Aircraft Flow Body Dual Heating Layout Against Re-Icing
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Solution Overview
Problem
Existing aircraft icing prevention systems, such as electric heating devices, often fail to effectively prevent ice accumulation in rear sections of flow bodies due to water runoff from melted ice, leading to potential re-icing.
Innovation Solution
A flow body for an aircraft with two heating devices, one integrated into the leading edge and the other into the trailing edge, where the second heating device spans over a significant chordwise section to ensure comprehensive ice melting, including a sandwich core or solid trailing edge component with integrated electric heaters.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a single heating device is used in the leading edge section, then the leading edge is effectively heated, but water runoff from melted ice causes re-icing in the rear section
Solution Approach 1:
The heating system is divided into multiple independent heating devices positioned at different chordwise sections of the flow body. Each heating device independently heats its designated section, preventing water runoff from refreezing in downstream sections. This segmentation allows targeted heating of both leading edge and trailing edge regions to comprehensively address ice prevention.
Solution Approach 2:
The heating devices are positioned and configured to preemptively heat the flow surface before ice can accumulate or to continuously heat the surface to prevent water runoff from refreezing. By maintaining continuous heating in both front and rear sections, the system prevents the harmful effect of re-icing before it occurs.
2Reliability
If heating coverage is extended to the trailing edge, then comprehensive ice prevention is achieved, but the device complexity increases
Solution Approach 1:
The flow body is divided into multiple chordwise sections, each equipped with an independent heating device. This segmentation allows the system to achieve comprehensive heating coverage from leading edge to trailing edge while maintaining modular simplicity. Each segment can be independently controlled and maintained, reducing overall system complexity despite extended coverage.
Solution Approach 2:
The heating devices serve multiple functions: they prevent ice accumulation on the flow surface, heat water runoff to prevent re-icing, and can be independently controlled based on local conditions. This multi-functionality justifies the presence of multiple heating devices while maximizing their utility across different chordwise sections.
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
Prevents ice formation and melting water runoff by effectively heating both leading and trailing edge sections, ensuring continuous ice prevention and maintaining aerodynamic characteristics.
Implementation Method 1
at least the second heating device comprises an electric heater
Data Source
Figure 1~2
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AI summary
A flow body (2) for an aircraft (44) is proposed, comprising a stiffening structure (4) and a flow surface (6) at least partially enclosing the stiffening structure (4), the flow surface (6) having a leading edge (8) and a trailing edge (10) at a distance to each other in a chordwise direction, the flow body further comprising a first heating device (18) attached to or integrated into the flow surface in a first chordwise section (12), a second heating device (22) attached to or integrated into the surface body in a second chordwise section (14), wherein the first chordwise section and the second chordwise section are distanced from each other, wherein the first chordwise section is closer to the leading edge than the second chordwise section, and wherein at least the second heating device (22) comprises an electric heater.