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.

Aircraft power system is disclosed having a hydraulic reservoir, a bi-directional hydraulic pump for pumping hydraulic fluid to and from the reservoir, and an electric motor. The electric motor is connectable to a first driveable component of the aircraft such that the electric motor is arranged to drive the first driveable component of the aircraft. The hydraulic pump is connectable to the first driveable component of the aircraft such that the hydraulic pump is arranged to pump hydraulic fluid from the reservoir to drive the first driveable component of an aircraft. Thus, in a first driveable mode of operation, the first driveable component is driven by both the electric motor and the hydraulic pump.

A system and method for deploying a flight control surface. The method includes displacing actuators engaged with the flight control surface during an initial period wherein each actuator displaces from zero speed to a deployment speed, and during a deployment period after the initial period. The method includes during the deployment period, controlling displacement of at least one of the actuators in response to actuator status information received therefrom. The method includes during the initial period, limiting an acceleration of said actuator from the zero speed to the deployment speed. The system has a control unit with a force fight controller and an acceleration limiter.

A system for detecting and controlling the position of a spoiler of an aircraft wing is described herein comprising: a hydraulic actuator having a piston rod operably connected to the spoiler, the piston rod being moveable between a retracted position, a neutral position and an extended position; and means for providing power to said hydraulic actuator; and a mechanical device for detecting whether the piston rod is in the retracted position, the neutral position or the extended position; and means, operatively connected to the mechanical device, that is configured to provide a change in a load applied to said hydraulic actuator, wherein said means is configured to change said load based on whether said piston rod is detected as being in said retracted position or said extended position.

Inerters with friction disk assemblies, and aircraft hydraulic systems and aircraft including the same. An inerter comprises an inerter housing containing an inerter fluid, a threaded shaft extending within the inerter housing and fixed relative to the first terminal, and an inerter rod extending at least partially within the inerter housing and fixed relative to the second terminal. The inerter further includes a friction disk assembly that, together with the inerter fluid, is configured to damp a motion of the second terminal relative to the first terminal. The friction disk assembly includes a fixed portion and a rotating portion, and is configured such that rotation of the rotating portion generates a frictional torque that opposes the rotation of the rotating portion. In some examples, the inerter is a component of a hydraulic actuator, an aircraft hydraulic system including the hydraulic actuator, and/or an aircraft including the aircraft hydraulic system.

Inerters with friction disk assemblies, and aircraft hydraulic systems and aircraft including the same. An inerter comprises an inerter housing containing an inerter fluid, a threaded shaft extending within the inerter housing and fixed relative to the first terminal, and an inerter rod extending at least partially within the inerter housing and fixed relative to the second terminal. The inerter further includes a friction disk assembly that, together with the inerter fluid, is configured to damp a motion of the second terminal relative to the first terminal. The friction disk assembly includes a fixed portion and a rotating portion, and is configured such that rotation of the rotating portion generates a frictional torque that opposes the rotation of the rotating portion. In some examples, the inerter is a component of a hydraulic actuator, an aircraft hydraulic system including the hydraulic actuator, and/or an aircraft including the aircraft hydraulic system.

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 aircraft comprises an aircraft structure, a flight control surface attached to the aircraft structure, and a local hydraulic power pack disposed proximal to the flight control surface. The local hydraulic power pack is configured to provide pressurized hydraulic fluid for actuating the flight control surface. The local hydraulic power pack comprises a reservoir for the hydraulic fluid and two hydraulic pumps for pressurizing the hydraulic fluid.

An aircraft comprises an aircraft structure, a flight control surface attached to the aircraft structure, and a local hydraulic power pack disposed proximal to the flight control surface. The local hydraulic power pack is configured to provide pressurized hydraulic fluid for actuating the flight control surface. The local hydraulic power pack comprises a reservoir for the hydraulic fluid and two hydraulic pumps for pressurizing the hydraulic fluid.

A control valve for a multi-stage hydraulic actuator includes a valve body defining a translation axis, a spool disposed within the valve body and movable along the translation axis, and a flange. The flange is fixed relative to the spool and has an aperture disposed externally of the valve body to removably fix the spool to a spool of a redundant control valve independently connected to the multi-stage hydraulic actuator for mitigating force fights between actuators coupled to the control valve.