| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide an electric actuator for an aircraft which can be used suitably without causing fault even in case that the electric motor of an electric actuator is made to output power, in condition that it is stopped in some position such that the rudder face is held in a fixed position in condition that aerodynamical power load is applied, etc. <P>SOLUTION: It is so arranged as to prevent a current from flowing concentratively to the coil of some phase of an electric motor, thereby preventing the concentrated temperature rise of the fixed phase of coil and preventing burning, etc., by outputting a control signal over the responsiveness of the electric actuator 1 to a three-phase coil by means of a control means 5, in case that the actuator 1 is operated in condition that it is positioned in a specified position and load is applied. <P>COPYRIGHT: (C)2004,JPO |
