Embodiments of the disclosure include a redundant control system for a vehicle. The redundant control system includes first and second actuator pistons mechanically coupled to one another and disposed in respective first and second fluid chambers. The first and second actuator pistons are movable by first and second primary stages. One of the primary stages includes a bypass valve with a pilot valve actuatable in response to movement of the first actuator piston.

Embodiments of the disclosure include a redundant control system for a vehicle. The redundant control system includes first and second actuator pistons mechanically coupled to one another and disposed in respective first and second fluid chambers. The first and second actuator pistons are movable by first and second primary stages. One of the primary stages includes a bypass valve with a pilot valve actuatable in response to movement of the first actuator piston.

A hydraulic system for an aircraft. The hydraulic system can include a hydraulic actuator that is operatively coupled to a flight control member. Hydraulic fluid is moved through the hydraulic system by an engine driven pump that delivers hydraulic fluid to the actuator at a first pressure, and a boost pump that delivers hydraulic fluid to the actuator at a second pressure that is higher than the first pressure. The hydraulic system is configured such that the hydraulic fluid returning from the actuator to the engine driven pump can be delivered to the boost pump prior to reaching the engine driven pump.

A dual-independent hybrid actuator system includes an actuator body defining a hydraulic chamber. The actuator system includes a hydraulic piston assembly, including a hydraulic piston disposed within the hydraulic chamber and dividing the hydraulic chamber into a first hydraulic sub-chamber in fluid communication with a first hydraulic fluid passage and a second hydraulic sub-chamber in fluid communication with a second hydraulic fluid passage. The actuator system further includes a piston rod mounted to the hydraulic piston that passes through the second hydraulic sub-chamber with a distal end that projects outward from the actuator body. The actuator system further includes an electric motor mounted to the actuator body, and a threaded axle mechanically coupled to a motor shaft of the electric motor. The threaded axle passes through the first hydraulic sub-chamber and engages with a threaded port formed in the hydraulic piston assembly.

The redundancy control device includes three controllers that output status signals, a majority voting circuit to which a first voltage or a second voltage is supplied as an output signal through an output line of each controller, a switch provided in each output line, a voltage supply unit provided for each output line to supply the second voltage to the output line when the first voltage is lost, a latch circuit provided for each output line to latch the second voltage when the second voltage is supplied thereto and continue to output the second voltage, a comparison circuit provided for each controller to output a comparison signal based on a comparison of the status signals, and a switch control unit provided for each switch to outputs a switch signal to the switch in response to the comparison signal from the comparison circuit.

The redundancy control device includes three controllers that output status signals, a majority voting circuit to which a first voltage or a second voltage is supplied as an output signal through an output line of each controller, a switch provided in each output line, a voltage supply unit provided for each output line to supply the second voltage to the output line when the first voltage is lost, a latch circuit provided for each output line to latch the second voltage when the second voltage is supplied thereto and continue to output the second voltage, a comparison circuit provided for each controller to output a comparison signal based on a comparison of the status signals, and a switch control unit provided for each switch to outputs a switch signal to the switch in response to the comparison signal from the comparison circuit.

An electromechanical actuator assembly comprises a first actuator and a second actuator. The first actuator and the second actuator are coupled together end-to-end and are independently operable. A method of actuating a moveable element using an actuator assembly, comprises: coupling a first actuator between a fixed structure and a second actuator so that the first actuator is operable to move the second actuator relative to the fixed structure; coupling the second actuator to the moveable element; and moving the moveable element by moving the second actuator using the first actuator.

A force fight mitigation system comprising: control means configured to provide a position command to each of two or more actuators arranged to position a surface, the position command indicative of a desired position of the actuator relative to the surface; means to detect the actual position of the actuator relative to the surface in response to the position command; and means to determine an offset between the desired position and the actual position and to store a rigging correction based on the offset; wherein, for each actuator, an offset is determined for each of three or more desired positions.

An actuation system for a control surface of an aircraft includes a drive lever. The drive lever includes a coupling end configured to pivotably couple to a plurality of wing attach fittings and a lever end. The lever end includes a first actuator fitting configured to pivotably couple to a first actuator on a forward side of the drive lever; a second actuator fitting configured to pivotably couple to a second actuator on an aft side of the drive lever; a first drive link fitting configured to couple, via a first drive link, to a control surface of an aircraft; and a second drive link fitting configured to couple, via a second drive link, to the control surface of the aircraft.

A holding device for an aircraft actuator, comprising a body that extends between a lug configured to hingedly connect the holding device to a actuator support body and an attachment flange configured to fixedly attach the holding device to a landing provided by a main body of an actuator. The holding device is configured to prevent movement of the actuator from a normal working position relative to the actuator support body in the event of structural failure of a connection body of the actuator.