The Boeing Company

Tlie Boeing Company

Joseph E Elliott

Stephen Todd Burrington

Neal Van Huynh

Kent Edmund Karnofski

Matthew August Lassen

Robert James Myers

John A Standley

Andrew Sones

Thomas Jenkins Staggs

Brandon R Boekelman

Camila J Proffitt

Grip for an aircraft

In one or more embodiments, a method for providing continuously variable feel forces for an aircraft comprises sensing, by each of at least one sensor associated with at least one aircraft control, a force sensor value. The method further comprises determining a net force value by using the force sensor value for each of at least one sensor. Also, the method comprises comparing the net force value to a desired breakout force. In addition, the method comprises determining whether the net force value exceeds the desired breakout force. Additionally, the method comprises determining an adjusted force value by using the desired breakout force and the net force value, when the net force value exceeds the desired breakout force. Also, the method comprises determining an actuator torque command based on the adjusted force value. Further, the method comprises commanding an autopilot actuator with the actuator torque command to apply torque.

Providing continuously variable feel forces for fully-powered flight control systems

A rudder control pedal assembly including an idler link pivotably coupled to a support frame at a first joint, a coupler link pivotably coupled to the idler link at a second joint, a drive link pivotably coupled to the coupler link at a third joint and pivotably coupled to the support frame at a fourth joint, and a pedal coupled to the coupler link and constrained to movement along an approximately linear travel path, wherein the support frame forms an imaginary fixed link to complete a four-bar linkage.

Rudder control pedal assembly with linear pedal travel path

Controlling a movement of an aircraft. A computer system detects a position of a group of integrated control levers for the aircraft. The computer system controls a forward thrust, a drag, and a reverse thrust generated by the aircraft based on the position of the group of integrated control levers.

Aircraft movement control system

Systems and methods for jam mitigation in aircraft fly-by-wire systems are described herein. An example method of controlling an aircraft with a fly-by-wire system includes determining a current position of a pilot cockpit controller of the fly-by-wire system, determining an amount of pilot input force applied to the pilot cockpit controller, determining an expected pilot input force value that corresponds to the current position of the pilot cockpit controller, and, if the amount of pilot input force applied exceeds the expected pilot input force value by a threshold, generating a pilot command based on the amount of pilot input force applied and not the current position of the pilot cockpit controller.

Jam mitigation in aircraft fly-by-wire systems and related methods

A rudder control apparatus includes a pair of pedal assemblies, coupled to a support frame for control of a rudder control device. Each one of the pedal assemblies includes an idler link, a coupler link, and a drive link. The idler link is coupled to the support frame and is pivotable relative to the support frame. The coupler link is coupled to the idler link and is pivotable relative to the idler link. The drive link is coupled to the coupler link and to the support frame and is pivotable relative to the coupler link and relative to the support frame. A pedal is coupled to the coupler link. A four-bar linkage is formed by the support frame, the idler link, the coupler link, and the drive link and confines movement of the pedal to a linear travel path in a forward direction and a rearward direction.

An apparatus for controlling the pitch of an aircraft. The apparatus includes a horizontal control column extending from a control wheel horizontally towards a front wall of a cockpit. A pitch output link is connected to a downstream pitch control mechanism to transfer a force applied at the pitch output link to the downstream pitch control mechanism. A transfer assembly is connected to the horizontal control column and to the pitch output link. The transfer assembly translates a horizontal force applied to the horizontal control column to the pitch output link to provide the force applied to the downstream pitch control mechanism.

Growing community of inventors

Shoreline, WA, United States of America

Joseph E Elliott