output member configured to be coupled between the driven member and the pilot input device. A magnetic circuit configured to deliver a magnetic field towards the MR fluid. The magnetic circuit is configured to control movement of the pilot input device by varying the strength of the magnetic field delivered towards the first MR fluid.
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公开(公告)号：US20160264239A1
公开(公告)日：2016-09-15
申请号：US15062375
申请日：2016-03-07
Applicant: Bell Helicopter Textron Inc.
Inventor： Carlos A. Fenny , Carl T. Elving , Rodney M. Cahoon , Charles Eric Covington
IPC: B64C27/64
CPC classification number: B64C27/64 , B64C27/605 , F15B15/1457 , F15B15/1466 , F15B2211/7054 , F15B2211/7055
Abstract: In some embodiments, an actuator includes a chamber, a piston disposed within the chamber, and a tube. The chamber has a first port and a second port. The piston comprises a first surface, a second surface, and an elongated conduit coupling the first surface to the second surface. The first surface is disposed between the first port and the second port. The second surface is offset from the first surface. The tube is disposed at least partially within the elongated conduit of the piston. The tube comprises a third port disposed within the elongated conduit of the piston and a fourth port disposed outside of the elongated conduit of the piston.
Abstract translation: 在一些实施例中，致动器包括室，设置在室内的活塞和管。 该室具有第一端口和第二端口。 活塞包括第一表面，第二表面和将第一表面连接到第二表面的细长导管。 第一表面设置在第一端口和第二端口之间。 第二表面偏离第一表面。 管至少部分地设置在活塞的细长导管内。 管包括设置在活塞的细长导管内的第三端口和设置在活塞的细长导管外侧的第四端口。
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公开(公告)号：US09156567B2
公开(公告)日：2015-10-13
申请号：US14338944
申请日：2014-07-23
Applicant: Bell Helicopter Textron Inc.
Inventor： Charles Eric Covington , Brian E. Tucker , Thomas B. Priest , David A. Platz , James M. McCollough
CPC classification number: B64F5/0045 , B64D45/00 , B64F5/60 , G01C23/00 , G05D1/0005
Abstract: The present application relates to a system and method for providing real-time indications of economic impact of aircraft operations to an aircraft operator. The system and method allow the aircraft operator to reduce economic impact during flight of the aircraft. Such an analysis and cue to the aircraft operator allows the operator to make real-time changes during flight to reduce damage of life-limited aircraft components, thereby reducing the economic impact of aircraft operation that is directly associated with maintenance and component replacement. The system and method can also include pre-flight and post-flight analysis methods for reduction of economic impact of flight operations.
Abstract translation: 本申请涉及一种用于向航空器操作者提供飞机操作的经济影响的实时指示的系统和方法。 该系统和方法允许飞行员在飞机飞行期间减少经济影响。 对航空器操作者的这种分析和提示允许操作者在飞行中进行实时改变以减少对生命限制的飞行器部件的损坏，从而减少与维护和部件更换直接相关的飞机操作的经济影响。 该系统和方法还可以包括飞行前和飞行后分析方法，以减少飞行运行的经济影响。
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