| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide an aircraft actuator hydraulic apparatus, which can drive an actuator even in the case of a loss or degradation of the function of the aircraft hydraulic power source, which can prevent a decrease in efficiency of the body of an aircraft, which can suppress an increase in temperature of the apparatus, and which can achieve miniaturization and weight reduction of the configuration of the apparatus. <P>SOLUTION: A backup hydraulic pump 11 is installed inside a wing 102 at which an elevator 103 is provided, and supplies pressure oil to an actuator 104a when a loss or degradation occurs in the function of aircraft hydraulic power sources (105, 106). An electric motor 12 is installed inside the wing 102 and drives the backup hydraulic pump 11. A driver 13 is installed inside the wing 102 and drives the electric motor 12. A cooling device 14 is installed inside the wing 102 and simultaneously cools the backup hydraulic pump 11, the electric motor 12, and the driver 13. <P>COPYRIGHT: (C)2012,JPO&INPIT |
