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公开(公告)号：US20220372921A1
公开(公告)日：2022-11-24
申请号：US17749686
申请日：2022-05-20
Applicant: Textron Aviation Inc.
Inventor： Stephen M. Eddy
Abstract: An automatic aircraft powerplant control system includes a throttle servo for adjusting a throttle valve via a throttle control linkage. A throttle control lever provides a user input to the throttle servo, and a throttle controller controls the throttle servo for controlling a throttle valve. A dual-redundant propellor servo drive provides propellor control, and a dual-redundant mixture servo drive controls an air-fuel mixture. A first processor and a second processor are communicatively coupled with the dual-redundant propellor servo drive and the dual-redundant mixture servo drive and with each other to provide dual-redundant propellor and mixture control. The throttle control lever provides a single lever for pilot control of aircraft power, and the throttle control configuration is compatible with an auto-land capability.
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公开(公告)号：US20180297691A1
公开(公告)日：2018-10-18
申请号：US15949232
申请日：2018-04-10
Applicant: Textron Aviation Inc.
Inventor： Stephen M. Eddy , Jeremy Phillip Taylor , Steven G. Hagerott , Philippe A. Ciholas
Abstract: An interconnected flight controller for an aircraft includes a mechanical linkage connecting a pilot interface with a copilot interface. When an input is provided to either of the pilot or copilot interfaces, coordinated motion is provided between them of a proportional magnitude and direction. A mechanical-disconnect element within the mechanical linkage is adapted to actuate mechanical decoupling between the pilot interface and the copilot interface. One or more sensors is coupled to the mechanical linkage to sense inputs and communicate the inputs to a fly-by-wire flight controller. An autopilot servo is coupled to the mechanical linkage for providing autopilot control or feedback and a force-feedback subsystem is connected to the mechanical linkage to simulate and apply an opposing force of aircraft control surfaces to the pilot interface and the copilot interface.
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公开(公告)号：US20240409202A1
公开(公告)日：2024-12-12
申请号：US18737131
申请日：2024-06-07
Applicant: Textron Aviation Inc.
Inventor： Stephen M. Eddy , Steven G. Hagerott
Abstract: A flight control system includes a first and second operator input means configured to receive a mechanical input from an operator and are connected to an artificial feel system and at least one sensor. The system includes a flight control computer (FCC) in data communication with the sensor, wherein the FCC receives a signal from the sensor in response to an input by the operator. The flight control system has first and second servo controllers in data communication with first and second servos, respectively, and the FCC. The servos are connected to control surfaces that, when moved, cause the aircraft to change attitude. The flight control system also includes a third and a fourth servo controller, the third and fourth servo controllers being in communication with the FCC and a dual-lane servo operably connected to a third control surface that, when moved, causes the aircraft to change attitude.
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公开(公告)号：US10940939B2
公开(公告)日：2021-03-09
申请号：US16213305
申请日：2018-12-07
Applicant: Textron Aviation Inc.
Inventor： Stephen M. Eddy , Scott Stallard , Richard John Scillia
Abstract: A ground spoiler control architecture for aircraft includes a primary control architecture for providing a roll function, a speed-brake function and a ground spoiler function, and a secondary control architecture for providing the ground spoiler function in the event of a failure of the primary control architecture. The primary and secondary control architectures each include multiple actuators for actuating ground spoilers via independent and redundant signaling paths. Redundant hydraulic accumulators provide pressurized hydraulic fluid to the actuators. A ground spoiler control method includes determining whether the aircraft is on the ground based on the throttle-level-angle and whether any two wheels speeds are active or whether the main landing gear is weighted. Deployment of at least a portion of the ground spoiler panels occurs when and when the main landing gear is on the ground and the aircraft is in a landing configuration based on the throttle-level-angle.
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公开(公告)号：US11952956B2
公开(公告)日：2024-04-09
申请号：US17749659
申请日：2022-05-20
Applicant: Textron Aviation Inc.
Inventor： Stephen M. Eddy
CPC classification number: F02D9/02 , B64C11/30 , B64C11/305 , B64C11/44 , B64D31/04 , F02D11/04 , F02D29/02 , F02D2009/021 , F02D2009/0213 , F02D2009/0277
Abstract: An automatic aircraft powerplant control system includes a throttle servo for adjusting a throttle valve via a throttle control linkage. A throttle control lever provides a user input to the throttle servo, and a throttle controller controls the throttle servo for controlling a throttle valve. A propeller servo is provided for adjusting a propeller governor setting of an engine. A propeller control lever provides a user input to the propeller servo, and a propeller controller controls the propeller servo. A mixture control servo is configured for providing a mixture control output to the engine via a mixture control linkage for adjusting an air-fuel mixture. A mixture controller is configured for controlling the mixture control servo.
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Patent Agency Ranking
公开(公告)号：US20190176966A1
公开(公告)日：2019-06-13
申请号：US16213305
申请日：2018-12-07
Applicant: Textron Aviation Inc.
Inventor： Stephen M. Eddy , Scott Stallard , Richard John Scillia
Abstract: A ground spoiler control architecture for aircraft includes a primary control architecture for providing a roll function, a speed-brake function and a ground spoiler function, and a secondary control architecture for providing the ground spoiler function in the event of a failure of the primary control architecture. The primary and secondary control architectures each include multiple actuators for actuating ground spoilers via independent and redundant signaling paths. Redundant hydraulic accumulators provide pressurized hydraulic fluid to the actuators. A ground spoiler control method includes determining whether the aircraft is on the ground based on the throttle-level-angle and whether any two wheels speeds are active or whether the main landing gear is weighted. Deployment of at least a portion of the ground spoiler panels occurs when and when the main landing gear is on the ground and the aircraft is in a landing configuration based on the throttle-level-angle.
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公开(公告)号：US20180029690A1
公开(公告)日：2018-02-01
申请号：US15662773
申请日：2017-07-28
Applicant: Textron Aviation Inc.
Inventor： Steven G. Hagerott , Russell Peters , Stephen M. Eddy
CPC classification number: B64C9/00 , B64C5/02 , B64C5/10 , B64C9/14 , B64C13/40 , B64C2009/005 , B64D45/0005 , G05D1/0808
Abstract: An actuator hardover monitor for a control surface includes an actuator sensor for detecting an actuator position, a command model of an expected position of the actuator based on an input command, and a monitor to determine whether a difference between the actuator position and the expected position exceeds a threshold for a predetermined duration. A method of preventing a hardover event for a control surface includes commanding an actuator valve to a commanded position, determining continuously when the commanded position, or an actuator valve position, or a control-surface position, or a modeled actuator valve position exceeds a predetermined limit to provide an exceedance. The method may further include filtering a signal of the exceedance based on a time constant to provide a filtered exceedance, and switching to a backup control-surface actuator when the filtered exceedance exceeds the predetermined limit for a predetermined duration.
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公开(公告)号：US11828247B2
公开(公告)日：2023-11-28
申请号：US17749686
申请日：2022-05-20
Applicant: Textron Aviation Inc.
Inventor： Stephen M. Eddy
CPC classification number: F02D9/02 , B64C11/30 , B64D31/04 , F02D11/04 , F02D29/02 , F02D2009/021 , F02D2009/0277
Abstract: An automatic aircraft powerplant control system includes a throttle servo for adjusting a throttle valve via a throttle control linkage. A throttle control lever provides a user input to the throttle servo, and a throttle controller controls the throttle servo for controlling a throttle valve. A dual-redundant propellor servo drive provides propellor control, and a dual-redundant mixture servo drive controls an air-fuel mixture. A first processor and a second processor are communicatively coupled with the dual-redundant propellor servo drive and the dual-redundant mixture servo drive and with each other to provide dual-redundant propellor and mixture control. The throttle control lever provides a single lever for pilot control of aircraft power, and the throttle control configuration is compatible with an auto-land capability.
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公开(公告)号：US20220411088A1
公开(公告)日：2022-12-29
申请号：US17749659
申请日：2022-05-20
Applicant: Textron Aviation Inc.
Inventor： Stephen M. Eddy
Abstract: An automatic aircraft powerplant control system includes a throttle servo for adjusting a throttle valve via a throttle control linkage. A throttle control lever provides a user input to the throttle servo, and a throttle controller controls the throttle servo for controlling a throttle valve. A propeller servo is provided for adjusting a propeller governor setting of an engine. A propeller control lever provides a user input to the propeller servo, and a propeller controller controls the propeller servo. A mixture control servo is configured for providing a mixture control output to the engine via a mixture control linkage for adjusting an air-fuel mixture. A mixture controller is configured for controlling the mixture control servo.
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公开(公告)号：US20220372922A1
公开(公告)日：2022-11-24
申请号：US17749708
申请日：2022-05-20
Applicant: Textron Aviation Inc.
Inventor： Stephen M. Eddy
Abstract: An automatic aircraft powerplant control system includes a throttle servo for adjusting a throttle valve via a throttle control linkage. A throttle control lever provides a user input to the throttle servo, and a throttle controller controls the throttle servo for controlling a throttle valve. A propeller servo may be provided for adjusting a propeller governor setting of an engine. A propeller control lever provides a user input to the propeller servo, and a propeller controller controls the propeller servo. A full-authority digital engine control (FADEC) controller is used to automatically control mixing of fuel and air via a fuel-air mixture device. The FADEC controller may be used to automatically provide propeller control.
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