Aircraft Cladding Element With Embedded Heating Layer
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Solution Overview
Problem
In aircraft interior spaces, particularly passenger cabins, there is a challenge in maintaining a comfortable indoor climate due to insufficient installation space for adequate insulation, leading to unacceptably low surface temperatures and thermal bridges, which compromise thermal insulation efficiency.
Innovation Solution
A cladding element with a sandwich construction incorporating a core layer and a visible cover layer, featuring an embedded electrically heating layer, such as heating paper or textile, which generates heat and disperses it towards the interior space without being compromised by additional core layers, ensuring efficient heat distribution while being protected from mechanical influences.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If insulation material is incorporated between the external skin and the internal wall, then thermal insulation is improved, but installation space is insufficient and thermal bridges occur
Solution Approach 1:
The heating layer is integrated directly into the cladding element structure, merging the heating function with the structural component. This eliminates the need for separate insulation material and allows adequate heating performance within limited installation space, preventing thermal bridges by providing continuous heating across the cladding surface.
Solution Approach 2:
The patent replaces passive mechanical insulation material with an active electric heating layer. Instead of relying on thick insulation layers to maintain temperature, the heating layer actively generates heat to compensate for thermal losses, achieving the desired surface temperature without requiring excessive installation space.
2Loss of energy
If heating layer is placed close to the visible side, then heat dispersal efficiency is improved, but mechanical protection is reduced
Solution Approach 1:
The cladding element structure is locally adapted to accommodate the heating layer. The cover layer is designed with specific properties (flexibility, thickness, material composition) to provide adequate mechanical protection to the heating layer while maintaining close proximity for efficient heat dispersal. This local optimization allows both protection and thermal efficiency.
Solution Approach 2:
The cladding element uses composite material construction with the heating layer embedded between the core layer and cover layer. The cover layer material is selected to provide both mechanical protection and thermal conductivity, creating a composite structure that simultaneously protects the heating layer and enables efficient heat dispersal to the visible surface.
3Temperature
If adequate insulation material is incorporated, then thermal comfort is improved, but system weight increases
Solution Approach 1:
The patent replaces heavy passive insulation material with a lightweight active heating layer. The heating layer has minimal weight compared to adequate insulation material but achieves the same thermal comfort effect by actively generating heat, thereby significantly reducing the overall system weight while maintaining thermal comfort in the aircraft interior.
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 enhanced thermal comfort with low energy consumption and system weight, meeting mechanical, fire safety, and moisture resistance requirements, while ensuring the heating element is protected and safely integrated within the fiber-composite structure.
Implementation Method 1
An electrically heating layer is disposed between that core layer that is closest to the cover layer and the cover layer. The heating layer serves for generating heat and for emitting the heat through the first cover layer
Data Source
AI summary
A cladding element having a heating layer in a sandwich construction. In the case of a cladding element in a sandwich construction for an interior space of an aircraft, the cladding element includes a core layer and a first cover layer. The first cover layer forms a visible side of the cladding element. An electrically heating layer extends at least across a sub-face of the first cover layer and serves for generating heat for emission through the first cover layer is disposed between the core layer and the first cover layer.