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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：US10101749B1
公开(公告)日：2018-10-16
申请号：US15465417
申请日：2017-03-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Luke Dafydd Gillett , Robert Earl Worsham, II
IPC: G01P5/00 , B64C27/26 , G01P5/16 , G05D1/10 , B64C27/06 , B64C27/82 , B64D43/02 , B64C17/06 , G01C21/18 , B64C13/50
Abstract: A rotorcraft includes airspeed sensors, inertial sensors, and a flight control computer (FCC) operable to provide a longitudinal control for the rotorcraft. The FCC receives a first indication of longitudinal airspeed from the airspeed sensors and receives a first indication of longitudinal acceleration from the inertial sensors. The FCC generates a filtered indication of longitudinal airspeed from the first indication of longitudinal airspeed and generates a scaled and filtered indication of longitudinal acceleration from the first indication of longitudinal acceleration. The FCC combines the filtered indication of longitudinal airspeed with the scaled and filtered indication of longitudinal acceleration to generate a determined longitudinal airspeed. The FCC generates a flight control signal to control operation of the rotorcraft, the flight control signal based on the determined longitudinal airspeed.
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公开(公告)号：US20180275684A1
公开(公告)日：2018-09-27
申请号：US15465417
申请日：2017-03-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Luke Dafydd Gillett , Robert Earl Worsham II
Abstract: A rotorcraft includes airspeed sensors, inertial sensors, and a flight control computer (FCC) operable to provide a longitudinal control for the rotorcraft. The FCC receives a first indication of longitudinal airspeed from the airspeed sensors and receives a first indication of longitudinal acceleration from the inertial sensors. The FCC generates a filtered indication of longitudinal airspeed from the first indication of longitudinal airspeed and generates a scaled and filtered indication of longitudinal acceleration from the first indication of longitudinal acceleration. The FCC combines the filtered indication of longitudinal airspeed with the scaled and filtered indication of longitudinal acceleration to generate a determined longitudinal airspeed. The FCC generates a flight control signal to control operation of the rotorcraft, the flight control signal based on the determined longitudinal airspeed.
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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：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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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：US20190056753A1
公开(公告)日：2019-02-21
申请号：US15961439
申请日：2018-04-24
Applicant: Bell Helicopter Textron Inc.
Inventor： Robert Earl Worsham, II , Troy Caudill , Luke Dafydd Gillett
Abstract: An embodiment rotorcraft includes a rotor system including a plurality of blades; a control assembly operable to receive commands from a pilot; a flight control system (FCS), the flight control system operable to control flight of the rotorcraft by changing an operating condition of the rotor system; and a flight management system (FMS) in signal communication with the control assembly and the FCS. The FMS is operable to receive a target location and a plurality of approach parameters from the control assembly; generate a plurality waypoints between a current location of the rotorcraft and a missed approach point (MAP) based on the target location and the plurality of approach parameters; receive a command to engage in an approach maneuver from the control assembly; and in response to the command to engage in the approach maneuver, instruct the FCS to fly to the MAP.
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公开(公告)号：US10093415B1
公开(公告)日：2018-10-09
申请号：US15464084
申请日：2017-03-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Robert Lee Fortenbaugh , Jillian Samantha Alfred , Luke Dafydd Gillett
Abstract: In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes operating the rotorcraft in a heading control mode that includes activating a yaw channel path of a heading controller and deactivating a roll channel path of the heading controller when a speed of the rotorcraft is less than a first speed threshold or a heading error is less than a heading error threshold, and activating the roll channel path of the heading controller and deactivating the yaw channel path of the heading controller when the speed of the rotorcraft is greater than a second speed threshold and the heading error is not less than the heading error threshold.
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公开(公告)号：US20180246510A1
公开(公告)日：2018-08-30
申请号：US15443493
申请日：2017-02-27
Applicant: Bell Helicopter Textron Inc.
CPC classification number: G05D1/0055 , B64C13/10 , B64C13/343 , B64C13/345 , B64C13/507 , B64C27/57 , F02C9/28 , F02C9/58 , F05D2220/329 , F05D2270/021
Abstract: A flight control computer (FCC) for a rotorcraft includes a processor and a non-transitory computer-readable storage medium storing a program to be executed by the processor, with the program including instructions for providing main rotor overspeed protection. The instructions for providing the main rotor overspeed protection include instructions for monitoring sensor signals indicating a main rotor RPM, determining a target operating parameter, determining one or more flight parameters in response to a relationship between the main rotor RPM and the target operating parameter indicating a main rotor overspeed condition. Determining the one or more flight parameters includes determining a setting for a flight control device of the rotorcraft that changes the main rotor RPM, controlling positioning of a pilot control according to the flight parameters, and controlling the flight control device of the rotorcraft according to positioning of the pilot control.
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公开(公告)号：US20180244369A1
公开(公告)日：2018-08-30
申请号：US15443826
申请日：2017-02-27
Applicant: Bell Helicopter Textron Inc.
CPC classification number: B64C13/503 , B64C13/18 , F02C9/44 , G05D1/0061 , G05D1/085 , G05D1/0858
Abstract: A fly-by-wire system for a rotorcraft includes a computing device having control laws. The control laws are operable to engage a roll command or a yaw command in response to deflection of a beep switch of a pilot control assembly, wherein a roll angle for the roll command or a yaw rate for the yaw command is determined based on forward airspeed of the rotorcraft. The beep switch may be disposed on a collective control of the pilot control assembly. The control laws are further operable to disengage the roll command or the yaw command in response to the beep switch being returned from a deflected position to a neutral position. In representative aspects, the roll angle or the yaw rate may correspond to a standard rate turn (e.g., 3° per second).
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