Aircraft Wing Trailing Edge Heat Shielding Composite
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircraft wing trailing edges are vulnerable to the high-temperature efflux from modern, efficient jet engines, leading to reduced ultimate tensile strength and potential structural integrity issues, with existing solutions either inadequate in temperature protection or costly and maintenance-intensive.
Innovation Solution
A composite material for aircraft wing components featuring a metal matrix with reinforcing materials and a surface layer of hollow metal ceramic spheres, providing structural strength and heat shielding, manufactured by laying up spheres and reinforcing materials in a mold and introducing liquid metal for casting.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If aluminum alloy is used for wing structure, then weight is reduced and ease of manufacture is improved, but temperature resistance deteriorates at high temperatures above 100°C
Solution Approach 1:
The patent applies composite materials by combining aluminum alloy matrix with hollow ceramic spheres and reinforcing fibers. This creates a metal matrix composite that maintains the lightweight advantage of aluminum while adding heat insulation capabilities through the hollow ceramic spheres, and structural strength through fiber reinforcement, thereby resolving the contradiction between weight and temperature resistance.
Solution Approach 2:
The patent implements local quality by creating a bimodal composite structure with different functional zones: hollow ceramic spheres concentrated in the trailing edge region for heat insulation, and reinforcing fibers distributed throughout the structure for strength. This localized functional differentiation allows the wing to have temperature resistance where needed while maintaining overall lightweight characteristics.
2Temperature
If epoxy resin composite is used for trailing edge, then temperature resistance is improved, but structural strength deteriorates compared to metal alloys
Solution Approach 1:
The patent uses composite materials to create a metal matrix composite that overcomes the strength limitations of epoxy resin composites. By embedding hollow ceramic spheres and reinforcing fibers within an aluminum alloy matrix, the material achieves both temperature resistance from the ceramic spheres and structural strength from the metal matrix and fiber reinforcement, resolving the strength deficit of pure resin composites.
Solution Approach 2:
The patent applies local quality by concentrating hollow ceramic spheres in the trailing edge portion that requires temperature resistance, while maintaining adequate reinforcing fiber distribution throughout to ensure overall structural strength. This localized functional assignment allows temperature protection without compromising structural integrity.
3Temperature
If thermally-insulating paste is applied to trailing edge, then temperature resistance is improved, but aerodynamic properties deteriorate and maintenance complexity increases
Solution Approach 1:
The patent merges the heat insulation function with the structural material itself by incorporating hollow ceramic spheres directly into the metal matrix composite. This integration eliminates the need for separate paste applications, ensuring that the heat-insulating layer maintains consistent aerodynamic surface properties while providing temperature protection, thereby resolving both the aerodynamic and maintenance issues.
Solution Approach 2:
The patent uses composite materials to embed hollow ceramic spheres within the structural composite, creating an integrated heat-insulating structure. This approach replaces external paste applications with an intrinsic composite material solution that maintains aerodynamic surface quality and eliminates maintenance requirements associated with paste application and monitoring.
4Temperature
If titanium or superalloys are used for trailing edge, then temperature resistance is improved, but manufacturing cost and processing difficulty increase significantly
Solution Approach 1:
The patent employs composite materials to achieve temperature resistance comparable to titanium or superalloys but at lower cost. By using an aluminum alloy matrix combined with hollow ceramic spheres and reinforcing fibers, the material provides high-temperature capability through the ceramic components while maintaining the cost-effectiveness and manufacturability of aluminum-based materials, resolving the cost contradiction.
Solution Approach 2:
The patent applies local quality by concentrating expensive heat-insulating hollow ceramic spheres only in the trailing edge region where temperature resistance is required, rather than using expensive materials throughout the entire wing structure. This localized application achieves necessary temperature protection while minimizing overall manufacturing cost.
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 composite material effectively insulates the trailing edge from high temperatures, maintaining structural integrity and extending service life while being cost-effective and aerodynamically sound.
Implementation Method 1
The portion of composite containing the hollow metal ceramic spheres acts as an embedded layer of heat insulation at the surface of the composite material
Data Source
AI summary
The trailing edge structure of an aircraft wing is subjected, in use, to high temperature efflux from an aircraft's engines. Such elevated temperatures can detrimentally affect the ultimate tensile strength of the trailing edge. An aircraft wing component includes composite material having a first portion including a metal matrix containing reinforcing material, and a second portion including a metal matrix containing hollow metal ceramic spheres, the second portion being adjacent a surface of the composite material. The provision of two portions, one of which contains reinforcing material and the other comprising hollow spheres means that the composite material has both structural strength and heat shielding qualities where they are needed most in the component. The portion of composite containing the hollow metal ceramic spheres acts as an embedded layer of heat insulation.