Transport element support system

Patent metadata

Field	Value
Publication number	US-11447229-B2
Application number	US-201815933784-A
Country	US
Kind code	B2
Filing date	Mar 23, 2018
Priority date	Mar 23, 2018
Publication date	Sep 20, 2022
Grant date	Sep 20, 2022

Abstract

A transport element support system comprising a first portion, a second portion, and a channel formed by the first portion and the second portion. The first portion has a hinge pin and the second portion has a receiving element. The receiving element is configured to engage with the hinge pin to couple the first portion to the second portion. The channel is configured to receive a transport element when the first portion and the second portion are coupled to each other. The transport element support system electrically isolates the transport element from a support structure in an aircraft.

First claim

What is claimed is:

1. A transport element support system that comprises:
a first portion that comprises:
a base of the first portion; and
a hinge pin that comprises segments separated by a rib;

a second portion that comprises:
a dielectric material;
a receiving element that comprises a groove, respectively, for each segment of the segments of the hinge pin, configured to engage with the hinge pin and rotate into a coupled position that couples the first portion to the second portion; and
a cutout configured to receive, in the coupled position, the base of the first portion; and

a channel formed by the first portion and the second portion, wherein the channel is configured to receive a transport element with the first portion and the second portion in the coupled position.

2. The transport element support system of claim 1 further comprising:
an insert positioned within the channel, wherein the insert is configured to surround a periphery of the transport element and stabilize the transport element within the channel.

3. The transport element support system of claim 2 , wherein the first portion, and the insert each comprise a second dielectric material.

4. The transport element support system of claim 3 , wherein the insert comprises:
a dielectric sleeve configured to open to receive the transport element and close around the transport element.

5. The transport element support system of claim 3 , wherein the second portion comprises:
a cutout; and
a number of ribs.

6. The transport element support system of claim 5 , wherein the first portion comprises a number of ribs.

7. The transport element support system of claim 1 , wherein the hinge pin and the receiving element are configured to share loads placed on the transport element support system during operation in an aircraft.

8. The transport element support system of claim 7 , wherein the hinge pin comprises:
a first segment; and
a second segment, wherein the first segment and the second segment are separated by one of the number of ribs in the first portion of the transport element support system.

9. The transport element support system of claim 8 , wherein the receiving element comprises:
a first groove configured to receive the first segment of the hinge pin;
a second groove configured to receive the second segment of the hinge pin; and
a gap between the first groove and the second groove.

10. The transport element support system of claim 1 , wherein the first portion is configured to rotate about the hinge pin and over an insert to interface with the second portion.

11. The transport element support system of claim 1 , wherein the second portion is configured to directly connect to a single support structure in an aircraft.

12. A method for stabilizing a transport element in an aircraft, the method comprising:
positioning an insert around a periphery of the transport element;
forming a transport element support system via coupling a first portion comprising a base to a second portion comprising a cutout via:
engaging a hinge pin, comprising segments separated by a rib, in the first portion with grooves in a receiving element on the second portion;
positioning the insert around the transport element onto an engagement surface of the second portion; and
rotating the first portion about the hinge pin and over the transport element to interface with the second portion such that:
the transport element sits within a channel formed by the first portion and the second portion; and
the base of the first portion sits within a cutout in the second portion.

13. The method of claim 12 further comprising:
fastening the transport element support system directly to a single support structure such that the transport element support system electrically isolates the transport element from the single support structure.

14. The method of claim 12 , wherein engaging the hinge pin with the receiving element comprises:
engaging a first segment of the segments of the hinge pin with a first groove in the grooves in the receiving element; and
engaging a second segment of the segments of the hinge pin with a second groove in the grooves in the receiving element.

15. The method of claim 12 , wherein the insert comprises a dielectric sleeve and positioning the insert comprises:
opening the dielectric sleeve to receive the transport element; and
closing the dielectric sleeve around the periphery of the transport element.

16. An aircraft that comprises:
a support structure;
a transport element aligned parallel to the support structure; and
a transport element support system that comprises:
a first portion that comprises:
a base of the first portion; and
a hinge pin that comprises segments separated by a rib;

a second portion that comprises:
a dielectric material;
a receiving element that comprises a groove, respectively, for each segment of the segments of the hinge pin, configured to engage with the hinge pin and rotate into a coupled position that couples the first portion to the second portion; and
a cutout configured to receive, in the coupled position, the base of the first portion; and

a channel formed by the first portion and the second portion in the coupled position, wherein the channel is configured to receive the transport element with the first portion and the second portion in the coupled position.

17. The aircraft of claim 16 , wherein the transport element support system further comprises:
an insert positioned within the channel, wherein the insert surrounds a periphery of the transport element to stabilize the transport element within the channel.

18. The aircraft of claim 17 , wherein the first portion and the insert each comprise a second dielectric material.

19. The aircraft of claim 16 , wherein the second portion is configured to directly connect to the support structure, and wherein the second portion comprises a second number of ribs.

20. The aircraft of claim 19 , wherein the first portion comprises a first number of ribs.

Assignees

• Boeing Co

Inventors

• Gilbertson Michael Leslie
• Carpenter Mark L

Classifications

• F16L3/015

  using articulated- or supple-guiding elements · CPC title

• F16L3/1083

  with two members, the two members being hooked in on one side and fastened together on the other side · CPC title

• H02G3/36

  Installations of cables or lines in walls, floors or ceilings · CPC title

• H02G3/22

  Installations of cables or lines through walls, floors or ceilings, e.g. into buildings · CPC title

• F17C5/06

  for filling with compressed gases · CPC title