Porous Heating Source with Suction for Aircraft Ice Protection
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Solution Overview
Problem
Existing ice protection systems for aircraft are complex, inefficient, and prone to ice runback, which can lead to engine failure and aerodynamic performance issues due to the inability to prevent ice formation effectively and manage melted ice drainage.
Innovation Solution
An ice protection system that incorporates a porous heating source with a suction mechanism and honeycomb cell support structure, allowing for efficient melting and drainage of ice through a perforated sheet and drain holes, reducing runback and enhancing aerodynamic performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If hot gas ducting is used to prevent ice formation, then ice protection is achieved, but system complexity increases and effectiveness is reduced
Solution Approach 1:
The patent applies porous heating elements that can be integrated directly into the skin structure, eliminating the need for complex ducting systems. The porous material allows uniform heat distribution across the surface while simplifying the overall system architecture.
Solution Approach 2:
The heating element is merged with the skin structure itself, creating an integrated system where the heating function is built into the structural component. This eliminates separate ducting systems and reduces overall complexity.
2Reliability
If heating is applied to prevent ice formation, then ice protection is improved, but melted ice runback occurs causing engine damage and aerodynamic performance loss
Solution Approach 1:
The patent extracts the harmful melted ice water from the system by implementing drainage holes that remove the liquid before it can runback into the engine or affect aerodynamic surfaces downstream.
Solution Approach 2:
The melted ice water, which would normally be harmful, is converted into a beneficial drainage flow that can be safely removed through controlled exit points, preventing damage while maintaining the protective heating function.
3Reliability
If conventional heating systems are used, then ice melting is achieved, but fuel efficiency decreases due to downstream heating requirements
Solution Approach 1:
By extracting and removing the melted ice water through drainage holes, the system eliminates the need for downstream heating to prevent runback ice formation, thereby reducing overall energy consumption and improving fuel efficiency.
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 prevents ice formation, reduces ice runback, improves aerodynamic performance, and enhances fuel efficiency by draining melted ice efficiently, minimizing downstream heating requirements and contact with engine components.
Implementation Method 1
a porous heating source with a suction mechanism and honeycomb cell support structure, allowing for efficient melting and drainage of ice through a perforated sheet and drain holes
Implementation Method 2
a porous heating source with a suction mechanism and honeycomb cell support structure, allowing for efficient melting and drainage of ice
Data Source
Figure 1
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AI summary
Disclosed is an ice protection system (140) for an aerodynamic surface of an aircraft, a surface having a flow facing side and an inwardly facing side that opposes the flow facing side, the system having: a perforated sheet (170) configured for disposal in the surface; a heating source connected to the perforated sheet; and a suction source (160) disposed to draw ice melted by the heating source (150) through the perforated sheet (170) and heating source.