Title:
航空機アクチュエータの油圧システム
Document Type and Number:
Japanese Patent JP5658117
Kind Code:
B2
Abstract:
A first actuator (14a) drives a control surface (103a) by being operated by supply of pressure oil from a first aircraft central hydraulic power source (104) including a first aircraft central hydraulic pump (104a) . A second actuator (14b) drives the control surface by being operated by supply of pressure oil from a second aircraft central hydraulic power source (105) including a second aircraft central hydraulic pump (105a) . A backup hydraulic pump (18) is installed inside a wing (102a) of the aircraft (100) and is provided so as to be able to supply pressure oil to the first actuator (14a) when a loss or degradation in a function of at least one of the first aircraft central hydraulic power source (104) and the second aircraft central hydraulic power source (105) occurs. A maximum discharge pressure of the backup hydraulic pump (18) is set to be greater than maximum discharge pressures of the first aircraft central hydraulic pump (104a) and the second aircraft central hydraulic pump (104b).
Inventors:
福井 淳
高木 憲優
高木 憲優
Application Number:
JP2011210135A
Publication Date:
January 21, 2015
Filing Date:
September 27, 2011
Export Citation:
Assignee:
ナブテスコ株式会社
International Classes:
B64C13/42; F15B20/00
Attorney, Agent or Firm:
Patent business corporation Wang Dee IP partners