Aircraft Joint Assembly Single Main Fitting Design
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Solution Overview
Problem
Existing aircraft joint assemblies are complex, expensive, time-consuming to manufacture, and heavy due to multiple components and fasteners, and can generate undesirable moments or torque when loads are applied, particularly with rear spar bulkhead fitting components having large gaps between prongs.
Innovation Solution
A joint assembly featuring a single main fitting with three flanges that couples an external spar component, an internal spar component, and a body rib using fasteners, providing a substantially vertical load path and preventing torque generation, with a solid design and reduced number of components and fasteners.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If multiple components and fasteners are used to assemble the joint assembly, then the structural integrity and load-bearing capacity are improved, but the manufacturing cost, assembly time, and weight increase
Solution Approach 1:
The patent combines multiple separate components (bulkhead fitting, spar fittings, reinforcement plates) into a single integrated main fitting with multiple flanges. This merging reduces the number of parts and fasteners while maintaining structural integrity through the unified design that distributes loads across multiple flange connections.
Solution Approach 2:
The main fitting serves multiple functions simultaneously: it connects the bulkhead, external spar, internal spar, and reinforcement structure through its different flanges. This multi-functional design eliminates the need for separate connection components for each attachment point, reducing overall assembly complexity.
2Strength
If multiple components and fasteners are used to assemble the joint assembly, then the structural integrity and load-bearing capacity are improved, but the manufacturing time and assembly time increase
Solution Approach 1:
By integrating multiple connection functions into a single main fitting component, the patent reduces the number of assembly steps. Instead of assembling multiple separate fittings and fasteners, the unified design allows for fewer installation operations while achieving the same structural integrity.
3Strength
If multiple components and fasteners are used to assemble the joint assembly, then the structural integrity and load-bearing capacity are improved, but the weight increases
Solution Approach 1:
The patent reduces joint assembly weight by merging multiple separate metal components into a single optimized main fitting. This eliminates the weight of redundant parts and fasteners while maintaining structural integrity through the efficient load-distributing flange design.
4Device complexity
If a rear spar bulkhead fitting component with two prongs separated by a large gap is used, then the manufacturing and assembly simplicity is improved, but the torque and moment induced under load increase
Solution Approach 1:
The patent merges the two separate prongs into a solid, continuous main fitting structure. This eliminates the gap between prongs, preventing the formation of moments and torque under load while maintaining manufacturing simplicity through the integrated design.
Data Source
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AI summary
A joint assembly for an aircraft is provided. The joint assembly includes a single main fitting including a first flange, a second flange, and a third flange, an external spar component coupled to the first flange using at least one fastener, an internal spar component coupled to the second flange using at least one fastener, and a body rib coupled to the third flange using at least one fastener.