Abstract: A rotary hydraulic actuator may be configured to output rotary motion to control a hinged surface of an aircraft. The actuator includes a nested ballscrew, ballnut, and output assembly that form concentric ball races for converting the linear motion and force of the linear actuator to rotary motion and torque of the output assembly that is connected to the hinged surface. One of the ball races is helically inclined and the other of the ball races is linear. The rotary hydraulic actuator may include a ball return structure that returns the balls from a loaded path of a ball race to an unloaded path of the ball race. The ball return structure may define a ball return path that is located at the same radial distance from the actuator centerline as the loaded path for minimizing the overall diameter of the actuator.

Abstract: A rotary hydraulic actuator may be configured to output rotary motion to control a hinged surface of an aircraft. The actuator includes a nested ballscrew, ballnut, and output assembly that form concentric ball races for converting the linear motion and force of the linear actuator to rotary motion and torque of the output assembly that is connected to the hinged surface. One of the ball races is helically inclined and the other of the ball races is linear. The rotary hydraulic actuator may include a ball return structure that returns the balls from a loaded path of a ball race to an unloaded path of the ball race. The ball return structure may define a ball return path that is located at the same radial distance from the actuator centerline as the loaded path for minimizing the overall diameter of the actuator.

Abstract: Vehicles commonly include control-surfaces and other components that are selectively moved during operation among a plurality of positions. Movement of aircraft control-surface components is crucial in flight, and an actuating assembly must consistently and dependably perform during normal operation and be prepared to survive situations outside normal operation and/or to compensate for circumstances causing loss of actuator control. Jam tolerant electromechanically operated actuation systems, of both the rotary and linear types, together with their methods of operation are described herein. Specifically, electrical jam-detection and control systems and associated locking and damping devices can be electrically and mechanically engaged and disengaged, are automatically reversible, and are testable.

Abstract: Vehicles commonly include control-surfaces and other components that are selectively moved during operation among a plurality of positions. Movement of aircraft control-surface components is crucial in flight, and an actuating assembly must consistently and dependably perform during normal operation and be prepared to survive situations outside normal operation and/or to compensate for circumstances causing loss of actuator control. Jam tolerant electromechanically operated actuation systems, of both the rotary and linear types, together with their methods of operation are described herein. Specifically, electrical jam-detection and control systems and associated locking and damping devices can be electrically and mechanically engaged and disengaged, are automatically reversible, and are testable.