Method for cavity noise reduction

Patent metadata

Field	Value
Publication number	US-10196125-B2
Application number	US-201715594929-A
Country	US
Kind code	B2
Filing date	May 15, 2017
Priority date	Mar 13, 2013
Publication date	Feb 5, 2019
Grant date	Feb 5, 2019

Abstract

A stretchable mesh material extends across the opening of a cavity of the landing gear of an aircraft when the landing gear is in the deployed position. The mesh material alters the flow of air across the opening of the landing gear cavity and significantly reduces the amount of noise produced by the wheel well at low-to-mid frequencies.

First claim

The invention claimed is:

1. A method of reducing noise generated in connection with a landing gear cavity of an aircraft having a deployable landing gear assembly that moves from a stowed configuration substantially within the cavity to a deployed configuration wherein at least a portion of the landing gear assembly extends out of the cavity, and having an edge defining an opening to the cavity, the method comprising:
providing an elastic membrane;
securing the elastic membrane to at least a portion of the edge;
configuring the elastic membrane so the elastic membrane extends over at least a substantial portion of the opening when the landing gear assembly is in the deployed configuration and alters air flow across the opening to reduce noise from the opening while the landing gear assembly is in the deployed configuration.

2. The method of claim 1 , wherein:
the elastic membrane comprises a mesh material having a plurality of openings.

3. The method of claim 2 , wherein:
the plurality of openings are disposed in rows.

4. The method of claim 2 , including:
stretching the mesh material when the mesh material extends over the opening to the cavity.

5. The method of claim 4 , wherein:
the opening to the cavity defines a leading edge; and including:
securing the mesh material along at least the leading edge of the opening.

6. The method of claim 5 , including:
connecting a portion of the mesh material to the landing gear assembly.

7. The method of claim 2 , wherein:
the openings through the mesh material are formed by a plurality of strands of material extending in a first direction and a second direction that is transverse to the first direction.

8. The method of claim 7 , wherein:
the openings have a homogeneous mesh spacing.

9. The method of claim 8 , wherein:
the mesh spacing is in a range of about 1.5 to about 3,0 meshes per inch.

10. The method of claim 8 , wherein:
The mesh thickness defines a thickness, and wherein the thickness is about 0.1 inches or less.

11. The method of claim 7 , Wherein:
the strands of material comprise nylon and spandex materials.

12. The method of claim 1 , wherein:
the elastic membrane promotes growth of three-dimensional flow structures within a free sheer layer at the opening to the cavity.

13. The method of claim 12 , wherein:
the edge defines a leading edge portion, and the three-dimensional flow structures generated by the membrane reduce the shear layer roll-up process and diminish or eliminate spanwise coherence of large-scale flow structures immediately downstream of the leading edge portion.

14. The method of claim 1 , wherein:
the edge defines a leading edge portion; and including:
securing a first portion of the elastic membrane to the aircraft structure along the leading edge portion.

15. The method of claim 14 , including:
connecting a second portion of the elastic membrane to the landing gear assembly;
wherein the second portion moves with the landing gear assembly as the landing gear assembly is moved between the deployed and stowed configurations.

16. The method of claim 1 , wherein:
the elastic membrane comprises a substantially impermeable layer of elastomeric material.

17. The method of claim 1 , wherein:
the elastic membrane comprises a woven fabric.

18. The method of claim 1 , wherein:
the elastic membrane is pretensioned.

Assignees

• The Us Administrator Of The Nasa
• Nasa

Inventors

• Khorrami Mehdi R

Classifications

• B64C25/16

  Fairings movable in conjunction with undercarriage elements · CPC title

• B64C25/12 Primary

  sideways · CPC title

• B64C1/403 Primary

  Arrangement of fasteners specially adapted therefor, e.g. of clips · CPC title

• B64C2025/003

  Means for reducing landing gear noise, or turbulent flow around it, e.g. landing gear doors used as deflectors · CPC title