Avionics Bay Heat Transfer via Conductive Arrays
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Solution Overview
Problem
Sealed aircraft equipment bays with heat-generating components face challenges in providing effective cooling to prevent premature equipment failure due to moisture intrusion restrictions, limiting traditional cooling methods like vents or louvers.
Innovation Solution
A heat transfer system comprising an aircraft panel with a foam core and heat conducting arrays extending between the upper and lower skins, utilizing pyrolytic graphite materials for thermal conductivity and resilience, along with a pressure-sensitive adhesive and optional stiffening materials, to efficiently dissipate heat from avionics components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional cooling methods like vents or louvers are used, then cooling effectiveness is improved, but moisture intrusion risk increases
Solution Approach 1:
The patent introduces a heat conducting array as an intermediary thermal management system that transfers heat from avionics to the aircraft skin through thermally conductive materials (pyrolytic graphite sheets, aluminum extrusions) without requiring openings in the sealed bay structure, thus resolving the conflict between cooling needs and moisture protection
Solution Approach 2:
The invention replaces the mechanical ventilation system (vents, louvers, fans) with a passive thermal conduction system using heat conducting arrays and pyrolytic graphite sheets, eliminating the need for physical openings while maintaining cooling effectiveness
2Object-affected harmful factors
If sealed equipment bays are used, then moisture protection is improved, but heat dissipation capability deteriorates
Solution Approach 1:
The patent extracts the heat from the sealed bay environment by creating dedicated thermal conduction pathways (heat conducting arrays extending through the panel structure) that conduct heat away from avionics to the external aircraft skin surface, allowing sealed bays to maintain both moisture protection and heat dissipation
Solution Approach 2:
The invention employs composite thermal management structures combining pyrolytic graphite sheets with aluminum extrusions and foam cores to create efficient heat conduction pathways that integrate within the sealed panel structure, enabling simultaneous moisture sealing and thermal management
3Temperature
If heat conducting arrays extend through foam core, then heat transfer efficiency is improved, but structural complexity increases
Solution Approach 1:
The heat conducting array serves multiple functions simultaneously: it acts as a structural element within the panel, a thermal conduction pathway, and a mounting structure for avionics components. This multi-functionality reduces overall system complexity despite the integrated design
Solution Approach 2:
The patent merges the thermal management function with the existing panel structure by integrating heat conducting arrays into the foam core and bonding them to skin surfaces, combining structural support and heat transfer functions into a unified assembly rather than separate 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 system reduces temperature differences by 14% between heat-generating components and the aircraft skin, effectively managing heat transfer without compromising moisture sealing, thus preventing premature equipment failure.
Implementation Method 1
heat conducting array extending through the foam core and between the upper skin and the lower skin... efficiently dissipate heat from avionics components... reduces temperature differences by 14%
Implementation Method 2
utilizing pyrolytic graphite sheets for thermal conductivity
Data Source
AI summary
A heat transfer system for use within an avionics bay of an aircraft is provided by the present disclosure that includes, in one form, an aircraft panel comprising an upper skin, a lower skin, and a foam core disposed between the upper skin and the lower skin. At least one heat conducting array extends through the foam core and between the upper skin and the lower skin, the heat conducting array defining at least one upper cap, at least one lower cap, and a wall portion extending between the upper cap and the lower cap, the upper cap being disposed proximate avionics within the avionics bay. A heat conducting spreader is disposed between the lower cap of the heat conducting array and the lower skin of the aircraft panel.