The disclosure relates to a flight control system comprising at least one hydraulic servo actuator, wherein the servo actuator includes a two-stage electrohydraulic servo valve, wherein the servo valve comprises a pilot stage in which the control current is translated into a hydraulic control pressure, and a power stage in which a valve slide is moved in response to the control pressure in order to adjust the throughflow direction and throughflow cross-section of the valve. The disclosure furthermore relates to an aircraft comprising such a flight control system.

The disclosure relates to a flight control system comprising at least one hydraulic servo actuator, wherein the servo actuator includes a two-stage electrohydraulic servo valve, wherein the servo valve comprises a pilot stage in which the control current is translated into a hydraulic control pressure, and a power stage in which a valve slide is moved in response to the control pressure in order to adjust the throughflow direction and throughflow cross-section of the valve. The disclosure furthermore relates to an aircraft comprising such a flight control system.

An integrated asymmetric brake system for an aircraft includes a housing and a control surface actuator arranged in the housing. The control surface actuator includes a torque limiter output member and is operable to selectively deploy and retract a control surface. An asymmetry brake system is arranged in the housing and is operably connected to the control surface actuator and the torque limiter output member. The asymmetry brake system is selectively operable to prevent deployment of the control surface by activating the torque limiter output member upon detecting an asymmetry event. An asymmetry brake test monitor switch is mounted in the housing and operably coupled to the asymmetry brake system. The asymmetry brake test monitor switch is monitored to confirm functionality of the asymmetry brake system prior to flight.

An actuator assembly may comprise a screw shaft having a shaft axis; a drive arrangement pivotally supported about the screw shaft axis for driving the screw shaft, e.g., about the shaft axis or along the shaft axis, and a rod mounted to the drive arrangement at a location off the shaft axis for providing a primary function of reacting torque about the shaft axis on the drive arrangement. The rod may comprise a rod axis and provide a load path along the rod axis for reacting torque. The rod may also comprise a device for which provides a secondary function for the actuator assembly based on the load experienced along the load path provided by the rod.

An actuator system for a flight control surface of an aerial vehicle includes a differential gear set having a first sun gear, a second sun gear and at least one planet gear to directly drive the flight control surface. The actuator system includes a first electric servomotor coupled to the aerial vehicle, and the first electric servomotor drives the first sun gear to drive the at least one planet gear. The actuator system includes a second electric servomotor coupled to the aerial vehicle, and the second electric servomotor drives the second sun gear to drive the at least one planet gear such that the first electric servomotor and the second electric servomotor cooperate to rotate the flight control surface relative to the aerial vehicle by producing a single rotary output.

An actuator system for controlling a movable surface has a main shaft connected between a power drive unit and the movable surface to transmit a command from the power drive unit to move the movable surface. If a failure in the main shaft is detected a failure control device connects a secondary shaft from the movable surface to the power drive unit e.g. by releasing a solenoid which releases gears so as to permit differential rotations between an outer ring and a sun gear of a planetary gear system, within prescribed limits. When these limits are exceeded, the solenoid brake is de-energised braking the planetary gear outer ring and tying the gears through an epicycle ratio corresponding to the ratio of gears connecting the main and secondary shafts. The gear system acts as a low mass asymmetry brake that allows post-failure operation of the surface control.

An actuator includes a ball screw, a rod provided at least partially within the ball screw, a ball nut, a ball nut restraint, a first biasing member disposed at least partially between a proximate end of the rod and a proximate end of the ball screw, and a second biasing member disposed at least partially between a distal end of the ball nut and an inner surface of the ball nut restraint.

There is provided an actuator comprising screw shaft and a nut assembly. The nut assembly comprises a primary nut for transmitting load through the actuator along a primary load path, and a secondary nut for transmitting load through the actuator along a secondary load path. The secondary nut comprises first and second portions movable relative to one another. As load is transmitted through the actuator along the primary load path the secondary nut does not transmit load through the actuator, wherein upon failure of the primary load path the first and second portions move relative to each other, such relative movement causing the first and second portions to engage the screw shaft and enable transmittal of load through the secondary nut of the actuator along the secondary load path.

The invention relates to an overload clutch for a drive gear mechanism for driving components of an aircraft wing, in particular for driving an outer slat flap of an aircraft wing, with at least one driving and at least one driven clutch body and with at least one torque transmission body arranged therebetween. The invention further relates to a drive gear mechanism with a corresponding overload clutch.

A ball screw assembly for use in an actuator is provided. The ball to screw assembly may include a ball screw supported for rotation by the actuator. A ball nut may be provided around the ball screw and may be held against rotation with the ball screw by said actuator. A primary load path may be provided between the ball screw and the ball nut for operatively coupling the ball nut with the ball screw. A secondary load path may be provided between the ball screw and the ball nut, wherein the secondary load path can be disengaged during a normal operating mode of the ball screw assembly and the secondary load path can be engaged during a second operating mode of the ball screw assembly.