An aircrew automation system may comprise an actuation system and a computer system having a processor and one or more interfaces. The computer system can be communicatively coupled with a flight control system of an aircraft and configured to generate control commands based at least in part on flight situation data. The actuation system is operatively coupled with the computer system and comprises a robotic arm, a force sensor, and a controller. The robotic arm can be configured to engage a cockpit instrument among a plurality of cockpit instruments. The force sensor is operably coupled to the robotic arm and configured to measure a force when the robotic arm makes contact with the cockpit instrument. The controller is operably coupled with the robotic arm and the force sensor.

An aircrew automation system may comprise an actuation system and a computer system having a processor and one or more interfaces. The computer system can be communicatively coupled with a flight control system of an aircraft and configured to generate control commands based at least in part on flight situation data. The actuation system is operatively coupled with the computer system and comprises a robotic arm, a force sensor, and a controller. The robotic arm can be configured to engage a cockpit instrument among a plurality of cockpit instruments. The force sensor is operably coupled to the robotic arm and configured to measure a force when the robotic arm makes contact with the cockpit instrument. The controller is operably coupled with the robotic arm and the force sensor.

An airplane rudder and brake pedal assembly includes a rudder arm assembly having one rudder arm with first upper and lower arm portions, and another rudder arm with second upper and lower arm portions. The rudder arm assembly is assembled to a beam at an intersection of the first upper and lower arm portions, and an intersection of the second upper and lower arm portions. The first and second rudder arms are configured to rotate about the beam at the intersection. The rotation of the first and second rudder arms is configured to adjust control surfaces that control a yaw axis of the airplane. A brake pedal is attached to the first and second lower arm portions. Rotation of the brake pedal brakes the airplane. A rotary sensor is assembled to the brake pedal and the lower arm portion, and configured to determine an extent of the brake pedal rotation.

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.

An airplane rudder and brake pedal assembly includes a rudder arm assembly having one rudder arm with first upper and lower arm portions, and another rudder arm with second upper and lower arm portions. The rudder arm assembly is assembled to a beam at an intersection of the first upper and lower arm portions, and an intersection of the second upper and lower arm portions. The first and second rudder arms are configured to rotate about the beam at the intersection. The rotation of the first and second rudder arms is configured to adjust control surfaces that control a yaw axis of the airplane. A brake pedal is attached to the first and second lower arm portions. Rotation of the brake pedal brakes the airplane. A rotary sensor is assembled to the brake pedal and the lower arm portion, and configured to determine an extent of the brake pedal rotation.

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.

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.

Provided are airplane trim systems and methods of controlling such systems. These systems utilize smaller portions of the stabilizer total travel range for takeoff trims, in comparison to other trim systems. A trim system described includes stabilizer and elevator, and these components are used together to achieved a takeoff total tail pitching moment. The elevator or, at least a portion of the elevator operating range, is available for flight control. As such, takeoff trim settings include stabilizer and elevator orientation settings. Addition of the elevator to control the takeoff tail pitching moment allows reducing the stabilizer total travel. The elevator orientation can be changed much faster than that of the stabilizer providing pilot more control.

Provided are airplane trim systems and methods of controlling such systems. These systems utilize smaller portions of the stabilizer total travel range for takeoff trims, in comparison to other trim systems. A trim system described includes stabilizer and elevator, and these components are used together to achieved a takeoff total tail pitching moment. The elevator or, at least a portion of the elevator operating range, is available for flight control. As such, takeoff trim settings include stabilizer and elevator orientation settings. Addition of the elevator to control the takeoff tail pitching moment allows reducing the stabilizer total travel. The elevator orientation can be changed much faster than that of the stabilizer providing pilot more control.

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.