An aircraft control system includes pilot and co-pilot flight control systems that each include a first shaft mechanically coupled to and displaced apart from a second shaft, the shafts defining and being rotatable about independent longitudinal axes. A connecting link enables rotation of one of the first shafts to rotate a corresponding one of the second shafts. A position transducer is mechanically coupled to each shaft and configured to communicate an electrical signal corresponding to the rotation of the respective shaft. A flight control unit electrically communicates with the position transducers and is configured to (a) receive the electrical signal from each position transducer, (b) detect a failure of the flight control system by detecting differences in the position transducers' electrical signals, and (c) communicate the electrical signal from the position transducer to a flight control surface actuation system to compensate for the detected failure.

A lockout assembly for first and second rudder pedals of an aircraft includes first and second spacers, each of which is configured to be inserted within a corresponding one of first and second slots disposed in an adjacent rudder pedal housing. A coupling mechanism is configured to couple the first spacer to the second spacer through the rudder pedal housing so as to retain the first and second spacers in corresponding ones of the slots. The lockout mechanism prevents movement of the rudder pedals in a same direction, and hence, movement of the aircraft's rudder.

Systems and methods are described for changing the performance of an aircraft by customizing aircraft control system parameters based on a subjective personal preference of a pilot. The system includes a user interface for receiving the customized aircraft control system parameters from the pilot. A first aircraft control module may receive the customized aircraft control system parameters from the user interface, and also receive flight control commands from the pilot. The received flight control commands and the received customized aircraft control system parameters may be processed by the first aircraft control module to cause the aircraft to perform according to customized characteristics as determined by the pilot.

A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

A system and method for retention of flight deck preferences operates to control a comprehensive combination of aircraft systems and system configurations enabling a pilot to seamlessly retain and recall the desired preferences based on a plurality of mission related factors. With system control of flight deck physical settings including seat position and shape, display illumination and color and internal and external lighting configurations, the system allows a pilot to save time, effort, and minimize errors of system set up and configuration. With a short entry, or short-range sensing, of the pilot ID, the pilot commands the system and method for retention of flight deck preferences to configure each of the plurality of aircraft systems according to the recalled pilot preference.

An aircraft control system includes: a motor with a rotating shaft; a pilot control input; a linear actuator connecting the pilot control input to the rotating shaft; a sensor identifying a position of the pilot control input; and a transmitter transmitting the pilot control input position to a controller, the controller adjusting an aircraft performance device based on the received pilot control input 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 hybrid fly/drive vehicle capable of being converted between a flying mode in which it is capable of flying in air and a road riding mode in which it is capable of driving on a road in normal traffic, includes an arrangement to allow the engine to be pedal-controlled in road riding mode and lever-controlled in flying mode, and further includes pedals for engine control and possibly clutch actuation in road riding mode and for rudder control in flying mode, which pedals also actuate the brakes in flying mode.

An electric pedal control device for an aircraft, the device comprising several pedal transmission assemblies, each of the pedal transmission assemblies comprising an electric motor, an elastic connector, a transmission mechanism, an angular displacement sensor, and a pedal, wherein the angular displacement sensor is configured to acquire rotational position information about the pedal; transmission mechanism revolute pairs of the transmission mechanisms in the pedal transmission assemblies are connected via a mechanical connecting rod mechanism to effect linkage; and a controller of the electric pedal control device is configured to receive the rotational position information, and to control, according to the rotational position information, the electric motors to dampen the elastic connectors.

Tail rotor control system is described for helicopters. A pedal position sensor operable by a pilot yields greater tail rotor RPM relative to the main rotor RPM, giving the pilot increased control over the vehicle. This proves especially useful in certain situations, such as high altitude, where increasing tail rotor speed from main rotor speed can give a pilot increased maneuverability and stability.