Aircraft actuator hydraulic system

Abstract

A backup hydraulic pump supplies pressure oil to an actuator when a loss or degradation of the function of an aircraft central hydraulic power source occurs. A control valve controls the operation of the actuator by controlling supply and discharge of the pressure oil to/from the actuator. The control valve has a main body provided with a pressure oil port, a spool portion that moves in a sliding manner within the main portion and switches a path of the pressure oil, and a drive portion. The drive portion is connected to an end of the spool portion and drives the spool portion by electromagnetic force so as to control the position of the spool portion based on an electric signal.

What is claimed is: 
     
         1 . An aircraft actuator hydraulic system for driving a moving surface of an aircraft using a hydraulically operated actuator, comprising:
 an actuator that operates as a result of a pressure oil being supplied from an aircraft central hydraulic power source installed in a body of the aircraft and drives the moving surface;   a backup hydraulic pump capable of supplying the pressure oil to the actuator when a loss or degradation of a function of the aircraft central hydraulic power source occurs;   an electric motor that drives the backup hydraulic pump; and   a control valve that is provided on a path that allows the backup hydraulic pump and the aircraft central hydraulic power source to be in communication with the actuator, and controls an operation of the actuator by controlling supply of the pressure oil to the actuator and discharge of the pressure oil from the actuator,   wherein the control valve has a main body provided with a pressure oil port to/from which the pressure oil is supplied and discharged, a spool portion provided so as to be slidable in the main body and capable of switching a path of the pressure oil, and a drive portion that is connected to an end of the spool portion and drives the spool portion by an electromagnetic force so as to control a position of the spool portion based on an electric signal.   
     
     
         2 . The aircraft actuator hydraulic system according to  claim 1 ,
 wherein the backup hydraulic pump, the electric motor, and the control valve are installed inside a wing on which the moving surface is provided in the aircraft.   
     
     
         3 . The aircraft actuator hydraulic system according to  claim 1 ,
 further comprising an actuator controller that controls an operation of the actuator via the control valve by outputting the electric signal to the control valve to drive the drive portion,   wherein the main body of the control valve and a casing of the actuator controller are integrally fixed, or fixed via a common base member.   
     
     
         4 . The aircraft actuator hydraulic system according to  claim 1 ,
 wherein a rotational speed of the backup hydraulic pump, at which the backup hydraulic pump is rotationally driven by the electric motor, can be switched to multiple levels.