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公开(公告)号：US11085391B2
公开(公告)日：2021-08-10
申请号：US16707556
申请日：2019-12-09
Applicant: Textron Aviation Inc.
Inventor： Mark Sheridan Hunter , Philippe A. Ciholas , Ronald J. Parker
Abstract: Disclosed is a throttle quadrant arrangement utilizing a single throttle lever. The single lever is independently mechanically connected to three Rotary Variable Differential Transformers (RVDTs). Failure points are engineered into the design such that when one of the mechanical jams, the mechanical connection to the other two RVDTs will not be compromised.
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Patent Agency Ranking
公开(公告)号：US11014648B2
公开(公告)日：2021-05-25
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：US20200182183A1
公开(公告)日：2020-06-11
申请号：US16707556
申请日：2019-12-09
Applicant: Textron Aviation Inc.
Inventor： Mark Sheridan Hunter , Philippe A. Ciholas
Abstract: Disclosed is a throttle quadrant arrangement utilizing a single throttle lever. The single lever is independently mechanically connected to three Rotary Variable Differential Transformers (RVDTs). Failure points are engineered into the design such that when one of the mechanical jams, the mechanical connection to the other two RVDTs will not be compromised.
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公开(公告)号：US11199867B2
公开(公告)日：2021-12-14
申请号：US16707586
申请日：2019-12-09
Applicant: Textron Aviation Inc.
Inventor： Mark Sheridan Hunter , Ronald J. Parker , Philippe A. Ciholas
Abstract: Disclosed is a throttle quadrant arrangement having a throttle lever which is independently mechanically connected to different Rotary Variable Differential Transformers (RVDTs). A friction lever selectively creates and releases friction from the throttle lever to enable it to be selectively positioned. The system is configured such that the mechanical connections existing between the throttle lever and the RVDTs are shielded from the friction created by the friction lever.
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公开(公告)号：US10960971B1
公开(公告)日：2021-03-30
申请号：US16127403
申请日：2018-09-11
Applicant: Textron Aviation Inc.
Inventor： Steven G. Hagerott , Philippe A. Ciholas
Abstract: An automatic yaw enhancement method for an aircraft having at least one propeller includes providing to a flight controller a pilot command from a pilot interface and avionic data for an airspeed, an angle of attack, and a thrust. A P-factor compensation is determined based on one or more of the airspeed, the angle of attack, and the thrust. A command to a trim device is determined based on a P-factor compensation. When a rudder bias persists, the command to the trim device is repeatedly updated until a rudder force input is nullified. The methods provide automatic pilot assistance for controlling yaw during asymmetric flight conditions and automatic turn coordination while allowing intentional side-slip for facilitating crosswind landings.
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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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