Control actuation system including staged direct drive valve with fault

Abstract

A control actuation system for an aircraft including an electromechanically controlled, hydraulically powered actuator for driving a main control valve of a dual hydraulic servo-actuator control system. The actuator includes a tandem piston connected to the main control valve which is controllably positioned by a staged valve of relatively short stroke whereby a force motor of minimum size and energy requirements may be used to directly drive the valve. The staged valve includes a linearly movable valve plunger for simultaneously controlling the differential application of fluid pressure from respective hydraulic systems on opposed pressure surfaces of respective piston sections to cause movement of the piston in response to relatively short axial movement of the valve plunger as long as at least one hydraulic system remains operative. Also, the staged valve includes a fault control valve sleeve concentric with the valve plunger which, upon shut-down or failure of both hydraulic systems, moves linearly to render the valve plunger inoperative and release fluid pressure from opposed, corresponding pressure surfaces of the tandem piston to respective returns therefor through respective centering rate control orifices in the fault control valve sleeve as the piston is moved to a neutral position by a centering spring device acting on the main control valve.