Morphing Wing Device for Aerodynamic Flow Control
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Solution Overview
Problem
Aircraft wings, particularly those designed for UAVs, face challenges in maintaining optimal aerodynamic performance across a wide range of flight conditions due to fixed geometric profiles, leading to performance losses and issues with drag and lift characteristics, especially at low Reynolds numbers where laminar-turbulent flow transitions are critical.
Innovation Solution
A device is movably mounted on the wing to selectively displace between different positions, altering the aerodynamic flow over specific areas of the wing surface, allowing for optimized drag reduction, mild stall characteristics, and lift increments by modifying the wing's geometry during flight, using a body with a flexible external surface that conforms to the wing's profile and is actuated by a motion-inducing arrangement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a fixed geometric profile is used for the wing, then the manufacturing and structural simplicity is maintained, but the aerodynamic performance is lost when operating under varying flight conditions
Solution Approach 1:
The patent applies the dynamics principle by making the wing geometry changeable during flight. A morphing device with inflatable bladders is integrated into the wing structure, allowing the airfoil shape to be dynamically adjusted between different configurations (e.g., high-lift and low-drag shapes) based on flight conditions. This enables the wing to adapt to varying operational requirements while maintaining a relatively simple overall structure.
Solution Approach 2:
The patent implements parameter changes by modifying the physical geometry parameters of the wing through inflation and deflation of internal bladders. The cross-sectional area, camber, and other aerodynamic parameters of the airfoil can be changed by controlling the pressure and volume of the inflatable elements, allowing optimization of aerodynamic performance for different flight regimes.
2Adaptability or versatility
If leading edge slats and trailing edge flaps are used to vary aerofoil geometry, then operation at different conditions is enabled, but the device complexity and drag penalty increase
Solution Approach 1:
The patent replaces traditional static high-lift devices (slats and flaps) with a dynamic morphing wing structure. The entire airfoil can continuously change shape through inflation/deflation of bladders, providing adaptability across the flight envelope without requiring separate movable high-lift devices that create drag penalties.
3Force
If the laminar separation bubble size is increased to increment lift, then the lift coefficient improves, but the drag increases and stall risk increases
Solution Approach 1:
The patent controls the laminar separation bubble characteristics by changing the airfoil geometry parameters through morphing. By adjusting the camber and curvature distribution along the airfoil surface, the flow transition and separation behavior can be optimized to maintain beneficial laminar separation bubbles that enhance lift while controlling their size to limit drag and stall risks.
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 solution enables improved aerodynamic performance by reducing drag, delaying stall, and increasing lift across various flight conditions, optimizing endurance and efficiency by dynamically adjusting the wing's geometry in response to changing aerodynamic conditions.
Implementation Method 1
selectively providing a modified aerodynamic flow over a wing under aerodynamic flight conditions
Data Source
AI summary
A device and a related method are disclosed for selectively providing a modified aerodynamic flow over a wing under aerodynamic flight conditions with respect to a respective datum aerodynamic flow over an external wing surface of the wing in the absence of the device under similar aerodynamic flight conditions. The device includes a body configured to be movably mounted to the wing for selective displacement between at least two different positions with respect to the external wing surface and having an external body surface. The device includes a motion inducing arrangement coupled to the body and configured for providing the selective displacement. In each position, the body is in a respective superposed relationship with a respective wing surface portion of the wing external surface and the modified aerodynamic flow includes airflow over the external body surface. A wing and an air vehicle including the device are also disclosed.