Landing gear of aircraft and aircraft comprising landing gear

Patent metadata

Field	Value
Publication number	US-2018072437-A1
Application number	US-201715703202-A
Country	US
Kind code	A1
Filing date	Sep 13, 2017
Priority date	Sep 13, 2016
Publication date	Mar 15, 2018
Grant date	—

Abstract

A landing gear of an aircraft of the present invention, includes a core section with a honeycomb structure, including a plurality of cell walls and a plurality of cell holes defined by the plurality of cell walls; a cover section which covers the core section; and a hole provided in the core section to absorb an impact, the hole having a diameter larger than that of the plurality of cell holes and extending in an extending direction of the plurality of cell holes.

First claim

What is claimed is:

1 . A landing gear of an aircraft, the landing gear comprising:
a core section with a honeycomb structure, including a plurality of cell walls and a plurality of cell holes defined by the plurality of cell walls; a cover section which covers the core section; and a hole provided in the core section to absorb an impact, the hole having a diameter larger than that of the plurality of cell holes and extending in an extending direction of the plurality of cell holes.

2 . The landing gear of the aircraft according to claim 1 ,
wherein the core section includes a body provided with the hole and a core bottom section provided between a bottom of the hole and a bottom surface of the core section.

3 . The landing gear of the aircraft according to claim 1 ,
wherein the core section has a shape in which a cross-sectional area in a direction perpendicular to the extending direction of the plurality of cell holes increases from a bottom surface of the core section toward a top surface of the core section.

4 . The landing gear of the aircraft according to claim 1 ,
wherein the core section is a first core section, the landing gear further comprising: a second core section placed on a top surface of the first core section; and a plate section interposed between the first core section and the second core section.

5 . The landing gear of the aircraft according to claim 4 ,
wherein the plurality of cell walls are a plurality of first cell walls, and the plurality of cell holes are a plurality of first cell holes, and wherein the second core section has a honeycomb structure, including a plurality of second cell walls and a plurality of second cell holes defined by the plurality of second cell walls.

6 . The landing gear of the aircraft according to claim 5 ,
wherein the hole is a first hole, and wherein the second core section includes a second hole extending between a top surface of the second core section and a bottom surface of the second core section.

7 . The landing gear of the aircraft according to claim 5 ,
wherein the second core section has a shape in which a cross-sectional area in a direction perpendicular to an extending direction of the plurality of second cell holes increases from the bottom surface of the second core section toward the top surface of the second core section.

8 . An aircraft comprising the landing gear as recited in claim 1 .

9 . An aircraft comprising:
the landing gear as recited in claim 5 ; and a bracket provided in such a manner that the second core section is interposed between the bracket and the plate section, wherein the plate section, the second core section, and the bracket constitute a honeycomb sandwich structure.

Assignees

• Kawasaki Heavy Ind Ltd

Inventors

• Sakamoto Fuminobu
• Kurose Toyotoshi

Classifications

• F16F7/121 Primary

  the members having a cellular, e.g. honeycomb, structure · CPC title

• B64C2025/325

  specially adapted for helicopters · CPC title

• B64G1/62 Primary

  Systems for re-entry into the earth's atmosphere; Retarding or landing devices · CPC title

• B64G1/625

  Landing devices; Undercarriages · CPC title

• B64C1/062

  specially adapted to absorb crash loads · CPC title