Distributed trailing edge wing flap systems are described. An example wing flap system for an aircraft includes a flap and first and second actuators. The flap is movable between a deployed position and a retracted position relative to a fixed trailing edge of a wing of the aircraft. The first and second actuators are configured to move the flap relative to the fixed trailing edge. The first actuator is actuatable via pressurized hydraulic fluid to be supplied from a hydraulic system of the aircraft to the first actuator via a hydraulic module operatively coupled to the first actuator. The first actuator is operatively coupled to a first shaft. The second actuator is actuatable via an electric motor of the second actuator. The electric motor is operatively coupled to an electrical system of the aircraft. The second actuator is operatively coupled to a second shaft. The first and second shafts are selectively operatively couplable via a clutch operatively positioned between the first and second shafts. The clutch is actuatable between a disengaged position in which the second shaft is operatively uncoupled from the first shaft and an engaged position in which the second shaft is operatively coupled to the first shaft.

An actuator includes a drive assembly, a ball screw, and a ball nut. The ball nut may include a first nut member, a second nut member; and first arm extending from the first nut member. The first arm may include a first portion and a second portion. The first portion may extend radially outward from the first nut member. The second portion may extend substantially axially from the first portion such that at least some of the second portion is disposed radially outward of the second nut member. A second arm may extend from the second nut member, and the second arm may include a first portion and a second portion. In embodiments, at least part of the second portion of the first arm is disposed radially outward of at least a part of the second portion of the second arm.

A nut arrangement for a screw actuator is disclosed for allowing detection of wear in a primary nut of the screw actuator. The nut arrangement comprises a primary nut for providing a primary load path and a secondary nut for providing a secondary load path. An interface ring may link the secondary nut to the primary nut. A sensor is provided to detect relative axial movement between the primary and secondary nuts. During normal operation, the interface ring is seated by a flexible coupling that allows relative axial displacement of the secondary nut to the primary nut to accommodate wear in the primary nut. The sensor can be used to monitor backlash between the primary and secondary nuts to determine wear of the primary nut.

An attachment assembly for connecting an actuator to a frame, a method for manufacturing this attachment assembly and a method for reducing backlash in an attachment assembly. The attachment assembly comprises: an outer yoke having a first end and an opposite second end and defining an internal cavity at said second end. The outer yoke has an aperture provided at its second end connected to the cavity; and an inner yoke located within the cavity. A tie bar having a ball shaped end extends through said aperture such that the ball shaped end is positioned within the cavity and cannot pass through the aperture. A spring is provided at said first end of said outer yoke that is configured to bias the inner yoke in the direction of the aperture. The attachment also includes shearable means for holding the inner yoke.

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 autopilot system includes an actuator arrangement that receives control signals to influence the flight of the helicopter in a selected one of a plurality of different flight modes. A control stick input arrangement allows flight mode selection and control with no more than a particular one of the pilot's hands in the engaged position on the stick and without moving the hand away from the engaged position. A slaved gyro output signal is based on no more than the set of sensor outputs used by the autopilot such that an autopilot display presents autopilot flight mode information while displaying a slaved gyro output. The autopilot provides for pilot selection of one of a subset of the plurality of flight modes which is customized based on a current flight status of the helicopter. An automatic autorotation mode is provided.

An actuator includes a housing member configured for connection with a first component, a drive screw connected to the housing member, a rod disposed at least partially in the drive screw and at least partially in the housing member, a retaining nut connected to the rod, a mounting member configured for connection with the first component, and a drive nut engaged with the drive screw and configured for connection with a second component. If the drive screw mechanically disconnects or is fractured, the rod may be configured to translate to engage one or more friction surfaces to restrict back driving of the drive screw.

In an example, a system includes a first controller for controlling a first-flight-control surface, a second controller for controlling a second-flight-control surface, and a first override system including a mechanical linkage between the first controller and the second controller. The first override system is configured such that: (i) while less than a first threshold amount of force is applied to the mechanical linkage, movement of the first controller causes a corresponding movement of the second controller and vice versa, and (ii) while greater than the first threshold amount of force is applied to the mechanical linkage, the first controller and the second controller move separately. The system also includes a second override system operable to permanently disconnect the mechanical linkage responsive to greater than a second threshold amount of force applied to the mechanical linkage. The second threshold amount of force is greater than the first threshold amount of force.

A system and method for actuating one or more high-lift flight control surfaces of an aircraft are disclosed. The system comprises actuators operatively coupled between a driveline and one or more high-lift flight control surfaces associated with a wing of the aircraft. The actuators are configured to cause actuation of the one or more first high-lift flight control surfaces in response to being driven by the first driveline. Each actuator is associated with a no-back device configured to prevent an air load on the one or more high-lift flight control surfaces from driving the one or more high-lift flight control surfaces. The system also comprises a backup brake applicable to the driveline. The backup brake can be applied upon the identification of a developing unsafe condition such as an asymmetry condition between the flight control surfaces of each wing of the aircraft or an uncommanded movement the flight control surfaces.

A transmission or gearbox assembly with fail-safe means for providing redundancy where failure can lead to loss of torque transmission between component parts of the assembly, the assembly comprising a plurality of first components in torque transmitting engagement and at least one second component associated with at least one of the first components, the second component being joined to the respective first component by a discontinuous joint. Preferably, each first component of the system has a corresponding second component joined thereto by a discontinuous joint.