Integrated Aerodynamic Panel Weight Reduction via Component Merging
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Solution Overview
Problem
Traditional aircraft aerodynamic panel assemblies are complex, heavy, and costly due to the large number of components and fasteners required for assembly.
Innovation Solution
An integrated aerodynamic panel design with reduced components, featuring a first panel region, a second panel region with decreasing thickness, a splice plate region, and a filler region that is flush with the outer mold line, allowing for simplified attachment via a reduced number of fasteners.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a traditional panel assembly with multiple components and fasteners is used, then the structural integrity and reliability are maintained, but the weight, cost, and assembly time increase
Solution Approach 1:
The patent merges the secondary panel, splice plate, and filler into a single integrated aerodynamic panel structure. The first panel region, second panel region with decreasing thickness, and filler region are combined in one piece, eliminating the need for separate components and fasteners while maintaining structural integrity through the integrated design
Solution Approach 2:
The invention extracts and eliminates the unnecessary intermediate components (separate splice plate and filler) from the traditional panel assembly. By taking out these redundant elements, the design achieves weight reduction while the remaining integrated structure maintains the necessary structural function through its optimized geometry
2Reliability
If a traditional panel assembly with multiple components is used, then the structural integrity is maintained, but the assembly complexity and number of fasteners increase
Solution Approach 1:
The patent combines multiple separate components (secondary panel, splice plate, filler) into a single integrated aerodynamic panel with continuous aerodynamic surface. This merging reduces the component count to essentially one piece while maintaining structural integrity through the integrated design
Solution Approach 2:
The integrated panel is segmented into functional regions (first panel region, second panel region with decreasing thickness, splice plate region, filler region) that are optimized for different functions while remaining part of a single continuous structure, allowing simplified assembly
3Reliability
If a traditional panel assembly with multiple fasteners is used, then the connection reliability is maintained, but the assembly time and cost increase
Solution Approach 1:
The patent merges the functions of multiple fasteners into a single integrated structure. The splice plate region and filler region are integrated into the panel itself, eliminating the need for multiple separate fasteners and reducing assembly time while maintaining connection reliability through the integrated design
Data Source
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AI summary
An integrated aerodynamic panel (200) - e.g., for a trailing edge or leading edge of an aircraft aerodynamic surface - includes a first panel region (202) defining inner (124) and outer (126) mold lines, and a second panel region (204) contiguous with and extending from the first panel region in a tapering fashion. A splice plate region (206) extends from the second panel region and includes an edge band region (104) configured to accept a fastener (108). A filler region (203) (e.g., a SYNCORE or fiberglass structure) adjacent the second panel region has an exposed surface (214) substantially flush with the outer mold line.