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公开(公告)号：US20190351995A1
公开(公告)日：2019-11-21
申请号：US15981525
申请日：2018-05-16
Applicant: Bell Helicopter Textron Inc.
Inventor： Jillian Samantha Alfred , Christopher M. Bothwell
Abstract: In an embodiment, a rotorcraft includes: a rotor system; a sensor; a flight control device; and a flight control computer (FCC) coupled to the rotor system, the sensor, and the flight control device, the FCC configured to: determine a rotation speed of the rotor system; select a first aeroservoelasticity filter configuration from a plurality of aeroservoelasticity filter configurations according to the rotation speed of the rotor system, the aeroservoelasticity filter configurations being predetermined configurations corresponding to different rotation speeds of the rotor system; receive a signal from the sensor; filter the signal according to the first aeroservoelasticity filter configuration; and adjust the flight control device according to the filtered signal.
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公开(公告)号：US10336438B2
公开(公告)日：2019-07-02
申请号：US15688164
申请日：2017-08-28
Applicant: Bell Helicopter Textron Inc.
Inventor： Sung K. Kim , Christopher M. Bothwell , Robert Lee Fortenbaugh
Abstract: A flight control system includes a pilot control module configured to receive commands from a pilot, a flight control module operable to transmit an instruction to change at least one operating condition of an aircraft, and a flight control computer in communication between the flight control module and the pilot control module. The flight control computer is configured to receive a pilot command to change a first flight characteristic, wherein changing the first flight characteristic would result in an expected change to a second flight characteristic. The flight control computer may instruct the flight control module to transmit an instruction to change a first operating condition of the aircraft and instruct the flight control module to transmit an instruction to change a second operating condition of the aircraft to at least partially offset the expected change to the second flight characteristic.
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公开(公告)号：US20190084690A1
公开(公告)日：2019-03-21
申请号：US15708767
申请日：2017-09-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher M. Bothwell , Robert Earl Worsham, II , Sung Kyun Kim , Brandon Jeffrey Thomas
Abstract: In an embodiment, a rotorcraft includes: tail rotor blades; a tail rotor actuator coupled to the tail rotor blades such that the pitch of the tail rotor blades varies according to a current extension of the tail rotor actuator; pilot flight controls electrically coupled to the tail rotor actuator; and a flight control computer electrically coupled to the tail rotor actuator and the pilot flight controls, the flight control computer configured to: determine the current extension of the tail rotor actuator; determine whether the current extension of the tail rotor actuator is within a margin of a maximum extension of the tail rotor actuator; and indicate a first warning to a pilot in response to the current extension of the tail rotor actuator being within the margin of the maximum extension of the tail rotor actuator.
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公开(公告)号：US20190161203A1
公开(公告)日：2019-05-30
申请号：US15978646
申请日：2018-05-14
Applicant: Bell Helicopter Textron Inc.
Inventor： Robert Earl Worsham, II , Morganne Cody Klein , Christopher M. Bothwell , Luke Dafydd Gillett , Jillian Samantha Alfred , Sung Kyun Kim , Stephanie Baynham , Troy Caudill
Abstract: In an embodiment, a method of indicating flight modes of a rotorcraft includes: detecting a change in flight mode of the rotorcraft from a previous flight mode to an active flight mode, the active flight mode and the previous flight mode each being from one of a first subset or a second subset of a plurality of flight modes; determining whether the active flight mode and the previous flight mode are from different subsets of the plurality of flight modes; and updating one or more flight mode indicators on an instrument panel of the rotorcraft in response to the active flight mode and the previous flight mode being from different subsets of the plurality of flight modes.
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公开(公告)号：US09886039B2
公开(公告)日：2018-02-06
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: G05D1/08 , G05D1/06 , B64C27/10 , B64C27/16 , B64C27/605
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.
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Patent Agency Ranking
公开(公告)号：US20180001995A1
公开(公告)日：2018-01-04
申请号：US15688164
申请日：2017-08-28
Applicant: Bell Helicopter Textron Inc.
Inventor： Sung K. Kim , Christopher M. Bothwell , Robert Lee Fortenbaugh
CPC classification number: B64C13/0421 , B64C13/04 , B64C13/12 , B64C13/503 , B64D43/00
Abstract: A flight control system includes a pilot control module configured to receive commands from a pilot, a flight control module operable to transmit an instruction to change at least one operating condition of an aircraft, and a flight control computer in communication between the flight control module and the pilot control module. The flight control computer is configured to receive a pilot command to change a first flight characteristic, wherein changing the first flight characteristic would result in an expected change to a second flight characteristic. The flight control computer may instruct the flight control module to transmit an instruction to change a first operating condition of the aircraft and instruct the flight control module to transmit an instruction to change a second operating condition of the aircraft to at least partially offset the expected change to the second flight characteristic.
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公开(公告)号：US09399511B2
公开(公告)日：2016-07-26
申请号：US14577373
申请日：2014-12-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Sung K. Kim , Christopher M. Bothwell , Robert Lee Fortenbaugh
CPC classification number: B64C13/503 , B64C13/04 , B64C13/12 , B64D43/00
Abstract: According to one embodiment, a flight control system includes a pilot control module configured to receive commands from a pilot, a flight control module operable to transmit an instruction to change at least one operating condition of an aircraft, and a flight control computer in communication between the flight control module and the pilot control module. The flight control computer is configured to receive a pilot command to change a first flight characteristic, wherein changing the first flight characteristic would result in an expected change to a second flight characteristic. The flight control computer may instruct the flight control module to transmit an instruction to change a first operating condition of the aircraft and instruct the flight control module to transmit an instruction to change a second operating condition of the aircraft to at least partially offset the expected change to the second flight characteristic.
Abstract translation: 根据一个实施例，飞行控制系统包括导频控制模块，其被配置为从飞行员接收命令，飞行控制模块可操作以发送改变飞行器的至少一个操作条件的指令，以及飞行控制计算机之间的通信 飞行控制模块和飞行员控制模块。 飞行控制计算机被配置为接收用于改变第一飞行特性的驾驶员命令，其中改变第一飞行特性将导致对第二飞行特性的预期变化。 飞行控制计算机可以指示飞行控制模块发送改变飞行器的第一操作状态的指令，并且指示飞行控制模块发送改变飞行器的第二操作状态的指令以至少部分地偏移预期的改变 到第二个飞行特征。
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公开(公告)号：US10315779B2
公开(公告)日：2019-06-11
申请号：US15708767
申请日：2017-09-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher M. Bothwell , Robert Earl Worsham, II , Sung Kyun Kim , Brandon Jeffrey Thomas
Abstract: In an embodiment, a rotorcraft includes: tail rotor blades; a tail rotor actuator coupled to the tail rotor blades such that the pitch of the tail rotor blades varies according to a current extension of the tail rotor actuator; pilot flight controls electrically coupled to the tail rotor actuator; and a flight control computer electrically coupled to the tail rotor actuator and the pilot flight controls, the flight control computer configured to: determine the current extension of the tail rotor actuator; determine whether the current extension of the tail rotor actuator is within a margin of a maximum extension of the tail rotor actuator; and indicate a first warning to a pilot in response to the current extension of the tail rotor actuator being within the margin of the maximum extension of the tail rotor actuator.
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公开(公告)号：US09771145B2
公开(公告)日：2017-09-26
申请号：US15212689
申请日：2016-07-18
Applicant: Bell Helicopter Textron Inc.
Inventor： Sung K. Kim , Christopher M. Bothwell , Robert Lee Fortenbaugh
CPC classification number: B64C13/503 , B64C13/04 , B64C13/12 , B64D43/00
Abstract: According to one embodiment, a flight control system includes a pilot control assembly and a flight control computer. The pilot control assembly can receive commands from a pilot. The flight control computer can receive, from the pilot control assembly, a pilot command to change a first flight characteristic, wherein changing the first flight characteristic would result in an expected change to a second flight characteristic. The flight control computer can instruct, in response to the received pilot command, the flight control system to change a first operating condition of the flight control system based on an inherently-coupled relationship between the first flight characteristic and the second flight characteristic. The flight control computer can instruct, in response to the expected change to the second flight characteristic, the flight control system to change a second operating condition of the flight control system.
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公开(公告)号：US20170137113A1
公开(公告)日：2017-05-18
申请号：US15212689
申请日：2016-07-18
Applicant: Bell Helicopter Textron Inc.
Inventor： Sung K. Kim , Christopher M. Bothwell , Robert Lee Fortenbaugh
CPC classification number: B64C13/503 , B64C13/04 , B64C13/12 , B64D43/00
Abstract: According to one embodiment, a flight control system includes a pilot control assembly and a flight control computer. The pilot control assembly can receive commands from a pilot. The flight control computer can receive, from the pilot control assembly, a pilot command to change a first flight characteristic, wherein changing the first flight characteristic would result in an expected change to a second flight characteristic. The flight control computer can instruct, in response to the received pilot command, the flight control system to change a first operating condition of the flight control system based on an inherently-coupled relationship between the first flight characteristic and the second flight characteristic. The flight control computer can instruct, in response to the expected change to the second flight characteristic, the flight control system to change a second operating condition of the flight control system.
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