Patent ID: 7789345
Filing Date: 2010-09-07
Classification: G05B

Abstract:
1. An actuator control system, comprising a plurality of actuators for driving one flight control surface of an aircraft; a plurality of actuator control apparatuses being installed for each of said actuators, and producing a control signal used to control said each of actuators; and a flight control computer producing an instruction signal used to control said actuator control apparatuses, each of said actuator control apparatuses comprising: said flight control computer controls said switching means so that said primary control signal is transmitted to said actuator as said control signal when a number of said slave instruction means having said flight control surface drive said actuator is not above a predetermined number, and controls said switching means so that said secondary control signal is transmitted to said actuator as said control signal when the number of said slave instruction means having said flight control surface drive said actuator is above said predetermined number, each of said slave instruction means having a monitoring section to monitor faults of said actuators and to transmit a monitoring signal to said flight control computer, and a solenoid valve driver to transmit a slave instruction signal to a solenoid valve equipped on one of said actuators being in fault, and said monitoring section monitoring the faults on the basis of said instruction signal supplied from said flight control computer, and feedback signals supplied from said actuators.