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公开(公告)号：US20190004542A1
公开(公告)日：2019-01-03
申请号：US16108479
申请日：2018-08-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Sung Kyun Kim
Abstract: In accordance with an embodiment, a method of operating a rotorcraft includes transitioning from a first mode to a second mode when a velocity of the rotorcraft exceeds a first velocity threshold. Transitioning between the first and second modes includes fading out a gain of a dynamic controller over a first period of time, and decreasing a value of an integrator of the dynamic controller over a second period of time.
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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：US20180251207A1
公开(公告)日：2018-09-06
申请号：US15446911
申请日：2017-03-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Sung Kyun Kim
CPC classification number: G05D1/0858 , B64C13/0421 , B64C13/503 , B64C13/506 , B64C13/507 , B64C27/04
Abstract: In accordance with an embodiment, a method of operating a rotorcraft includes transitioning from a first mode to a second mode when a velocity of the rotorcraft exceeds a first velocity threshold. Transitioning between the first and second modes includes fading out a gain of a dynamic controller over a first period of time, and decreasing a value of an integrator of the dynamic controller over a second period of time. In the first mode, the translational speed of the rotorcraft is determined based on a pilot stick signal, and in the second mode, an output of an attitude rate controller is proportional to an amplitude of the pilot stick signal.
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公开(公告)号：US20200023941A1
公开(公告)日：2020-01-23
申请号：US16416508
申请日：2019-05-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Luke Dafydd Gillett , Sung Kyun Kim , Robert Earl Worsham, II
Abstract: In an embodiment, a rotorcraft includes: a flight control computer configured to: receive a first sensor signal from a first aircraft sensor of the rotorcraft; receive a second sensor signal from a second aircraft sensor of the rotorcraft, the second aircraft sensor being different from the first aircraft sensor; combine the first sensor signal and the second sensor signal with a complementary filter to determine an estimated vertical speed of the rotorcraft; adjust flight control devices of the rotorcraft according to the estimated vertical speed of the rotorcraft, thereby changing flight characteristics of the rotorcraft; and reset the complementary filter in response to detecting the rotorcraft is grounded.
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公开(公告)号：US10386858B2
公开(公告)日：2019-08-20
申请号：US15594393
申请日：2017-05-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Mike Bothwell , Jillian Samantha Alfred , Sung Kyun Kim , Marko Vuga , Matthew Hendricks , Mark Wasikowski , Thomas Parham , Michael Reaugh Smith
Abstract: In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes receiving a measured yaw rate from a yaw rate sensor or a measured lateral acceleration from a lateral acceleration sensor of the rotorcraft, filtering the measured yaw rate or the measured lateral acceleration using a filter to form a filtered measured yaw rate or a filtered measured lateral acceleration, and regulating a yaw rate or a lateral acceleration of the rotorcraft based on the measured yaw rate or the measured lateral acceleration. The filter includes a bandpass characteristic or a notch characteristic, and the filtering is configured to reduce lateral vibrations caused by airflow in a tail section of the rotorcraft.
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Patent Agency Ranking
公开(公告)号：US10261517B2
公开(公告)日：2019-04-16
申请号：US15484994
申请日：2017-04-11
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Mike Bothwell , Sung Kyun Kim , Jillian Samantha Alfred , Robert Earl Worsham, II , Luke Dafydd Gillett , Morganne Cody Klein
Abstract: A rotorcraft including a flight control computer (FCC) providing a vertical speed hold for the rotorcraft, a collective control, and a collective trim motor connected to the collective control. The collective trim motor moves the collective control according to a collective set command generated by the FCC according to a target vertical speed and when the FCC determines the collective control is in-detent. A collective position sensor is connected to the collective control. The collective position sensor generates, and sends to the FCC, a collective position signal indicating the position of the collective control. A flight control device controls a flight parameter of the rotorcraft in response to a flight control device control signal received from the FCC. The FCC generates the flight control device control signal according to the collective position signal, and sends the flight control device control signal to a flight control device.
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公开(公告)号：US20180329430A1
公开(公告)日：2018-11-15
申请号：US15594393
申请日：2017-05-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Mike Bothwell , Jillian Samantha Alfred , Sung Kyun Kim , Marko Vuga , Matthew Hendricks , Mark Wasikowski , Thomas Parham , Michael Reaugh Smith
CPC classification number: G05D1/0858 , B64C27/001 , B64C27/04 , B64C27/57 , B64C27/82 , G05D1/0825
Abstract: In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes receiving a measured yaw rate from a yaw rate sensor or a measured lateral acceleration from a lateral acceleration sensor of the rotorcraft, filtering the measured yaw rate or the measured lateral acceleration using a filter to form a filtered measured yaw rate or a filtered measured lateral acceleration, and regulating a yaw rate or a lateral acceleration of the rotorcraft based on the measured yaw rate or the measured lateral acceleration. The filter includes a bandpass characteristic or a notch characteristic, and the filtering is configured to reduce lateral vibrations caused by airflow in a tail section of the rotorcraft
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公开(公告)号：US20200216165A1
公开(公告)日：2020-07-09
申请号：US16238889
申请日：2019-01-03
Applicant: Bell Helicopter Textron Inc.
IPC: B64C13/16 , B64C27/605 , B64C13/04 , G05D1/08
Abstract: In an embodiment, a method includes: obtaining a first signal from a first sensor of a rotorcraft, the first signal indicating measured angular velocity around a first axis of the rotorcraft; filtering the first signal with a lag compensator to estimate angular position around the first axis of the rotorcraft; and adjusting flight control devices of the rotorcraft according to the estimated angular position and the measured angular velocity around the first axis of the rotorcraft, thereby changing flight characteristics of the rotorcraft around the first axis of the rotorcraft.
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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：US20190155282A1
公开(公告)日：2019-05-23
申请号：US16253037
申请日：2019-01-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Sung Kyun Kim
Abstract: In accordance with an embodiment, a method of operating an aircraft includes operating the aircraft in a first mode including determining an attitude based on a pilot stick signal, where a translational speed or an attitude of the aircraft is proportional to an amplitude of the pilot stick signal in the first mode; transitioning from the first mode to a second mode when a velocity of the aircraft exceeds a first velocity threshold; and operating the aircraft in the second mode where the output of the rate controller is proportional to the amplitude of the pilot stick signal.
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