The Boeing Company

Theboeing Company

David George Miller

Joseph G Irwin

Nathaniel T Morgan

Pieter G Einthoven

Channing S Morse

Paul Lee Redkoles

David C Mossman

John D Butkiewicz

Yi Lu

James P Roberts

Mark S Spano

Pasquale A Randazzo

Robert Paul Gradle

Jeffrey S Nicholas

Martin R Sarsfield

James E Taylor

James D Culp

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 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

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.

Active-inceptor tactile-cueing hands-off rate-limit

A method and apparatus for a split detent tactile cueing control system comprising an inceptor, a position sensor, vehicle sensors, and a flight control computer. The inceptor can be moved into different positions measured by a position sensor. The vehicle sensors generate signals in response to detecting parameters about a vehicle during a flight. The flight control computer is coupled to the inceptor and the vehicle sensors. The flight control computer is capable of generating actuation signals used to generate tactile cues to generate a flight path hold detent and an altitude hold detent within the plurality of positions using a force feel profile and the parameters. An extension of a latch force from the flight path hold detent to the altitude hold detent is present during changes in vehicle direction. Series actuator compensation allows increased split detent separation with insignificant command overshoot.

Precision adjust split detent for a vehicle

A bias correcting phase compensating rate limiter to control movement of a device may include a switching arrangement adapted to reverse a polarity of an error signal in response to a set of predetermined conditions that may include a commanded rate of movement of the device exceeding a rate limit capability of the device; a time rate of change of an input signal to the rate limiter being opposite in polarity to a difference between the input signal to the rate limiter and an output signal from the rate limiter; and a time rate of change of the input signal to the rate limiter being opposite in polarity to a difference between the output signal from the rate limiter and a signal corresponding to a pre-specified neutral or trim position of the device.

Bias correcting phase compensating rate limiter

Systems and methods are provided for determining a final heading of a turning vehicle, such as a rotorcraft. The system may include an algorithm that calculates an advance prediction of a final heading that will be achieved after control input is terminated. The system may also include a device, such as a display, for conveying predicted final heading information to an aircraft controller, such as a pilot.

Heading reference command and control algorithm and cueing systems and methods for aircraft turn-to-target maneuvers

A system, a method, and a computer program product for determining tactile cueing of a flight control input apparatus includes an interface for receiving observed parameters relating to the flight envelope of an aircraft. Upstream processing elements receive the observed states, convert dimensional aircraft state parameters into nondimensional aircraft state parameters, and provide the data to neural networks. The neural networks receive combinations of observed parameters and nondimensional aircraft state parameters and predict flight envelope limiting parameters. The neural networks are trained to predict the limiting parameters. A downstream processing element determines the most limiting flight envelope limiting parameter provided from the neural networks, therefore providing a tactile cueing position for a flight control input apparatus.

Method, system, and computer program product for tactile cueing flight control

A split detent tactile cueing vehicle control system ( ) for a vehicle ( ) is provided including an active control inceptor system ( ). The active system ( ) includes a control inceptor ( ) having a plurality of positions and a position sensor ( ) that generates a control inceptor position signal. The tactile cueing system ( ) also includes a plurality of vehicle performance sensors that generate a plurality of vehicle performance signals. A flight controller ( ) is electrically coupled to the position sensor ( ) and the plurality of vehicle performance sensors, and generates a control inceptor actuation signal by applying a tactile cueing model having a split detent and in response to the position signal and the plurality of vehicle performance signals. A method of performing the same is also provided.

Split detent tactile cueing vehicle control system

A method and apparatus for automatically jettisoning cargo carried by a dual-point suspension system when a suspension system failure is detected. Three conditions must be satisfied before a load is jettisoned. The average value of the load and an instantaneous value of the load on a hook must have fallen below a threshold value (zero load condition). A threshold amount of the load must have shifted from one hook to the other (dynamic load split condition). A threshold amount of an initial hook load must have been lost within a short period of time (rapid rate-of-decrease condition). For all three conditions, the threshold amount or value is adaptively set based on the actual load carried by the dual-point suspension. If all three conditions are satisfied for either the forward or the aft hook, the cargo is jettisoned. Additionally, a fourth condition that detects whether a structural limit of a hook has been exceeded is evaluated. If the structural limit has been exceeded, the load is jettisoned.

Growing community of inventors

Mount Laurel, NJ, United States of America

David George Miller