A system and method for flying an aircraft is disclosed. The system includes one or more flight-assist agents for performing an operation related to flying the aircraft and a vehicle autonomy management system. The vehicle autonomy management system allocates tasks of a task workload involved in the operation between a flight crew and the one or more flight-assist agents, monitors a performance of the flight crew in executing a portion of the task workload allocated to the flight crew, and adjusts an allocation of the task workload between the flight crew and the one or more flight-assist agents based on the performance of the flight crew.

A control augmentation system for high aspect ratio aircraft has aileron/flaperon and throttle position sensors; spoiler and flap controls; a mode switch with manual, and landing modes; and a controller driving left and right spoiler and flap servos, the controller including at least one processor with memory containing firmware configured to: when the mode switch is in manual mode, drive both spoiler servos to a symmetrical position according to the spoiler control; when the mode switch is in landing mode, drive the left spoiler to a position dependent on aileron and throttle position, and the right spoiler to a position dependent on aileron and throttle position, the left and right spoiler positions differing whenever ailerons are not centered, and an average of spoiler positions is more fully deployed when the throttle position is at a low-power setting than when the throttle position is at a high-power setting.

Systems and methods are provided for a lockout device. The lockout device may prevent movement of aircraft control devices. The lockout device may include one or more portions and may include features that are designed to couple to or clasp a yoke of an aircraft as well as interface or couple to a pedal housing of the aircraft. Features of the lockout device may prevent movement of the aircraft control devices. The lockout device may include features to lock the device and may be multiple separate pieces or may be a hinged device.

A bracket (20) for mounting a touch-to-talk actuator (38) off of a control column (24) of an airplane steering yoke (26) has a split collar (22) for clamping onto the control column (24) and an elongated support rod (32) cantilevered from the split collar (22), providing a distal mounting end (36) for the touch-to-talk actuator (38). Wires (44) link the touch-to-talk actuator (38) with controls in the airplane cockpit for intercom, radio, phone or other voice-communication path between the pilot and others, whether on the ground or elsewhere. The support rod (32) is elongated, configured and cantilevered from the split collar (22) such that the touch-to-talk actuator (38) is proximal one of the handles or hand grip portions of the steering yoke (26) so that the pilot can actuate it with a single digit, like his or her thumb, without otherwise letting go of the steering.

The airplane anti-hijacking system is an access control, alarm, and lockout system that is installed on commercial aircraft for the purpose of preventing unauthorized persons from taking control of the aircraft. The airplane anti-hijacking system is a biometric system that authenticates the identity of the flight crew and automatically monitors the flight operation for anomalies. Should an anomaly occur in-flight, an emergency message is sent via satellite to the appropriate authorities. Upon receipt of an emergency message, airplane anti-hijacking system gives the appropriate authorities the ability to seize control of the aircraft by locking out in-flight control of the operation of the flight controls and operating the aircraft remotely. The airplane anti-hijacking system further comprises a craft control module and a plurality of biometric scanners.

An aircraft hand controller is disclosed. The hand controller includes a set of finger controls on a single hand grip structure, the set of finger controls including a first finger control configured to control throttle of the aircraft and a second finger control, separate from the first, configured to control rotation about a first rotational axis of the aircraft.

The present invention relates to a fly-by-wire type of aircraft flight control system having a pair of sidesticks for pilot and co-pilot input, respectively, and having logic that controls the priority of input as between the two sidesticks in certain aircraft flight situations. It allows either the pilot or co-pilot to ensure that his/her sidestick is the only one issuing flight control commands at any one moment in time by first pressing a simple latch button located, for example, on the glareshield in the cockpit and then maneuvering the sidestick in the desired manner to effectuate flight control, e.g., pitch and/or roll, of the aircraft.

A sensor, and method of using the sensor, includes a primary resolver circuit and a static reference resolver circuit. The primary resolver circuit is configured to provide first and second primary analog outputs. The primary analog outputs are indicative of a sensed condition of the sensor. The static reference resolver circuit includes a transformer and is configured to generate first and second reference analog outputs indicative of a reference condition of the sensor. The first and second reference analog outputs match the first and second primary analog outputs when the sensed condition is equivalent to the reference condition.

Systems and methods are provided for a lockout device. The lockout device may prevent movement of aircraft control devices. The lockout device may include one or more portions and may include features that are designed to couple to or clasp a yoke of an aircraft as well as interface or couple to a pedal housing of the aircraft. Features of the lockout device may prevent movement of the aircraft control devices. The lockout device may include features to lock the device and may be multiple separate pieces or may be a hinged device.

A flight control system for an aircraft includes at least one flight control computer that carries out a ground lift dump function that selectively extends a spoiler located on a wing of the aircraft into an airflow passing over the wing. The at least one flight control computer includes arming logic that is responsive to an input signal indicative of an aircraft parameter to automatically arm the ground lift dump function during certain phases of operation of the aircraft. The at least one flight control computer includes spoiler deployment logic that is responsive to an arming signal from the aiming logic which indicates that the ground lift function is armed to deploy the spoiler into its extended position within the airflow passing over the wing of the aircraft to assist in stopping the aircraft while the aircraft is on the ground.