Interwoven Wire Fabric in Composite Aircraft Structures Against Arcing
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Solution Overview
Problem
Composite materials used in aircraft structures provide less electromagnetic shielding than metallic materials, leading to reduced current dissipation during electromagnetic events like lightning strikes, which can compromise structural integrity and cause arcing.
Innovation Solution
Incorporating an interwoven wire fabric (IWWF) as a conductive laminate over composite structures to create a conductive pathway that channels current away from the structure, minimizing the risk of arcing and maintaining structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If composite materials are used for aircraft structures, then weight is reduced and strength-to-weight ratio is improved, but electromagnetic shielding capability is reduced leading to poor current dissipation during lightning strikes
Solution Approach 1:
The patent applies composite materials by combining non-conductive composite structure with conductive interwoven wire fabric (IWWF) to create a hybrid composite that provides both weight reduction and electromagnetic shielding. The IWWF is embedded within or attached to the composite laminate, creating a multi-material composite system that leverages the advantages of both material types while mitigating their individual disadvantages.
2Weight of moving object
If composite materials are used for aircraft structures, then weight is reduced, but current dissipation capability is reduced causing arcing and hot spots during lightning strikes
Solution Approach 1:
The interwoven wire fabric acts as an intermediary conductive layer between the external lightning strike and the non-conductive composite structure. It provides a controlled path for current dissipation, preventing uncontrolled arcing and hot spots on the composite surface while maintaining the weight benefits of composite materials.
Solution Approach 2:
The patent converts the harmful effect of lightning strikes by using the IWWF to channel and dissipate electrical energy safely. The conductive fabric transforms the potentially destructive direct strike into a controlled current flow that exits through designated pathways, protecting the composite structure from thermal and electrical damage.
3Reliability
If interwoven wire fabric is added to composite structures to improve current dissipation, then electromagnetic shielding is improved, but structural complexity increases
Solution Approach 1:
The patent merges the structural and electromagnetic shielding functions by integrating the IWWF directly into the composite laminate structure. The wire fabric is embedded within the composite layers or bonded to its surface, combining the mechanical structure and conductive pathway into a single integrated component rather than separate additive elements.
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 IWWF laminate effectively directs current during electromagnetic events, reducing the risk of structural damage and arcing, thereby enhancing the integrity and safety of composite aircraft components.
Implementation Method 1
the candidate conductive element is arranged to form a conductive pathway in the structural element... effectively directs current during electromagnetic events
Data Source
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AI summary
A method and system for designing a structural element for an aircraft includes defining a structural element, the structural element including a composite structure and a candidate interwoven wire fabric, wherein the candidate interwoven wire fabric forms a conductive pathway in the structural element. This may include generating a computer model of the composite structure; generating a computer model of the candidate interwoven wire fabric; forming a virtual prototype of the structural element including the composite structure and candidate interwoven wire fabric integrated therein; simulating, via a finite element model, a direct current injection event into the virtual prototype; determining an expected conductive pathway; identifying a risk associated with the expected conductive pathway in the virtual prototype; and implementing, as the structural element, the composite structure and the candidate interwoven wire fabric when the risk is less than a threshold risk.