Morphing Wing Ribs for Aerodynamic Twist Control
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Solution Overview
Problem
Conventional aircraft control surfaces lead to aerodynamic inefficiencies due to flow separation and require heavy actuators, complex structures, and high installation costs, while existing morphing skin technologies struggle with maintaining a smooth surface and reducing drag.
Innovation Solution
A wing or blade element with rotatable and slidable ribs, actuated by servomotors and stiffening rods, which twist to change the aerodynamic configuration, maintaining a smooth surface and reducing drag through a compression assembly that keeps the surface gap-free.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If traditional discrete control surfaces are used, then control functionality is achieved, but aerodynamic performance deteriorates due to flow separation
Solution Approach 1:
The patent applies dynamics by replacing static control surfaces with a morphing wing system that can dynamically change its aerodynamic configuration. The wing uses adjustable twist mechanisms and variable geometry elements that allow continuous adaptation to flight conditions, eliminating the fixed geometry limitations of traditional surfaces and reducing flow separation during control maneuvers.
Solution Approach 2:
The patent implements parameter changes by modifying the aerodynamic parameters of the wing through controlled twist angles and geometry adjustments. The system varies parameters such as twist distribution, camber, and airfoil shape along the wing span to optimize performance during different flight phases, thereby reducing energy loss from flow separation while maintaining effective control.
2Loss of energy
If morphing technologies are used to improve aerodynamic performance, then control efficiency increases, but structural complexity and weight increase
Solution Approach 1:
The patent applies segmentation by dividing the wing structure into modular components with independent twist and geometry adjustment capabilities. The wing is segmented into multiple control elements along the span, each capable of independent morphing, which simplifies the overall control system compared to a fully integrated morphing wing while maintaining aerodynamic efficiency benefits.
Solution Approach 2:
The patent implements local quality by applying morphing capabilities selectively to specific regions of the wing rather than the entire structure. The twist and geometry adjustment mechanisms are localized to areas where they provide maximum aerodynamic benefit, reducing overall structural complexity and weight while maintaining improved performance in critical flight control zones.
3Loss of energy
If morphing technologies are used to improve aerodynamic performance, then control efficiency increases, but cost increases
Solution Approach 1:
The patent applies segmentation to reduce manufacturing cost by producing the wing from modular, standardized components that can be manufactured using conventional processes. The segmented design allows for simplified assembly and reduced tooling requirements compared to fully integrated morphing wings, lowering overall production costs while maintaining aerodynamic efficiency through the distributed twist control system.
4Ease of operation
If high winglet twist angles are used for control, then roll control effectiveness improves, but aerodynamic efficiency decreases
Solution Approach 1:
The patent implements parameter changes by optimizing the twist angle distribution along the wing span rather than applying uniform high twist angles. The system adjusts local twist parameters to achieve effective roll control through differential twisting, maintaining smoother airflow and reducing the aerodynamic penalties associated with excessive twist while preserving control effectiveness.
Data Source
AI summary
A blade or wing element includes a plurality of ribs (20) rotatable and/or slidable with respect to one another whereby to vary the aerodynamic configuration of the blade or wing element by causing a twist thereof. A blade or wing or blade or wing assembly, including such a blade or wing element is disclosed, as well as an aerodynamic apparatus such as an aircraft, or a wind turbine. A method of assembling a blade or wing element is also disclosed.