Title:
分散型後縁翼フラップシステム
Document Type and Number:
Japanese Patent JP7245643
Kind Code:
B2
Abstract:
A wing flap system (300) for an aircraft, comprising four flaps (112,114,118,120) configured to be moved between respective deployed positions and respective retracted positions, the flaps being configured to be moved relative to fixed trailing edges (110,116) of the wings (102,104) of the aircraft, eight actuators (302,304,306,308,310,312,314,316) configured to move the flaps relative to the fixed trailing edges, respective ones of the actuators being configured to be hydraulically driven via first pressurized hydraulic fluid to be supplied by a first hydraulic system (334) of the aircraft, respective ones of the actuators being configured to be hydraulically driven via second pressurized hydraulic fluid to be supplied by a second hydraulic system (338) of the aircraft; and four local power units, four of the actuators being configured to be independently hydraulically driven via pressurized hydraulic fluid to be supplied by the local power units.
Inventors:
Neil V. Finn
Application Number:
JP2018242755A
Publication Date:
March 24, 2023
Filing Date:
December 26, 2018
Export Citation:
Assignee:
The Boeing Company
International Classes:
B64C13/16; B64C13/42; F15B20/00
Domestic Patent References:
| JP2011519770A |
Foreign References:
| WO2006105048A1 |
Attorney, Agent or Firm:
Minoru Yoshida
Tatsuya Tanaka
Suzuki Yasumitsu
Usui Nao
Shintaro Suzuki
Keita Kobuchi
Tomokazu Saito
Tatsuya Tanaka
Suzuki Yasumitsu
Usui Nao
Shintaro Suzuki
Keita Kobuchi
Tomokazu Saito