Aircraft floor and method of assembly

• US 8,360,362 B2
• Filed: 03/27/2008
• Issued: 01/29/2013
• Est. Priority Date: 02/21/2006
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kismarton, Max U., Westre, Willard N., Buchan, Stuart M.
• Primary Examiner(s): Bonzell, Philip J
• Application Number:
  US12/056,456
• Publication Number:
  US 20080210820A1
• Time in Patent Office: 1,769 Days
• Field of Search: 244/117.R, 244/119, 244/118.2
• US Class Current: 244/117.R
• CPC Class Codes: B64C 1/18 Floors
• CPC Class Codes: B64F 5/10 Manufacturing or assembling aircraft, e.g. jigs therefor

Abstract

The invention relates to aircraft floor assemblies and to methods for their assembly. In one embodiment, an aircraft comprises at least one fuselage section and at least one floor section. At least one system component is installed to the floor section prior to installation of the floor section in the fuselage of the aircraft. In another embodiment, a floor section adapted to be installed in an aircraft includes at least one system component installed to the floor section while it is outside of the aircraft. In yet another embodiment, a method is disclosed for assembling an aircraft. The method comprises installing at least one system component to a floor section, and installing the floor section into a fuselage section of the aircraft.

Claims

1. A method of assembling an aircraft, comprising:

forming a stand-alone floor section having a span extending substantially across the width of the aircraft'"'"'s fuselage by laminating a first higher density structural core and second lower density structural core between top-layer and bottom layer skins with a septum therebetween, including placing the first structural core next to the top-layer skin, placing the septum beneath the first structural core and placing the second structural core beneath the septum and next to the bottom-layer skin;

embedding a hollow tubular mounting structure in at least one of the cores of said floor section;

preassembling a subassembly outside of the aircraft by attaching at least one aircraft system component to the floor section;

said attaching the at least one aircraft system component includes using an attaching structure to attach the at least one aircraft system component to the mounting structure;

moving the subassembly into the fuselage of the aircraft; and

installing the subassembly into the fuselage.

2. The aircraft assembly method of claim 1, wherein preassembling the subassembly is performed at a workstation outside the fuselage.

3. The aircraft assembly method of claim 1, wherein attaching at least one aircraft system component to the floor section comprises attaching at least one of a seat, a duct, an electrical system, an electrical box, electrical wiring, a control system, a lighting system, an entertainment system, carpeting, a seat track, a cable, a housing, a flight control, and a panel.

4. The aircraft assembly method of claim 1, wherein laminating the first higher density structural core and second lower density structural core comprises laminating a first core having a density approximately 3 to 5 times greater than a density of the second core.

5. The aircraft assembly method of claim 1, wherein laminating the first higher density structural core comprises laminating a core having a thickness of approximately 0.1 inches and a density in the range of approximately 3 pounds per cubic foot to 10 pounds per cubic foot, and laminating the second lower density structural core comprises laminating a core having a thickness of approximately 0.4 inches and a density in the range of approximately 2 pounds per cubic foot to 3 pounds per cubic foot, and wherein the first and second cores comprise at least one of Nomex®

and Kevlar®

.

6. The aircraft assembly method of claim 1, wherein laminating the first and second structural cores between top-layer and bottom layer skins comprises laminating a top-layer skin having a thickness in a range of approximately 0.03 inches to 0.08 inches, and a bottom-layer skin having a thickness in a range of approximately 0.02 inches to 0.08 inches, and at least one of the top-layer and bottom-layer sheets comprises at least one of a titanium foil sheet, a titanium-CFRP laminate, a fiberglass laminate, a carbon-fiber reinforced plastic sheet, a thermoplastic sheet, and a thermoplastic resin.

7. The aircraft assembly method of claim 1, wherein placing the septum beneath the first structural core comprises placing a septum having a thickness in the range of approximately 0.005 inches to 0.03 inches, the septum comprising at least one of:

a titanium foil sheet, a titanium-CFRP laminate, a fiberglass laminate, a carbon-fiber reinforced plastic sheet, a thermoplastic sheet, and, a thermoplastic resin.

8. The aircraft assembly method of claim 1, wherein embedding the hollow tubular mounting structure in at least one of the cores comprises embedding a hollow tubular mounting structure having a plurality of through holes therein respectively representing a plurality of locations at which the aircraft system component may be attached.

9. The aircraft assembly method of claim 1, wherein using an attaching structure to attach the at least one aircraft system component to the mounting structure comprises using a bracket for attaching the aircraft system component to the bottom of the floor section.

10. The aircraft assembly method of claim 1, further comprising attaching a first carbon plank along a length of the floor section above the hollow tubular mounting structure, the first carbon plank having a width greater than a width of the hollow tubular mounting structure.

11. The aircraft assembly method of claim 10, further comprising attaching a second carbon plank along a length of the floor section below the hollow tubular mounting structure.