Interior module installation in an aircraft fuselage

Patent metadata

Field	Value
Publication number	US-10870476-B2
Application number	US-201816031802-A
Country	US
Kind code	B2
Filing date	Jul 10, 2018
Priority date	May 27, 2015
Publication date	Dec 22, 2020
Grant date	Dec 22, 2020

Abstract

A method of installing interior modules to support structures in an aircraft fuselage comprises attaching fixed ends of a plurality of tie rods to the support structures; and determining installation length of the tie rods, installation spacing between free ends of the tie rods, and installation orientation of the tie rods prior to positioning the interior module for installation. The method further comprises securing tie rod holding fixtures to the tie rods to hold the spacing and orientation at or near final configuration to facilitate installation of the interior modules.

First claim

What is claimed is:

1. A method of installing interior modules to support structures in an aircraft fuselage, the method comprising:
attaching fixed ends of a plurality of tie rods to the support structures;
determining installation length of the plurality of tie rods, installation spacing between free ends of the plurality of tie rods, and installation orientation of the plurality of tie rods prior to positioning the interior modules for installation; and
securing a tie rod holding fixture to the plurality of tie rods to hold the installation spacing and installation orientation at or near a final configuration to facilitate installation of the interior modules.

2. The method of claim 1 , further comprising installing the interior module to the free ends of the plurality of tie rods while removing the tie rod holding fixture.

3. The method of claim 2 , wherein installing the interior module to the free ends of the plurality of tie rods while removing the tie rod holding fixture comprises installing an overhead stowage bin to the free ends of the plurality of tie rods while removing the tie rod holding fixture.

4. The method of claim 2 , wherein the attaching, determining and securing are performed while the fuselage is progressing through a moving assembly line.

5. The method of claim 4 , wherein a plurality of shops perform work on the fuselage while the fuselage is progressing through the moving assembly line, wherein a first shop of the plurality of shops secures the holding fixtures to the plurality of tie rods, and later, a second shop of the plurality of shops installs the interior modules to the free ends of the plurality of tie rods.

6. The method of claim 5 , wherein securing the holding fixtures to the plurality of tie rods at the first shop comprises attaching the fixed end of the plurality of tie rods to exposed devises attached to the support structures.

7. The method of claim 5 , wherein the first shop uses a beam tool to determine the installation length of the plurality of tie rods, the installation orientation of the plurality of tie rods, and the installation spacing between the free ends of the plurality of tie rods, prior to securing the tie rod holding fixtures.

8. The method of claim 7 , wherein securing the tie rod holding fixtures to the plurality of tie rods at the first shop comprises moving an elevated platform that spans an interior length of the fuselage.

9. The method of claim 7 , wherein the second shop installs the interior modules without using the beam tool.

10. The method of claim 1 , wherein:
the plurality of tie rods includes first and second vertical tie rods and a lateral tie rod; and
securing the tie rod holding fixture to each of the plurality of tie rods comprises securing the tie rod holding fixture to the first and second vertical tie rods and the lateral tie rod of each of the tie rods.

11. The method of claim 10 , wherein:
at least one of the tie rod holding fixtures includes an elongated fixture body having an adjustable length, first and second clasps located at opposite ends of the fixture body, the first and second clasps configured to firmly grasp the vertical tie rods, and a third clasp coupled to the fixture body and configured to firmly grasp the lateral tie rod; and
securing the tie rod holding fixture to the plurality of tie rods comprises securing the first and second clasps to the vertical tie rods and securing the third clasp to the lateral tie rod.

12. The method of claim 11 , wherein the fixture body is collapsible between a stowed position and a deployed position; and wherein the fixture body is moved from the stowed position to the deployed position just prior to securing the tie rod holding fixtures to the plurality of tie rods.

13. The method of claim 12 , wherein:
the fixture body includes first and second segments having respective near ends hinged together by a hinge, and the third clasp is secured to the hinge; and
moving the fixture body from the stowed position to the deployed position comprises moving the first and second segments from a side by side configuration and moving the first and second clasps from a side by side configuration.

14. The method of claim 12 , wherein the fixture body includes a connector, a first arm, a second arm, and a third arm, wherein the first, second and third clasps are at far ends of the first, second and third arms; and wherein moving the fixture body from the stowed position to the deployed position comprises inserting near ends of the first, second and third arms in the connector.

15. The method of claim 14 , wherein the first, second and third arms are tethered to the connector by cords; and wherein moving the fixture body from the stowed position to the deployed position comprises maintaining tethered connection of the first, second, and third arms to the connector using the cords.

16. An aircraft fuselage comprising:
a plurality of support structures;
a plurality of tie rods having fixed ends secured to the support structures; and
a plurality of tie rod holding fixtures, each fixture clamped to a set of tie rods that includes a first vertical tie rod, a second vertical tie rod, and a lateral tie rod, so that each holding fixture holds a predetermined spacing and orientation of free ends of the first vertical tie rod, the second vertical tie rod, and the lateral tie rod of the set of tie rods, each tie rod holding fixture including:
a collapsible fixture body;
first and second clasps at respective ends of the fixture body, the first and second clasps configured to grasp the first and second vertical tie rods of the set of tie rods; and
a third clasp coupled to the fixture body and configured to grasp the lateral tie rod of the set of tie rods.

17. The aircraft fuselage of claim 16 , wherein the first clasp is disposed at a first orientation angle to grasp the first vertical tie rod, the second clasp is disposed at a second orientation angle, different from the first orientation angle, to grasp the second vertical tie rod, the third clasp is disposed at a third orientation angle, different from the first and second orientation angles, to grasp the lateral tie rod.

18. The aircraft fuselage of claim 16 , wherein the collapsible fixture body includes a first segment, a second segment, and a hinge connected between respective near ends of the first and second segments; and wherein the third clasp is secured to the hinge of the fixture body.

19. A method of installing interior modules to support structures in an aircraft fuselage, the method comprising:
attaching fixed ends of a plurality of tie rods to the support structures, the plurality of tie rods including a first vertical tie rod, a second vertical tie rod, and a lateral tie rod;
determining installation length of the plurality of tie rods, installation spacing between free ends of the plurality of tie rods, and installation orientation of the plurality of tie rods prior to positioning the interior modules for installation; and
securing a tie rod holding fixture to the plurality of tie rods to hold the installation spacing and installation orientation at or near a final configuration to facilitate installation of the interior modules, the tie rod holding fixture including:
a collapsible fixture body;
first and second clasps at respective ends of the fixture body, the first and second clasps configured to grasp the first and second vertical tie rods, respectively; and
a third clasp coupled to the fixture body and configured to grasp the lateral tie rod.

Assignees

• Boeing Co

Inventors

• Doran Joseph L
• Hackett Jr Andrew R
• Nadvornick Mark J

Classifications

• B64C1/061 Primary

  Frames · CPC title

• B64D2011/0046

  Modular or preassembled units for creating cabin interior structures · CPC title

• B64D11/003

  Stowage devices for passengers' personal luggage · CPC title