Title:
セミレバー式収縮着陸装置
Document Type and Number:
Japanese Patent JP7120808
Kind Code:
B2
Abstract:
A shrink mechanism (300) for use with a landing gear (200A) of an aircraft (100) is provided. The landing gear includes an outer sleeve (310) at least partially surrounding a shock strut (210), the shrink mechanism has a shaft (312) rotatably coupled to the outer sleeve about a shaft rotation axis (314), the shaft being disposed perpendicular to a centerline (316, 316') of the shock strut, an anchor arm (318) coupled to the shaft, the anchor arm being configured to couple to a structure (320) within a wing (322) of the aircraft, a shrink arm (324) coupled to the shaft, the shrink arm and the anchor arm being coupled to the shaft so as to rotate as a unit with the shaft about the shaft rotation axis, and a shrink link (326) rotatably coupled to the shrink arm, the shrink link being configured to rotatably couple to the shock strut.
Inventors:
Bruce A Dahl
Sakurai
Sakurai
Application Number:
JP2018098651A
Publication Date:
August 17, 2022
Filing Date:
May 23, 2018
Export Citation:
Assignee:
The Boeing Company
International Classes:
B64C25/60
Domestic Patent References:
| JP63028797A | ||||
| JP6219394A | ||||
| JP6008886A | ||||
| JP54022679B1 | ||||
| JP60071394A |
Foreign References:
| US2754072 |
Attorney, Agent or Firm:
Murayama Yasuhiko
Tatsuhiko Abe
Shinpei Kuroda
Choe Yun
Tatsuhiko Abe
Shinpei Kuroda
Choe Yun