The Boeing Company

Theboeing Company

Joseph G Irwin

David George Miller

Nathaniel T Morgan

Russell J Enns

Gary D Klein

Bryan C Chu

Jon F Lenander

Brandon R Brown

Pieter G Einthoven

Bryan E Kashawlic

Mark S Spano

A control system having a variable operator interface (VOI) is disclosed, and includes one or more processors and a memory coupled to the processors. The memory stores program code causing the control system to detect an existence and first direction of an operator control input to one or more active inceptors being backdriven from an operator on inceptor detector (OID). The control system is caused to compare the first direction of the operator control input with a second direction of one or more zero-force detent rates to determine a variance and interprets the operator control input as inadvertent based on the variance. In response to interpreting the operator control input as inadvertent, the control system is caused to limit the operator control input to reduce or substantially eliminate movement of the machine caused by inadvertent input by modifying the operator control input based on one or more command modifiers.

Variable operator interface for backdriving control input devices

A control circuitry includes a first filter configured to filter a gravity compensated longitudinal acceleration of an aircraft to generate a filtered gravity compensated longitudinal acceleration. The propulsor trim control circuitry also includes a second filter configured to generate a filtered speed of the aircraft based on a speed of the aircraft. The propulsor trim control circuitry includes intermediary circuitry configured to generate a filtered longitudinal control effector error based on the filtered gravity compensated longitudinal acceleration and the speed. The propulsor trim control circuitry also includes a third filter configured to generate a filtered longitudinal thrust effector command value based on a longitudinal thrust effector command value. The propulsor trim control circuitry further includes output circuitry configured to generate a predicted longitudinal thrust effector trim value for a target horizontal state based on the filtered longitudinal control effector error and the filtered longitudinal thrust effector command value.

Propulsor trim prediction for aircraft

A control circuitry includes a propulsor trim prediction circuitry and an output circuitry. The propulsor trim prediction circuitry is configured to generate a predicted proprotor nacelle trim value based on an aircraft velocity and a pitch attitude deviation from a reference. The output circuitry is configured to output a proprotor nacelle command based on the predicted proprotor nacelle trim value. The proprotor nacelle command is configured to cause an adjustment in a nacelle angle of a proprotor of an aircraft.

Pitch and thrust control for tilt-rotor aircraft

A control system for a machine having variable rate damping based control (VRDC) is disclosed, and includes one or more processors and a memory coupled to the processors storing data comprising a database and program code that, when executed by the processors, causes the control system to receive an inceptor position from one or more active inceptors and calculate an operator command based on at least the inceptor position. The control system is caused to determine an amplitude of the operator command. The control system is caused to determine a variable gain based on the amplitude of the operator command and determines an actuation command based on the variable gain. The control system sends the inline actuators the actuation command. The inline actuators actuate into a total actuator position to variably damp movement of the machine as a function of the magnitude of the operator command.

Variable rate damping based control system for backdriven control input devices

A control circuitry includes a propulsor trim prediction circuitry configured to generate a predicted propulsor collective blade pitch trim value for a target state of an aircraft based on an aircraft velocity and a pitch attitude deviation from a reference. The control circuitry further includes an output circuitry configured to output a propulsor collective blade pitch angle command based on the predicted propulsor collective blade pitch trim value. The propulsor collective blade pitch angle command is configured to cause an adjustment in a blade pitch angle of a propulsor of the aircraft. Additionally or alternatively, the control circuitry includes a pitch attitude trim prediction circuitry configured to generate a predicted pitch attitude trim value. The output circuitry is configured to output an aircraft pitch attitude trim command, configured to cause an adjustment in a pitch angle of the aircraft, based on the predicted pitch attitude trim value.

Pitch and thrust control for compound aircraft

A control circuitry includes a first filter configured to generate a filtered velocity based on a component of a vertical velocity of an aircraft. The pitch trim prediction circuitry also includes a second filter configured to generate a filtered pitch attitude based on a measured pitch attitude of the aircraft. The pitch trim prediction circuitry further includes output circuitry configured to generate a predicted pitch attitude trim value for a target vertical state based on a horizontal velocity of the aircraft, the filtered velocity, and the filtered pitch attitude. The predicted pitch attitude trim value is configured to cause a flight control effector to be adjusted.

Pitch trim prediction for aircraft

A point-and-shoot automatic landing system (P-A-S ALS) realizes safety and mission effectiveness benefits in vertical takeoff and landing (VTOL) aircraft, allowing a pilot, using an inceptor device, to select an aim point with an aiming device providing visual indication of the aim point. Once a flight path is computed the pilot may allow the P-A-S ALS to automatically control the flight to touchdown. A suite of ranging devices determines the relative position of the aircraft to the selected aim point and an approach profile guidance algorithm computes the flight path. One or more devices provide confirmation that automatically controlled flight to the selected aim point is achievable. The P-A-S ALS is configured to allow termination of the controlled flight path at any time and selection of a new aim point through the inceptor device.

Point-and-shoot automatic landing system and method

The system contains the active inceptor having mobility in a first direction. A feedback mechanism is in communication with the active inceptor. The mechanism provides a variable level of force to the active inceptor in the first direction. A programmable device communicates with the feedback mechanism. The programmable device controls the level of force provided to the active inceptor from the feedback mechanism. The programmable device is capable of recognizing and distinguishing between regimes wherein the operator is physically engaging the inceptor ('hands-on' state) and when the operator is 'hands-off' the inceptor. The programmable device limits the maximum rate of displacement of an active inceptor to a specified safe and effective value regardless of changes in forces applied by the variable force feel feedback mechanism. The limit on rate of change of active inceptor position is varied based on the recognized &#x201c;hands-on&#x201d; or &#x201c;hands-off&#x201d; state and the type of tactile cue to satisfy otherwise conflicting requirements for failure robustness and effective tactile cueing during highly dynamic operations.

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Landenberg, PA, United States of America

Joseph G Irwin