Aircraft floor and method of assembly
First Claim
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.
1 Assignment
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Accused Products
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.
35 Citations
11 Claims
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1. A method of assembling an aircraft, comprising:
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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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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Specification