Wing Spar Fitting Attachment Without Sealed Area Penetration

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Solution Overview

Problem

Current aircraft assembly processes are inefficient and costly due to the need for complex wing-to-body joint assembly methods that require penetration of sealed areas, leading to delayed fuel tank sealing and increased assembly time and costs.

Innovation Solution

A method and apparatus using a mechanical joint formed by a wing spar fitting and a body frame fitting connected with fasteners, allowing for attachment without penetrating sealed areas, facilitating preassembly and testing of sub-assemblies and reducing weight.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Weight of moving object

If shear fasteners are used to attach wing to body, then aircraft weight is reduced, but assembly time increases and sub-assembly testing is not possible

Engineering Contradiction:

Improveaircraft weightVSAvoidassembly time

Core Design Contradiction:

Weight of moving objectVSLoss of time

Solution Approach 1:

The joint assembly is segmented into modular components: a wing spar fitting attached to the wing sub-assembly, and a body frame fitting attached to the body. This segmentation allows the wing sub-assembly to be pre-assembled and tested independently with the spar fitting, then quickly connected to the body via the body frame fitting, reducing both weight compared to solid pins and assembly time compared to multiple shear fasteners.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The wing spar fitting is pre-attached to the wing sub-assembly before final assembly with the body. This preliminary action enables leak testing and functional testing of the wing sub-assembly (including fuel tanks) to be completed before the wing is attached to the body, eliminating rework and delays that would occur if testing had to wait until final assembly.

Inventive Principle:

Principle #10Preliminary action

2Weight of moving object

If shear fasteners are used to attach wing to body, then aircraft weight is reduced, but fuel tank sealing is delayed and assembly complexity increases

Engineering Contradiction:

Improveaircraft weightVSAvoidassembly complexity

Core Design Contradiction:

Weight of moving objectVSDevice complexity

Solution Approach 1:

Inventive Principle:

Principle #1Segmentation

3Loss of time

If a large pin is used for wing front spar to body frame joint, then assembly is quick and sub-assembly testing is enabled, but aircraft weight increases

Engineering Contradiction:

Improveassembly timeVSAvoidaircraft weight

Core Design Contradiction:

Loss of timeVSWeight of moving object

Solution Approach 1:

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Inventive Principle:

Principle #10Preliminary action

4Reliability

If wing is assembled before attaching to body, then sub-assembly testing can be performed, but sealed areas must be penetrated during attachment

Engineering Contradiction:

Improvesub-assembly testingVSAvoidpenetration of sealed areas

Core Design Contradiction:

ReliabilityVSObject-affected harmful factors

Solution Approach 1:

The wing spar fitting acts as an intermediary component that connects the wing sub-assembly to the body frame fitting. This intermediary allows the wing sub-assembly to be pre-assembled and tested with the fitting in place, then connected to the body without requiring penetration of sealed fuel tank areas, as the connection is made through the fitting structure itself rather than through the wing skin.

Inventive Principle:

Principle #24Intermediary (Mediator)

Data Source

PatentUS8016236B2Method and apparatus for attaching a wing to a body

Publication Date: 2011.09.13 THE BOEING CO

AI summary

A method and apparatus for assembling an aircraft. A wing spar fitting is connected to a spar in a wing for the aircraft. A body frame fitting is connected to a frame in a body for the aircraft. The locations and orientations of the body frame fitting and the wing spar fitting allow for the body frame fitting to be attached to the wing spar fitting when the wing is positioned for attachment to the body of the aircraft. The wing is positioned with respect to the body of the aircraft for attachment to the body. The body frame fitting and the wing spar fitting are attached to each other with a set of fasteners after the body frame fitting is aligned to the wing spar fitting without penetrating any sealed areas in the wing, wherein the wing is attached to the body by a mechanical joint that is formed by the body frame fitting and the wing spar fitting.