Mounting systems including load-bearing attachment assemblies and methods for mounting structures to an aircraft

Patent metadata

Field	Value
Publication number	US-10487864-B2
Application number	US-201615040197-A
Country	US
Kind code	B2
Filing date	Feb 10, 2016
Priority date	Feb 10, 2016
Publication date	Nov 26, 2019
Grant date	Nov 26, 2019

Abstract

A load-bearing attachment assembly is provided for mounting a structure to an aircraft. The load-bearing attachment assembly comprises a male fastening component and a female fastening component. The male fastening component comprises a radially-extending head, a first aperture, and a cylindrical portion extending perpendicular to the radially-extending head. The cylindrical portion has a first threaded portion circumferentially disposed on an outer surface of the cylindrical portion. The radially-extending head comprises a first clamping surface. The female fastening component comprises an annulus enclosing a second aperture, a second clamping surface disposed on the annulus, and a second threaded portion circumferentially disposed on an inner surface perpendicular to the second clamping surface. The first aperture and the second aperture are configured for a fastener to extend therethrough. In response to rotation of the fastener, first clamping surface translates toward second clamping surface.

First claim

What is claimed is:

1. A mounting system comprising:
a male fastening component comprising a radially-extending head, a first aperture, a cylindrical portion extending perpendicular to the radially-extending head, and a chamfer portion extending from the radially extending head to the cylindrical portion, the cylindrical portion having a first threaded portion circumferentially disposed on an outer surface of the cylindrical portion, an inboard surface of the radially-extending head comprising a first clamping surface, wherein the radially-extending head comprises a flat head, and wherein the first clamping surface is a first planar surface; and
a female fastening component comprising an annulus enclosing a second aperture, at least two openings disposed on the annulus and configured to provide tooling access during assembly, a second clamping surface disposed on the annulus having a second planar surface extending from the second aperture to a perimeter of the annulus, and a second threaded portion circumferentially disposed on an inner surface perpendicular to the second clamping surface, and wherein the second planar surface is parallel to the first planar surface; and
a structure to an aircraft having a mounting portion comprising a substantially flat mounting portion including a mounting opening that extends from the first side to the second side thereof, the mounting opening defining an inner surface, the female fastening component being cooperatively engaged with the male fastening component through the mounting opening, the chamfer portion disposed within the mounting opening and separated from the inner surface, the clamping surface engaging the substantially flat mounting portion, and a fastening extending through the male fastening component, the female fastening component, and the mounting portion of the structure.

2. The mounting system of claim 1 , wherein the first threaded portion is configured to be cooperatively engaged with the second threaded portion of the female fastening component.

3. The mounting system of claim 1 , wherein an outboard side of the annulus comprises the second clamping surface wherein the first threaded portion of the male fastening component and the second threaded portion of the female fastening component have complementary threads configured for cooperative engagement.

4. The mounting system of claim 3 , wherein the male fastening component is configured to be at least partially positioned on a first side of the mounting portion of the structure and the female fastening component is configured to be at least partially positioned on a second side of the mounting portion, wherein the first clamping surface of the male fastening component and the second clamping surface of the female fastening component are configured for damping the mounting portion therebetween upon mounting the -to the aircraft, thereby transferring load to the female fastening component that is disposed against the aircraft.

5. The mounting system of claim 1 , wherein the structure further comprises at least one of a panel or a compartment.

6. The mounting system of claim 5 , wherein the structure comprises a packboard compartment and the mounting portion comprises a flange portion of the packboard compartment.

7. The mounting system of claim 1 , wherein the at least two openings extend through the annulus.

8. The mounting system of claim 1 , wherein the second clamping surface is a knurled surface.

Assignees

• Goodrich Corp

Inventors

• Schmidt Ryan
• Baglini Jr James

Classifications

• F16B5/01

  by means of fastening elements specially adapted for honeycomb panels · CPC title

• F16B5/02

  by means of fastening members using screw-thread ({F16B5/0004 takes precedence}; construction of screw-threaded connections F16B25/00 - F16B39/00) · CPC title

• F16B5/0621 Primary

  in parallel relationship (fastened by a drive-pin F16B19/1081; fastened by a device locking by rotation F16B21/02) · CPC title