Aircraft Wing Element Shield Temperature Measurement
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing aircraft wing elements lack the capability to separately measure the temperature of the shield and evaluate the thermal energy flow transferred to it, leading to potential heat accumulation points that can degrade the wing element during operation.
Innovation Solution
Incorporating a second temperature sensor between the electrothermal mat and the insulating film, with a conductive track covering at least 50% of the support film's surface, allows for accurate measurement of the shield's temperature and evaluation of thermal energy flow, reducing heat inhomogeneities and preventing accumulation points.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If only a first temperature sensor connected to the structure portion is used, then the temperature of the electrothermal mat can be measured, but the temperature of the shield cannot be measured separately and thermal energy flow cannot be evaluated
Solution Approach 1:
The temperature measurement function is segmented into two separate sensors: the first temperature sensor measures the electrothermal mat temperature, while the second temperature sensor measures the shield temperature. This segmentation allows independent measurement of each component's temperature, enabling separate evaluation of thermal energy flow from the mat to the shield.
Solution Approach 2:
The second temperature sensor acts as an intermediary element positioned between the electrothermal mat and the insulating film. This intermediary sensor captures the thermal state at the mat-shield interface, providing critical information about heat transfer that cannot be obtained by measuring only the mat or structure portion temperature.
2Ease of manufacture
If the second temperature sensor track has low surface occupation, then manufacturing is easier, but heat accumulation points occur between the shield and electrothermal mat
Solution Approach 1:
The second temperature sensor track is designed with meandering geometry that achieves at least 50% surface occupation on the support film. This local density enhancement ensures sufficient thermal conductivity at critical heat transfer locations while maintaining the overall sensor structure. The meandering pattern optimizes heat distribution by creating multiple thermal pathways, preventing localized heat accumulation points.
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 enables precise temperature measurement and thermal energy evaluation, ensuring uniform heat transfer and preventing damage to the wing element by avoiding heat accumulation points, thus enhancing the wing's operational efficiency and longevity.
Implementation Method 1
When it is supplied with electrical current, the electrothermal mat produces heat, at least part of which diffuses towards the shield with the aim of preventing ice formation or melting any ice which has already accumulated thereon
Implementation Method 2
a first temperature sensor, which itself comprises a first support film and at least one first track of a first electrically conductive material with an electrical resistivity value of this first material that varies as a function of its temperature
Implementation Method 3
a second temperature sensor, which itself comprises a second support film and at least a second track of a second electrically conductive material, with an electrical resistivity value of the second material which varies as a function of a temperature of the latter
Implementation Method 4
an electrically insulating film, which is rigidly connected to the electrothermal mat by a first face of this insulating film, and connected to the shield by a second face of the same insulating film... The function of the insulating film is to electrically insulate the shield with respect to internal components of the wing element
Data Source
AI summary
An aircraft wing element comprises two temperature sensors that are situated on each side of an electrothermal mat, between a structure portion and a shield of said wing element. A shield temperature can be measured more accurately, and a thermal energy flow that is transferred to the shield can be evaluated.