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公开(公告)号：US10860037B2
公开(公告)日：2020-12-08
申请号：US15991369
申请日：2018-05-29
Applicant: Textron Innovations Inc.
Inventor： Robert Earl Worsham, II , Luke Dafydd Gillett
Abstract: A method for controlling a rotorcraft, including receiving, by a fly-by-wire (FBW) system of the rotorcraft, a pilot input that initiates an automated descend-to-hover flight mode, scheduling, by the FBW system, a descend plane for bringing the rotorcraft to a hover, and autonomously descending and decelerating the rotorcraft according to the descend plane in response to determining that the rotorcraft has entered the automated descend-to-hover flight mode and until the rotorcraft reaches a hover or the rotorcraft exits the automated descend-to-hover flight mode.
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公开(公告)号：US20200277041A1
公开(公告)日：2020-09-03
申请号：US16877365
申请日：2020-05-18
Applicant: Textron Innovations Inc.
Inventor： Robert Earl Worsham II , Luke Dafydd Gillett
Abstract: A fly-by-wire system for a rotorcraft includes a computing device having control laws. The control laws are operable to engage a level-and-climb command in response to a switch of a pilot control assembly being selected. The level-and-climb command establishes a roll-neutral (“wings level”) attitude with the rotorcraft increasing altitude. The switch may be disposed on a collective control of the pilot control assembly (e.g., a button on a grip of the collective control). Selection of the switch may correspond to a button depress. The level-and-climb command may include a roll command and a collective pitch command. One or more control laws may be further operable to increase or decrease forward airspeed in response to pilot engagement of the level-and-climb command. The level-and-climb command may correspond to a go-around maneuver, an abort maneuver, or an extreme-attitude-recovery maneuver to be performed by the rotorcraft.
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公开(公告)号：US11599111B2
公开(公告)日：2023-03-07
申请号：US16830463
申请日：2020-03-26
Applicant: Textron Innovations Inc.
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：US11117653B2
公开(公告)日：2021-09-14
申请号：US15983752
申请日：2018-05-18
Applicant: Textron Innovations Inc.
Inventor： Charles Eric Covington , Bradley Don Linton , Thomas Earl Johnson, Jr. , Luke Dafydd Gillett , Robert Earl Worsham, II , Jillian Samantha Alfred
Abstract: An rotorcraft including a pilot control, a pilot control position sensor connected to the pilot control and operable to generate a position signal indicating a position of the pilot control, a flight control computer (FCC) in signal communication with the pilot control position sensor and operable to provide a tactile cue in the pilot control in response to the position signal indicating the position of the pilot control exceeds a threshold associated with an operating limit, and further operable to determine a tactile cueing value for the tactile cue according to a relationship between the position of the pilot control and the threshold, and generate a cue control signal according to the tactile cueing value, and a tactile cue element connected to the pilot control and in signal communication with the FCC and operable to control action of the pilot control in response to the cue control signal.
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公开(公告)号：US10802482B2
公开(公告)日：2020-10-13
申请号：US15443493
申请日：2017-02-27
Applicant: Textron Innovations Inc.
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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Patent Agency Ranking
公开(公告)号：US20200285232A1
公开(公告)日：2020-09-10
申请号：US16830463
申请日：2020-03-26
Applicant: Textron Innovations Inc.
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：US10703470B2
公开(公告)日：2020-07-07
申请号：US15892558
申请日：2018-02-09
Applicant: Textron Innovations Inc.
Inventor： Luke Dafydd Gillett
Abstract: A rotorcraft including a main rotor, flight controls connected to the main rotor, a plurality of engines connected to the main rotor and operable to drive the main rotor, a main rotor revolutions per minute (RPM) sensor, and a monitoring system operable to determine an engine failure of the plurality of engines. The monitoring system is further operable to engage an automated autorotation entry assist process in response to at least determining the engine failure and according to the measured main rotor RPM, where the automated autorotation entry assist process comprises the monitoring system generating one or more rotor RPM related commands according to at least a target main rotor RPM and the measured main rotor RPM, where the automated autorotation entry assist process further comprises controlling the one or more flight controls according to the one or more rotor RPM related commands.
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公开(公告)号：US11472535B2
公开(公告)日：2022-10-18
申请号：US16877365
申请日：2020-05-18
Applicant: Textron Innovations Inc.
Inventor： Robert Earl Worsham, II , Luke Dafydd Gillett
Abstract: A fly-by-wire system for a rotorcraft includes a computing device having control laws. The control laws are operable to engage a level-and-climb command in response to a switch of a pilot control assembly being selected. The level-and-climb command establishes a roll-neutral (“wings level”) attitude with the rotorcraft increasing altitude. The switch may be disposed on a collective control of the pilot control assembly (e.g., a button on a grip of the collective control). Selection of the switch may correspond to a button depress. The level-and-climb command may include a roll command and a collective pitch command. One or more control laws may be further operable to increase or decrease forward airspeed in response to pilot engagement of the level-and-climb command. The level-and-climb command may correspond to a go-around maneuver, an abort maneuver, or an extreme-attitude-recovery maneuver to be performed by the rotorcraft.
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公开(公告)号：US11312480B2
公开(公告)日：2022-04-26
申请号：US16416508
申请日：2019-05-20
Applicant: Textron Innovations Inc.
Inventor： Luke Dafydd Gillett , Sung Kyun Kim , Robert Earl Worsham, II
IPC: B64C13/50 , B64C13/04 , B64C27/605 , B64C27/78 , B64C27/82 , B64C27/08 , B64D35/04 , B64C27/72 , B64C39/02
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：US20200290733A1
公开(公告)日：2020-09-17
申请号：US16892020
申请日：2020-06-03
Applicant: Textron Innovations Inc.
Inventor： Luke Dafydd Gillett
Abstract: A rotorcraft including a main rotor, flight controls connected to the main rotor the main rotor, a plurality of engines connected to the main rotor and operable to drive the main rotor, a main rotor revolutions per minute (RPM) sensor, and a monitoring system operable to determine an engine failure of the plurality of engines. The monitoring system is further operable to engage an automated autorotation entry assist process in response to at least determining the engine failure and according to the measured main rotor RPM, where the automated autorotation entry assist process comprises the monitoring system generating one or more rotor RPM related commands according to at least a target main rotor RPM and the measured main rotor RPM, where the automated autorotation entry assist process further comprises controlling the one or more flight controls according to the one or more rotor RPM related commands.
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