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公开(公告)号：US20140361118A1
公开(公告)日：2014-12-11
申请号：US14297114
申请日：2014-06-05
Applicant: Bell Helicopter Textron Inc.
Inventor： Joseph M. Schaeffer , Jignesh Patel , Eric O'Neill
CPC classification number: B64C27/04 , G05D1/0833 , G05D1/0858
Abstract: A method of limiting vertical axis augmentation in a rotorcraft, the method comprising: measuring a torque with a sensor; deriving a comparison of the torque to a lower torque limit, using a computer processor; and adjusting a vertical axis control command based upon the comparison of the torque to the lower torque limit.
Abstract translation: 一种在旋翼航空器中限制垂直轴增大的方法，所述方法包括：用传感器测量扭矩; 使用计算机处理器得到扭矩与较低扭矩极限的比较; 以及基于所述转矩与所述下转矩极限的比较来调整垂直轴控制指令。
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12.发明授权System and method of protecting an engine and other aircraft components from damage that may otherwise occur from a fuel control unit failure 有权保护发动机和其他飞机部件免受燃料控制单元故障可能发生的损坏的系统和方法公开(公告)号：US08825342B2
公开(公告)日：2014-09-02
申请号：US13667441
申请日：2012-11-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Joseph M. Schaeffer , Areian A. Kouros , Christopher Cawelti , Curtis L. Moore , Michael D. Trantham
CPC classification number: F01D17/06 , F01D21/02 , F02C9/28 , F02C9/46 , F05D2270/021
Abstract: The system for mitigating an overspeeding condition of a turbine engine can include a sensor for measuring an actual speed of a gas generator turbine of the turbine engine and a processor for deriving a delta, the delta being a comparison between the actual speed of the gas generator turbine and a predicted gas generator turbine speed. The system is configured for detecting the overspeeding condition when delta is higher than a predetermined threshold. A method of detecting an overspeeding condition during operation of a turbine engine can include measuring an actual speed of a gas generator turbine, then evaluating a delta between the actual speed of the gas generator turbine and a predicted speed of the gas generator turbine, then comparing the delta to a threshold value.
Abstract translation: 用于减轻涡轮发动机的超速状态的系统可以包括用于测量涡轮发动机的气体发生器涡轮机的实际速度的传感器和用于导出三角形的处理器，该三角形是气体发生器的实际速度之间的比较 涡轮机和预测的气体发生器涡轮机速度。 该系统被配置用于当delta高于预定阈值时检测超速状况。 在涡轮发动机运行期间检测超速状况的方法可以包括测量气体发生器涡轮机的实际速度，然后评估气体发生器涡轮机的实际速度与气体发生器涡轮机的预测速度之间的差值，然后比较 delta到阈值。
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13.发明申请公开(公告)号：US20140129111A1
公开(公告)日：2014-05-08
申请号：US13667441
申请日：2012-11-02
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Joseph M. Schaeffer , Areian A. Kouros , Christopher Cawelti , Curtis L. Moore , Michael D. Trantham
CPC classification number: F01D17/06 , F01D21/02 , F02C9/28 , F02C9/46 , F05D2270/021
Abstract: The system for mitigating an overspeeding condition of a turbine engine can include a sensor for measuring an actual speed of a gas generator turbine of the turbine engine and a processor for deriving a delta, the delta being a comparison between the actual speed of the gas generator turbine and a predicted gas generator turbine speed. The system is configured for detecting the overspeeding condition when delta is higher than a predetermined threshold. A method of detecting an overspeeding condition during operation of a turbine engine can include measuring an actual speed of a gas generator turbine, then evaluating a delta between the actual speed of the gas generator turbine and a predicted speed of the gas generator turbine, then comparing the delta to a threshold value.
Abstract translation: 用于减轻涡轮发动机的超速状态的系统可以包括用于测量涡轮发动机的气体发生器涡轮机的实际速度的传感器和用于导出三角形的处理器，该三角形是气体发生器的实际速度之间的比较 涡轮机和预测的气体发生器涡轮机速度。 该系统被配置用于当delta高于预定阈值时检测超速状况。 在涡轮发动机运行期间检测超速状况的方法可以包括测量气体发生器涡轮机的实际速度，然后评估气体发生器涡轮机的实际速度与气体发生器涡轮机的预测速度之间的差值，然后比较 delta到阈值。
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Patent Agency Ranking
公开(公告)号：US10392105B2
公开(公告)日：2019-08-27
申请号：US15642279
申请日：2017-07-05
Applicant: Bell Helicopter Textron Inc.
Inventor： Joseph M. Schaeffer , Jignesh Patel , Eric O'Neill
Abstract: A method of assisting in rotor speed control in a rotorcraft can include measuring a rotor speed with a sensor; detecting a droop in the rotor speed beyond a lower droop limit; and commanding a decrease in collective in response to the rotor speed drooping beyond the lower droop limit. A system of assisting in rotor speed control in a rotorcraft, the system can include: a computer having a control law, the control law operable to generate a decrease collective command to an actuator in response to a rotor speed decreasing below a lower droop limit; wherein the lower droop limit is below a normal lower rotor speed range.
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公开(公告)号：US10059439B2
公开(公告)日：2018-08-28
申请号：US14800346
申请日：2015-07-15
Applicant: Bell Helicopter Textron Inc.
Inventor： Luke D. Gillett , Brandon J. Thomas , Joseph M. Schaeffer
CPC classification number: B64C27/56 , B64C13/16 , B64C13/345 , B64C13/44 , B64C13/46 , B64C13/507 , B64C27/57 , B64D31/04 , G05D1/0072 , G05D1/0858
Abstract: According to one embodiment, a pilot assistance system includes a trim assembly and a trim assembly control system. The trim assembly is operable to communicate with a pilot control device and operable to apply a force against the pilot control device in resistance of a command received from a pilot via the pilot control device. The trim assembly control system is in communication with the trim assembly, configured to identify a first pilot control device position relative to a reference pilot control device position, and configured to instruct the trim assembly to apply a cueing force against the pilot control device if the pilot control device is positioned proximate to the first pilot control device position.
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公开(公告)号：US09821908B2
公开(公告)日：2017-11-21
申请号：US14297136
申请日：2014-06-05
Applicant: Bell Helicopter Textron Inc.
Inventor： Joseph M. Schaeffer , Jignesh Patel , Eric O'Neill
CPC classification number: B64C27/57 , B64C27/46 , G05D1/0858
Abstract: A method of assisting in rotor speed control in a rotorcraft can include measuring a rotor speed with a sensor; detecting a droop in the rotor speed beyond a lower droop limit; and commanding a decrease in collective in response to the rotor speed drooping beyond the lower droop limit. A system of assisting in rotor speed control in a rotorcraft, the system can include: a computer having a control law, the control law operable to generate a decrease collective command to an actuator in response to a rotor speed decreasing below a lower droop limit; wherein the lower droop limit is below a normal lower rotor speed range.
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公开(公告)号：US20170017241A1
公开(公告)日：2017-01-19
申请号：US14800346
申请日：2015-07-15
Applicant: Bell Helicopter Textron Inc.
Inventor： Luke D. Gillett, JR. , Brandon J. Thomas , Joseph M. Schaeffer
CPC classification number: B64C27/56 , B64C13/16 , B64C13/44 , B64C13/46 , B64C27/57 , B64D31/04 , G05D1/0072 , G05D1/0858
Abstract: According to one embodiment, a pilot assistance system includes a trim assembly and a trim assembly control system. The trim assembly is operable to communicate with a pilot control device and operable to apply a force against the pilot control device in resistance of a command received from a pilot via the pilot control device. The trim assembly control system is in communication with the trim assembly, configured to identify a first pilot control device position relative to a reference pilot control device position, and configured to instruct the trim assembly to apply a cueing force against the pilot control device if the pilot control device is positioned proximate to the first pilot control device position.
Abstract translation: 根据一个实施例，先导辅助系统包括修剪组件和修剪组件控制系统。 修剪组件可操作以与先导控制装置通信，并且可操作以通过先导控制装置对从先导控制装置接收到的命令的电阻施加对先导控制装置的力。 修剪组件控制系统与修剪组件连通，其被配置为相对于参考先导控制装置位置识别第一先导控制装置位置，并且被配置为指示装饰组件对先导控制装置施加提示力，如果 先导控制装置位于第一先导控制装置位置附近。
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18.发明申请SYSTEM AND METHOD FOR AVOIDING INADVERTANT ENTRY INTO AN UNSAFE VERTICAL DESCENT SPEED REGION FOR ROTORCRAFT 审中-公开避免进入不安全垂直下降速度区域的系统和方法公开(公告)号：US20150232176A1
公开(公告)日：2015-08-20
申请号：US14623382
申请日：2015-02-16
Applicant: Bell Helicopter Textron Inc.
Inventor： Luke D. Gillett , Joseph M. Schaeffer , Christopher M. Bothwell , Robert Worsham , Jillian Alfred , Sung Kim
IPC: B64C27/605 , B64C27/16 , B64C27/10
CPC classification number: G05D1/0607 , B64C27/10 , B64C27/16 , B64C27/605
Abstract: A flight control system having a control law, the control law operable to generate a modified pitch command, the modified pitch command representing a greater amount of collective pitch compared to an amount of collective pitch generated by a first pitch command, the modified pitch command being generated because a vertical descent speed of the rotorcraft at a given forward airspeed is greater than a threshold. A method of avoiding entry into an undesired vertical descent speed region during operation of a rotorcraft, including measuring a forward airspeed; evaluating a vertical descent of the rotorcraft; and generating a modified collective pitch command in respond to a first collective pitch command having a collective pitch value that would cause the rotorcraft to experience a vertical descent rate greater than a threshold value at the forward airspeed of the rotorcraft.
Abstract translation: 一种具有控制规则的飞行控制系统，所述控制规则可操作以产生修正的俯仰指令，所述修正的俯仰指令表示与由第一俯仰指令产生的总音调量相比较大的总音调， 这是因为在给定的前进空速下旋翼飞机的垂直下降速度大于阈值。 一种在旋翼航空器操作期间避免进入不期望的垂直下降速度区域的方法，包括测量前进空速; 评估旋翼航空器的垂直下降; 以及响应于具有共同音调值的第一集体音调命令来产生修正的集体音调命令，所述集体音调值将导致旋翼航空器在所述旋翼航空器的前进空速下经历大于阈值的垂直下降速率。
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