Aerofoil Trailing-Edge Hinge for Shear-Resistant Control
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Solution Overview
Problem
Existing aerofoil designs face challenges in scaling due to internal space constraints and are prone to buckling under extreme vertical sheer forces, particularly in rotating blades of aircraft and wind turbines, necessitating improved hinge mechanisms for strength and energy-efficient control.
Innovation Solution
The aerofoil features a movable trailing edge portion connected via first and second connection members forming a triangular hinge, with the axis of rotation at the outer surface, supported by a framework and inertia damper, allowing for accurate control and absorption of vertical sheer forces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If the control flap is positioned along the centreline of the aerofoil, then the hinge mechanism can be simplified, but internal space constraints prevent scaling to practice
Solution Approach 1:
The invention moves the hinge axis from the traditional centreline position to the outer surface of the aerofoil. This dimensional relocation eliminates internal space constraints while maintaining hinge functionality, allowing the mechanism to scale to practice without being limited by internal volume availability.
2Volume of moving object
If a traditional hinge is used at the centreline, then the structure can be compact, but it buckles under extreme vertical sheer forces
Solution Approach 1:
Relocating the hinge axis to the outer surface creates a more favorable structural configuration that naturally resists vertical sheer forces. The outer surface positioning allows the hinge to function as a stronger structural element rather than an internal component subjected to buckling loads.
Solution Approach 2:
The framework is pre-configured with connection members arranged in a triangular configuration before loading occurs. This preliminary structural arrangement ensures that vertical sheer forces are distributed and resisted effectively, preventing buckling under extreme loads.
3Ease of operation
If the trailing edge portion is moved upwardly, then the area A is disposed upwardly for control, but the connection members must flex significantly increasing energy requirements
Solution Approach 1:
The connection members are pre-configured in a triangular arrangement with the framework, creating a mechanically advantageous structure before actuation. This preliminary configuration reduces the force required to move the trailing edge portion, thereby reducing energy requirements while maintaining control accuracy.
Solution Approach 2:
The invention combines the hinge function with the structural framework by integrating connection members that serve both as structural supports and as the hinge mechanism itself. This merging eliminates the need for separate, energy-intensive actuation systems while maintaining precise control capability.
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 configuration enables efficient energy absorption, accurate control, and enhanced structural strength, reducing noise and vibration by minimizing the force required for angular displacement and preventing buckling.
Implementation Method 1
The first and second connection members are configured to flex upwardly when the actuating device is operated to move the trailing edge portion upwardly with respect to the main portion
Implementation Method 2
An inertia damper is provided in the cavity defined by the first and second connection members. The inertia damper is configured to absorb energy derived from forces subjected to the trailing edge portion, in use.
Implementation Method 3
The inertia damper is configured to absorb energy derived from forces subjected to the trailing edge portion, in use.
Data Source
Figure 1~2
Figure 3
Figure 4~6
AI summary
An aerofoil has a main portion of aerofoil cross section and a trailing edge portion movable with respect to the main portion by an actuating device, the trailing edge portion is movable at or about an area / point of flexion A, the area / point of flexion A is located at or adjacent a pressure or suction surface of the aerofoil, the trailing edge portion is connected to the main portion by first and second connection members, the first connection member extends inwardly away from the area / point of flexion A and has an end which is directly or indirectly connected to the main portion, the first and second connection members are flexible.