Inductive Ice Protection for Composite Aircraft Surfaces
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Solution Overview
Problem
Existing ice protection systems for aircraft aerodynamic surfaces, particularly those made of carbon fiber reinforced polymer (CFRP), face inefficiencies due to poor thermal and electrical conductivity, limiting the effectiveness of heating methods like electromagnetic induction, which requires a conductive layer and specific winding distribution to prevent ice formation and detachment.
Innovation Solution
A composite ice protection device with a perimetric and inner winding configuration for CFRP surfaces, utilizing an electrically conductive layer on the outer surface for electromagnetic induction heating, allowing controlled heating and ice management through a control unit, and enabling efficient heat generation without conduction, with windings placed at the inner face for easier maintenance and modular design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If electromagnetic induction heating is used on CFRP surfaces, then heating efficiency is improved, but the poor electrical conductivity of CFRP prevents strong eddy currents from forming
Solution Approach 1:
A conductive layer is introduced as an intermediary between the electromagnetic field source and the CFRP surface. This conductive layer has high electrical conductivity that enables strong eddy currents to form, which then generate heat that transfers to the CFRP surface for ice protection.
Solution Approach 2:
The solution combines the CFRP structural material with a conductive material layer to create a composite structure. The CFRP provides structural integrity while the conductive layer provides the necessary electrical properties for electromagnetic induction heating.
2Use of energy by moving object
If a conductive layer is added to enable electromagnetic induction, then heating capability is improved, but device complexity increases
Solution Approach 1:
The conductive layer is merged with the CFRP surface to form an integrated structure. The layer is applied directly to the aerodynamic surface, combining the structural CFRP with the functional conductive layer in a single unified component.
Solution Approach 2:
The conductive layer serves multiple functions: it provides electrical conductivity for electromagnetic induction heating, maintains aerodynamic surface properties, and integrates with the CFRP structure. This multi-functionality reduces the need for separate components.
3Temperature
If windings are placed on the outer surface for electromagnetic induction, then heating effectiveness is improved, but maintenance difficulty increases
Solution Approach 1:
Instead of placing the electromagnetic induction windings on the outer surface, the solution inverts the arrangement by placing the windings on the inner surface of the aerodynamic structure. The electromagnetic field penetrates through the CFRP to induce eddy currents in the conductive layer on the outer surface, achieving heating effectiveness while improving maintenance accessibility.
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
This solution provides effective and efficient ice protection for CFRP surfaces by generating heat directly on the outer surface, controlling ice formation and detachment, and simplifying maintenance, while minimizing weight and optimizing electrical transformer resistance.
Implementation Method 1
a layer of electrically conductive material configured for being located at the outer face of the composite layer and adapted for being heated by electromagnetic induction
Implementation Method 2
eddy currents are formed in electrically conductive materials which then heat the material by Joule effect
Implementation Method 3
a perimetric monophasic winding configured for heating the edge surrounding a delimited area of the electrically conductive layer, an inner monophasic or multiphasic winding configured for heating the inside of the delimited area
Data Source
AI summary
An ice protection device for an aircraft surface having a composite layer. The device comprises a layer of electrically conductive material configured to be located at an outer face of the composite layer and adapted to be heated by electromagnetic induction. The device also comprises a perimetric monophasic winding to heat an edge surrounding a delimited area of the electrically conductive layer, an inner monophasic or multiphasic winding to heat the inside of the delimited area of the perimetric monophasic winding, a control unit, to independently control the outer winding and the inner winding, the control unit being adapted to continuously operate the outer winding to avoid the formation of ice in the edge of the delimited area and also to operate the inner winding when the ice formed inside the delimited area is to be detached.