An actuation system for controlling flight control members of a vehicle. Each flight control member is controlled by two or more linear hydraulic actuators. Synchronization members extend between the hydraulic actuators on the same flight control members to synchronize the movements of the hydraulic actuators for consistent movement across the length of the flight control members. Brakes can maintain the positions of the synchronization members and thus the flight control members. Motors can provide for moving the synchronization members to control the positioning of the hydraulic actuators and flight control members.

A crank device provided with an upstream lever and with a downstream lever. The crank device includes a phase shifter system connected to the upstream lever and to the downstream lever so that movement in rotation of the upstream lever about an axis of rotation induces movement in rotation of the downstream lever about the axis of rotation, the phase shifter system comprising a linear actuator mechanism carried by the upstream lever, the linear actuator mechanism having an outlet rod, the outlet rod having only one degree of freedom of movement in translation relative to the upstream lever, the outlet rod being connected via an outlet helical connection to the downstream lever so that movement in translation of the outlet rod generates movement in rotation of the downstream lever about the axis of rotation.

Disclosed herein is an apparatus for determining a position of a first part relative to a second part. The first part is movable relative to the second part. The apparatus comprises a magnetic position indicator and a magnetic field sensor. The magnetic position indicator is non-movably fixed to the first part and comprises a plurality of magnetic field sources positioned along a length of the magnetic position indicator. Each magnetic field source of the plurality of magnetic field sources generates a magnetic field having a unique magnetic signature. The magnetic field sensor is non-movably fixed to the second part and configured to detect the unique magnetic signatures of the magnetic fields generated by the plurality of magnetic field sources of the magnetic position indicator.

A bootstrap hydraulic reservoir includes a bootstrap chamber to hold hydraulic fluid, a piston chamber fluidly connected to a pressure line of the hydraulic fluid system, a piston having a bootstrap end portion held within the bootstrap chamber and a pressure end portion held within the piston chamber, and a hydraulic accumulator fluidly connected to the pressure line of the hydraulic fluid system. The hydraulic accumulator accumulates pressurized hydraulic fluid from the pressure line. The bootstrap hydraulic reservoir also includes a valve fluidly connected to the pressure line of the hydraulic fluid system between the hydraulic accumulator and an outlet of a pump of the hydraulic fluid system. The valve includes an actuator selectively moves the valve to an open position when the pressure line of the hydraulic fluid system is de-pressurized.

A method and apparatus for positioning a control surface. A desired position for the control surface associated with an aerodynamic aircraft structure is identified. The control surface is moved to the desired position using an electronically controlled rotary actuator system located inside of the aerodynamic aircraft structure, wherein a shape of the aerodynamic aircraft structure with the electronically controlled rotary actuator system has a desired aerodynamic performance.

A method and apparatus for positioning a control surface. A desired position for the control surface associated with an aerodynamic aircraft structure is identified. The control surface is moved to the desired position using an electronically controlled rotary actuator system located inside of the aerodynamic aircraft structure, wherein a shape of the aerodynamic aircraft structure with the electronically controlled rotary actuator system has a desired aerodynamic performance.

An actuation system for controlling flight control members of a vehicle. Each flight control member is controlled by two or more linear hydraulic actuators. Synchronization members extend between the hydraulic actuators on the same flight control members to synchronize the movements of the hydraulic actuators for consistent movement across the length of the flight control members. Brakes can maintain the positions of the synchronization members and thus the flight control members. Motors can provide for moving the synchronization members to control the positioning of the hydraulic actuators and flight control members.

An actuation system for controlling flight control members of a vehicle. Each flight control member is controlled by two or more linear hydraulic actuators. Synchronization members extend between the hydraulic actuators on the same flight control members to synchronize the movements of the hydraulic actuators for consistent movement across the length of the flight control members. Brakes can maintain the positions of the synchronization members and thus the flight control members. Motors can provide for moving the synchronization members to control the positioning of the hydraulic actuators and flight control members.

Systems and methods for communicating a signal over a hydraulic line in a vehicle are provided. In one embodiment, a system can include a hydraulic line. The hydraulic line can include at least one communication medium for propagating a communication signal. The system can also include at least one signal communication device configured to receive the communication signal communicated over the hydraulic line. The system can also include at least one vehicle component in communication with the at least one signal communication device.

Embodiments include an apparatus comprising an aircraft wing and a trailing edge aerodynamic surface connected to a trailing edge of the aircraft wing via a piston assembly in which the piston assembly holds the trailing edge aerodynamic surface in a neutral position relative to the aircraft wing at a constant supply pressure. The piston assembly may be implemented using a pneumatic piston or a hydraulic piston. A first end of the piston assembly may be connected to the aircraft wing and a second end of the piston assembly may be connected to the trailing edge aerodynamic surface. The piston assembly may include a pressure relief valve which may open or close, raising or lowering the aerodynamic surface, responsive to lift load on the aircraft wing.