Aircraft Leading Edge Panel Overmoulding for Laminar Flow Surface Finish
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Solution Overview
Problem
The manufacturing of aircraft leading edge panels with low surface roughness and tight geometric tolerances is complex and costly, limiting the extension of laminar flow over the wing surface, which increases drag and energy consumption.
Innovation Solution
A method involving overmoulding a coating in a mould with an optimized surface finish to produce aircraft leading edge panels, reducing production costs and achieving high precision without the need for extensive machining.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If machining and shaping processes are used to achieve low surface roughness and tight geometric tolerances on leading edge panels, then manufacturing precision is improved, but device complexity and production costs increase
Solution Approach 1:
The patent replaces traditional mechanical machining processes with a compression molding process. The molding process uses a mold with precision-machined surfaces that directly form the leading edge panel geometry and surface finish in a single step, eliminating subsequent machining operations. This substitution of mechanical machining with molding reduces process complexity while maintaining manufacturing precision.
Solution Approach 2:
The patent performs the surface finishing and geometric precision work in advance during the molding process itself. The mold cavity is pre-machined with the desired surface roughness and geometric tolerances, and this precision is transferred to the panel during molding. This preliminary action eliminates the need for post-molding machining operations.
2Manufacturing precision
If traditional machining processes are used to achieve optimized surface finish on leading edge panels, then manufacturing precision is improved, but productivity decreases and production costs increase
Solution Approach 1:
The patent merges multiple operations into a single compression molding process. The molding operation simultaneously achieves panel shaping, surface finish creation, and geometric precision in one step, rather than requiring separate machining operations. This merging of operations increases productivity while maintaining manufacturing precision.
Solution Approach 2:
The surface finish and geometric precision are created in advance during the molding process before the panel leaves the mold. This preliminary action eliminates time-consuming post-processing machining operations, thereby increasing production efficiency and productivity.
3Manufacturing precision
If extensive machining is performed to achieve low surface roughness, then manufacturing precision is improved, but loss of time increases
Solution Approach 1:
The surface roughness and geometric precision are established in advance during the compression molding process. The mold surfaces are pre-machined with the required precision, and this precision is transferred to the panel during molding. This preliminary action eliminates time-consuming machining operations that would otherwise be required after panel fabrication.
Solution Approach 2:
The patent replaces time-consuming mechanical machining operations with a faster compression molding process. The molding process achieves the same surface roughness and geometric precision in a single operation, significantly reducing the total manufacturing cycle time compared to traditional machining sequences.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The method extends laminar flow, reducing drag by 8% and aviation fuel consumption by 4-5% by achieving a smooth, precise surface finish during the manufacturing process.
Implementation Method 1
overmoulding a coating onto the sheet by injecting a material into the cavity of the mould, the coating comprising, after the overmoulding step, an exterior face which corresponds to the exterior face of the panel that is to be obtained and which exhibits an optimized surface finish conferred by the shaping surface of the mould
Data Source
AI summary
A method for manufacturing an aircraft leading edge panel, includes a step of overmoulding a coating onto a sheet positioned in a cavity of a mould, which cavity is delimited by a shaping surface which exhibits an optimized surface finish. The coating includes, after the overmoulding step, an exterior face which corresponds to the exterior face of the panel that is to be obtained and which exhibits an optimized surface finish conferred by the shaping surface of the mould. A panel may be obtained using this method and a leading edge includes at least one such panel. Because of the optimized surface finish of the exterior surface thereof, the panel contributes to extending the regions of laminar flow.