Flexible Deice Boot Vortex Generators for Wing Ice Shedding
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Ice buildup on aircraft wings exacerbates stall conditions by increasing the critical angle of attack, leading to flow separation, decreased lift, and increased drag, which complicates control and balance, especially in adverse weather conditions.
Innovation Solution
The integration of a deice boot with protrusions, such as vortex generators, on the leading edge of the wing, constructed from flexible materials like neoprene rubber, which inflate and deflate to shed ice and feature a ramped upper face and laterally converging sides to minimize flow separation, particularly at stall conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If a deice boot is used to remove ice buildup, then ice shedding is improved, but flow separation increases at stall conditions
Solution Approach 1:
The deice boot is segmented into multiple spanwise inflatable tubes that can be independently controlled. This segmentation allows different sections to be inflated at different times, creating a more controlled ice shedding pattern that reduces turbulent flow separation compared to a single large inflatable structure.
Solution Approach 2:
The vortex generator protrusions are pre-positioned on the deice boot surface before inflation occurs. These protrusions create controlled vortices in advance that energize the boundary layer, preventing flow separation before it can occur during the ice shedding process.
2Object-affected harmful factors
If the deice boot is inflated to shed ice, then ice removal is improved, but aerodynamic performance deteriorates
Solution Approach 1:
The deice boot operates through periodic inflation and deflation cycles rather than remaining continuously inflated. This periodic action allows the wing to maintain optimal aerodynamic performance during deflation phases while achieving ice removal during brief inflation periods, thus preserving overall aerodynamic efficiency.
Solution Approach 2:
Vortex generators are positioned to create beneficial flow patterns before the aircraft reaches stall conditions. This preliminary aerodynamic conditioning ensures that when ice shedding occurs, the flow remains attached and aerodynamic performance is maintained.
3Stability of the object's composition
If protrusions are added to the deice boot to minimize flow separation, then aerodynamic stability is improved, but device complexity increases
Solution Approach 1:
The protrusions are integrated into the flexible rubber boot material itself rather than being separate rigid components. This allows the protrusions to flex and deform with the boot during inflation and deflation cycles, maintaining structural simplicity while achieving the aerodynamic function of flow separation control.
Solution Approach 2:
The vortex generator protrusions are merged with the deice boot structure, combining two functions (ice shedding and flow control) into a single integrated component. This eliminates the need for separate vortex generator devices and reduces overall system complexity.
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 effectively reduces flow separation and improves handling characteristics by maintaining attached airflow and preventing premature stalls due to ice buildup, ensuring stable aircraft control even in contaminated conditions.
Implementation Method 1
Deice boots include flexible sheets of rubber which are adhered to the leading edge of the wing and have span-wise inflatable tubes which are stitched into the rubber matting. When the tubes are inflated, the boot causes the accumulated ice to be pushed away from the leading edge surface.
Implementation Method 2
The protrusion is adapted such that it minimizes flow separation from the wing, especially when the aircraft approaches stall conditions. Structurally speaking, this flow separation minimization, in one embodiment, is achieved by configuring the protrusions such that each has a ramped upper face and two laterally converging sides. In some embodiments the protrusions are vortex generators.
Data Source
AI summary
An arrangement of devices as well as a method for improving the aerodynamics of an aircraft wing are disclosed. In embodiments, a plurality of vortex generators are attached in span-wise alignment on an deice boot along the wing's leading edge. The vortex generators are, in embodiments, constructed of a flexible material such that they are able to be expanded along with the boot during inflation and deflation thus mechanically involving the aerodynamic devices in the ice-shedding process.