Aircraft Wing Panel Reinforcing Part for Stress Distribution
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Solution Overview
Problem
Aircraft wing panels experience significant stress concentration at brackets due to force transmission, leading to localized stress and potential structural issues.
Innovation Solution
A wing panel design featuring a sandwich structure with a core between two skins, incorporating a reinforcing part with a cylindrical tube and stiffener to distribute and diffuse forces, reducing stress concentration and enhancing structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If brackets are used to articulate and actuate the wing panel, then the panel can be actuated relative to adjacent panels or lifting surfaces, but stress concentration occurs at the brackets and assembly means
Solution Approach 1:
The patent applies local quality by introducing a reinforcing part with specific structural features (flank, cylindrical tubes) at the precise location where stress concentration occurs (at the brackets and assembly means). This localized reinforcement modifies the stress distribution characteristics only where needed, without changing the overall panel design or actuation mechanism.
Solution Approach 2:
The reinforcing part is constructed as a composite structure combining a flank (providing structural support) with cylindrical tubes (providing additional reinforcement and stress distribution). This composite approach allows the reinforcement to effectively manage stress concentration while maintaining the actuation functionality of the original bracket system.
2Ease of operation
If assembly means pass through the panel to connect brackets, then the panel can be articulated and actuated, but considerable stress concentration occurs at the assembly means
Solution Approach 1:
The cylindrical tubes act as intermediaries between the assembly means (bolts/nuts) and the panel structure. These tubes surround and reinforce the assembly means, distributing the loads and stresses that would otherwise concentrate at the bolt holes or rivet points, thereby protecting the structural integrity while maintaining ease of assembly and articulation.
Solution Approach 2:
The patent addresses the stress concentration problem by adding a dimensional element - the cylindrical tubes extend in the thickness direction of the panel, providing reinforcement that spans across the stress concentration zone. This three-dimensional reinforcement approach distributes stresses along the tube length rather than concentrating them at a single point in the panel plane.
Data Source
AI summary
A panel for an aircraft wing, having a sandwich structure in which there is arranged a reinforcing part. When the panel is attached to a bracket so as to be articulated to another element, the reinforcing part is provided in order to distribute, over its entire surface, a force transmitted by the bracket to the panel.