Aircraft Feeder Cable Cooling Using Thermoelectric Grommets
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Solution Overview
Problem
Aircraft propulsion systems face challenges in thermal management of high-power electrical conductors due to the conduction of high electric power through wing and fuselage structures, requiring effective solutions to mitigate heat buildup and ensure efficient power transmission.
Innovation Solution
A support system for feeder cables incorporating a thermoelectric cooler with a heated side attached to the aircraft structure and a cooled side in thermal contact with the cable, powered by induced current from an inductive coil, to efficiently manage heat dissipation and maintain electrical conductivity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If high electric power is conducted through the aircraft wing structure, then power transmission capability is improved, but thermal management difficulty increases
Solution Approach 1:
The patent extracts the thermal management function from the structural components by introducing separate thermoelectric cooler devices. These coolers are positioned adjacent to the feeder cable and actively remove heat from the high-power electrical conductors, separating the power transmission function from the thermal control function.
Solution Approach 2:
The patent introduces thermoelectric coolers as intermediary devices between the heat-generating feeder cable and the surrounding aircraft structure. These coolers act as thermal mediators that actively transfer heat away from the cable, preventing thermal buildup while allowing the high-power transmission to continue.
2Temperature
If thermoelectric cooler is added to manage heat, then thermal management effectiveness is improved, but device complexity increases
Solution Approach 1:
The patent implements self-service by using the electromagnetic field from the feeder cable itself to power the thermoelectric cooler through an inductive coupling mechanism. The alternating current in the feeder cable induces current in a nearby coil, which rectifies and powers the cooler, eliminating the need for separate power supply wiring and reducing system complexity.
Solution Approach 2:
The patent merges multiple functions into integrated components. The attachment structure combines mechanical mounting, thermal conduction pathways, and electrical isolation functions. The inductive coupling mechanism combines power extraction and control functions, reducing the number of discrete components needed.
3Temperature
If feeder cable is thermally connected to cooled side, then cooling effectiveness is improved, but electrical insulation requirement increases
Solution Approach 1:
The patent applies local quality by providing thermal conduction only where needed - at the interface between the attachment and the feeder cable insulation. The attachment is designed with thermally conductive material positioned to contact the cable insulation, creating a localized thermal pathway that does not compromise the overall electrical insulation integrity of the cable system.
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 effectively dissipates heat away from high-power electrical conductors, ensuring reliable power transmission and reducing thermal stress on aircraft structures, thereby enhancing the performance and longevity of electric propulsion systems.
Implementation Method 1
a cooled side thermally conductive with the inner perimeter at a thermal conductivity greater than 100 watts per meter-kelvin at one °C and a heated side thermally conductive with the structure at the thermal conductivity
Implementation Method 2
an inductive coil disposed near the passage such that when alternating current is passing through the feeder cable, induced current is induced in the inductive coil
Data Source
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AI summary
Disclosed is an aircraft having an aircraft electric motor (114); a motor controller (110); a structure having ribs (108) and spars (106) defining a wingbox (104) of the aircraft; a feeder cable (112) connecting the motor controller and the aircraft electric motor through the wingbox; and a grommet (342) defining an orifice by an inner perimeter sized to receive the feeder cable, the passage (116) housing a thermoelectric cooler (320) having a cooled side (318) thermally conductive with the inner perimeter at a thermal conductivity greater than 100 watts per meter-kelvin at one °C and a heated side (316) thermally conductive with the structure at the thermal conductivity.