Integrated Aircraft De-icing Panel with Trabecular Core
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Solution Overview
Problem
Current de-icing systems for aircraft are complex, costly, and inefficient, with multiple discrete components increasing maintenance time and weight, and often result in suboptimal hot air fluid force and high electric power requirements, which are not scalable for large aircraft.
Innovation Solution
A structurally integrated de-icing system using a single-piece, multi-layer panel with integrated hot air ducts and trabecular core that optimizes hot air distribution directly within the aircraft structure, reducing weight and complexity, and utilizing additive manufacturing to minimize parts and assembly costs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple discrete components (ducts, stiffeners, brackets, connections, nozzles) are used for thermal de-icing systems, then the de-icing function is achieved, but the device complexity and maintenance time increase significantly
Solution Approach 1:
The patent merges multiple discrete de-icing components (ducts, stiffeners, brackets, connections, nozzles) into a single integrated thermal de-icing system. This consolidation maintains the de-icing function while dramatically reducing device complexity and maintenance requirements by eliminating the need for separate components and their associated assembly/disassembly operations.
Solution Approach 2:
The integrated thermal de-icing system performs multiple functions simultaneously: it provides de-icing capability, structural support, and thermal management through a single unified design. This multi-functionality eliminates the need for separate dedicated components for each function, thereby reducing overall system complexity.
2Reliability
If multiple discrete components are used for thermal de-icing systems, then the de-icing function is achieved, but the manufacturing costs and production time increase
Solution Approach 1:
By combining multiple de-icing components into a single integrated system, the patent reduces manufacturing costs and production time. The unified design eliminates the need to manufacture, quality-test, and assemble multiple separate parts, thereby streamlining the manufacturing process and reducing overall production time.
3Reliability
If inefficient de-icing systems with low thermal efficiency are used, then the de-icing function is achieved, but more hot air must be bled from the engine, reducing aircraft performance
Solution Approach 1:
The patent optimizes the thermal efficiency parameters of the de-icing system by improving heat distribution characteristics. This allows the system to achieve effective de-icing with reduced hot air bleeding from the engine, thereby minimizing energy loss and maintaining aircraft performance.
4Reliability
If discrete de-icing components are added to the aircraft structure, then the de-icing function is provided, but the aircraft weight increases, reducing payload capacity
Solution Approach 1:
The integrated thermal de-icing system merges the de-icing function with the aircraft's existing structural components. This integration eliminates the need for separate heavy de-icing components, thereby reducing the overall weight added to the aircraft and preserving payload capacity.
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 solution significantly reduces hot air bleeding from the engine, minimizes maintenance complexity, and achieves improved thermal efficiency, structural integrity, and aerodynamics while allowing for interchangeable de-icing configurations and reduced environmental impact.
Implementation Method 1
a single tube (13) which transfers the hot air bled from the engine compressor and distributes it to the multi-layer panel (17) through the slot (14)
Implementation Method 2
the layer (15) inside the multi-layer panel (17) that is also made integrally in a single component
Data Source
AI summary
An aircraft (A) comprising at least a component part (1, 2, 3, 4, 5, 6, 7, 8) provided with thermal de-icing means (S) suitable to eliminate and/or prevent the formation of ice on said component part, said de-icing means (S) are directly integrated in the structure of said part (1, 2, 3, 4, 5, 6, 7, 8).