The Boeing Company

Bryan C Chu

Gary D Klein

Russell J Enns

Joseph G Irwin

Jon F Lenander

Donald J Hunter

Jaheen Noor Ahmad

Jacob Walrath

A flight control system includes an active control inceptor, a flight control computer, and a force trim release. The active control inceptor includes a control member movable from a first position to a second position to command a vehicle-body rate and including a detent position that holds an attitude. The flight control computer generates a trim command from the second position, a reference position, and a vehicle-body state. With the force trim release selected when the control member is moved from the first position to the second position, the first position is designated as the reference position and the second position is designated as the detent position. Upon deselection of the force trim release with the control member at the second position, the second position is designated as the reference position and the trim command is designated as the detent position.

Split-reference system and method for rapid re-trimming rate command of force trim release

A flight control system having a plurality of dual mode operator control inputs is disclosed and includes a plurality of active parallel actuators, one or more processors, and memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the flight control system to receive a signal indicating an airspeed of the compound aircraft and select between rotary and fixed wing modes of operation based on the airspeed. In response to selecting a mode of operation, the flight control system sends either a rotary or a fixed wing force feel profile to the plurality of active parallel actuators, where the force feel profile defines the respective detent force gradient, where the fixed wing detent force gradient is at least about two times greater than a rotary wing detent force gradient.

Parallel actuation control system providing dual mode operator control inputs for a compound aircraft

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 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.

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Phoenix, AZ, United States of America

Bryan C Chu