| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a hydraulic apparatus for an aircraft actuator capable of driving the actuator even when the function of an airframe side hydraulic source is lost or degraded, reducing the size and the weight of the constitution of the hydraulic apparatus, and suppressing the temperature rise of the apparatus and hydraulic fluid. <P>SOLUTION: There are provided a pump unit 12 installed inside a wing 102, and a panel body constituting a part of a wing structure portion 112 forming a surface structure of the wing 102. The pump unit 11 includes a backup hydraulic pump 13 which is installed on an airframe 101 side to supply pressure oil to an actuator 104a when the function of an airframe side hydraulic source 105 to supply pressure oil to the actuator 104a is lost or degraded, and an electric motor 14 that drives the pump 13. Except at least the panel body 11, the wing structure portion 112 is formed of fiber reinforced plastics. The panel body 11 is formed of a metallic material. <P>COPYRIGHT: (C)2012,JPO&INPIT |
