Edge Morphing Airfoil Sub-Flap for Dynamic Shape Control
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Solution Overview
Problem
Conventional airfoils lack the ability to dynamically adjust their shape and contour to optimize lift-to-drag ratios across varying flight conditions, such as stable flight, takeoff, and landing, which limits their performance and efficiency.
Innovation Solution
A compliant sub-flap system is integrated with the airfoil, featuring flexible upper and lower surfaces that can morph and twist to change shape in response to actuation, allowing for adjustable camber and span-wise twist, thereby optimizing aerodynamic properties during different flight conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a conventional fixed airfoil is used, then the structure is simple and reliable, but the lift-to-drag ratio cannot be optimized for different flight conditions
Solution Approach 1:
The airfoil is divided into multiple independent segments along its span, with each segment capable of independent morphing. This segmentation allows different portions of the airfoil to be optimized for different flight conditions simultaneously, resolving the contradiction between adaptability and structural simplicity.
Solution Approach 2:
The airfoil transitions from a static structure to a dynamic one where segments can change shape and position in response to flight conditions. This dynamic capability enables optimization of lift-to-drag ratio across varying flight regimes without requiring completely different airfoil designs.
2Productivity
If the airfoil contour is adjusted for optimal performance, then aerodynamic efficiency improves, but the structural complexity and manufacturing difficulty increase
Solution Approach 1:
The airfoil employs flexible shell structures that can be actuated to change contour, replacing traditional rigid structures with complex movable parts. This approach achieves variable geometry for optimized aerodynamic efficiency while simplifying the manufacturing process through fewer discrete components and assembly steps.
Solution Approach 2:
The airfoil utilizes materials and structures whose physical parameters (such as stiffness, shape) can be changed through actuation rather than requiring physical reconfiguration of rigid components. This enables continuous contour adjustment for optimal aerodynamic performance while maintaining manufacturing simplicity.
3Adaptability or versatility
If the airfoil shape is varied for different flight conditions, then flight performance optimizes, but the control system complexity increases
Solution Approach 1:
The airfoil segments are designed to respond automatically to flight condition changes through integrated sensors and actuation systems, reducing the need for complex external control mechanisms. The structure essentially controls itself by detecting and responding to aerodynamic conditions, simplifying the overall control system while maintaining high adaptability.
Data Source
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AI summary
An edge-morphing arrangement for an airfoil includes a compliant upper surface and a compliant lower surface that are joined together. An actuator is coupled to a driven surface and actuated to move the driven surface and change the shape thereof, with the non-driven surface changing its shape in response to actuation of the driven surface. The upper and lower surfaces can be part of a sub-flap mounted to a traditional flap of the fixed wing of an airplane. The upper and lower surfaces can be mounted to existing structure in the flap, or the flap components can be mounted to the sub-flap. The upper and lower surfaces can alternatively replace the traditional flap in the fixed wing of an aircraft. The upper and lower surfaces are continuous and can be deflected upward, downward, or twisted in a span-wise direction relative to the flap or wing.