Dielectric Transport Element Clamp System for Aircraft
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Solution Overview
Problem
Current aircraft transport element support assemblies are time-consuming and costly to manufacture due to the need for cap sealing metal fasteners to prevent arcing and sparking, and they require complex, multi-piece fittings that are difficult to align and connect, extending assembly time and increasing electromagnetic interference risks.
Innovation Solution
A transport element clamp system using dielectric materials for both structural support and electromagnetic isolation, eliminating the need for cap sealing by integrating electromagnetic isolation and structural support in a single mechanism with interchangeable, load-sharing components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If metal fasteners and metal bridge are used to support transport elements, then structural support strength is improved, but electromagnetic sparking and arcing occur during electromagnetic events
Solution Approach 1:
The patent changes the material parameter of the support assembly from conductive metal to dielectric material, fundamentally altering the electrical properties while maintaining structural integrity. This parameter change eliminates electromagnetic sparking and arcing while preserving the mechanical support function.
Solution Approach 2:
The patent employs composite dielectric material construction consisting of a bridge portion and fastener portions made from non-conductive materials. This composite approach combines structural support capability with electromagnetic isolation properties, resolving the contradiction between strength and electromagnetic safety.
2Reliability
If cap seals are installed over each fastener to prevent arcing, then electromagnetic safety is improved, but manufacturing time and cost increase significantly
Solution Approach 1:
The patent extracts the need for cap seals entirely by using dielectric fasteners that inherently prevent arcing. By removing the conductive fasteners that would require sealing, the design eliminates the time-consuming cap seal installation process while maintaining electromagnetic safety.
Solution Approach 2:
The dielectric fasteners provide self-contained electromagnetic protection without requiring additional protective components. The material itself serves the dual function of fastening and electromagnetic isolation, eliminating the need for separate cap seal components and their associated assembly steps.
3Strength
If multiple metal parts are used in the assembly, then structural support capability is improved, but positioning, alignment, and sealing complexity increase
Solution Approach 1:
The patent merges the functions of structural support and electromagnetic isolation into a single integrated dielectric assembly. The bridge and fasteners work as a unified non-conductive system, eliminating the need for separate cap seal components and reducing the number of parts that require alignment and sealing.
Solution Approach 2:
The dielectric fastener portions serve multiple functions simultaneously: mechanical fastening, electromagnetic isolation, and alignment reference. This multi-functionality reduces the overall complexity of the assembly by eliminating dedicated alignment and sealing components.
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 solution reduces manufacturing time and cost by eliminating the need for cap sealing, simplifies assembly with interchangeable parts, and provides effective electromagnetic isolation, reducing the risk of arcing and sparking while ensuring secure transport element support.
Implementation Method 1
the lower portion and the upper portion are comprised of a dielectric material, and the transport element clamp system electrically isolates the number of transport elements from the two support structures
Data Source
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AI summary
A transport element clamp system comprising a lower portion, an upper portion, and a channel system. The lower portion has a first number of cutouts and the upper portion has a second number of cutouts. The lower portion is configured to bridge a gap between two support structures in an aircraft. The upper portion is configured to interlock with the lower portion. The channel system is formed by the first number of cutouts and the second number of cutouts. The channel system is configured to receive a number of transport elements when the upper portion and the lower portion are coupled to each other. The transport element clamp system electrically isolates the number of transport elements from the two support structures.