Passive Adaptive Wing Buckling Members for Gust Load Mitigation
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Solution Overview
Problem
High-altitude, long-endurance (HALE) aircraft face challenges in reducing structural mass fraction and aerodynamic loads due to gust conditions, leading to increased wing loading and potential structural failure, with existing active and passive morphing technologies either being too heavy or limited in their ability to respond nonlinearly to aerodynamic loads.
Innovation Solution
A passive adaptive wing design utilizing buckling members that respond to aerodynamic loads by changing shape in a nonlinear, stepwise manner, reducing camber and angle of attack to mitigate gust loads without the need for active actuators or complex control systems, thereby reducing structural mass and maintaining aerodynamic efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If active morphing technologies are used to change wing shape, then aerodynamic performance can be optimized, but structural weight and device complexity increase significantly
Solution Approach 1:
The wing structure uses its own aerodynamic loads to trigger and drive the morphing process. When gust loads exceed a threshold, the resulting deformation automatically activates the morphing mechanism without external actuators. The structure serves itself by using environmental loads as the actuation source, eliminating the need for heavy active control systems.
Solution Approach 2:
The wing transitions from a static, fixed geometry to a dynamic structure that can change shape in response to varying aerodynamic conditions. The morphing capability allows the wing to adapt its aerodynamic characteristics real-time, optimizing performance across different flight regimes while maintaining structural efficiency.
2Adaptability or versatility
If conventional fixed wing designs are used, then structural simplicity is maintained, but adaptability to changing aerodynamic conditions and mission segments is limited
Solution Approach 1:
The wing structure uses its own aerodynamic loads to trigger and drive the morphing process. When gust loads exceed a threshold, the resulting deformation automatically activates the morphing mechanism without external actuators. The structure serves itself by using environmental loads as the actuation source, eliminating the need for heavy active control systems.
Solution Approach 2:
The wing transitions from a static, fixed geometry to a dynamic structure that can change shape in response to varying aerodynamic conditions. The morphing capability allows the wing to adapt its aerodynamic characteristics real-time, optimizing performance across different flight regimes while maintaining structural efficiency.
3Duration of action of moving object
If structural mass fraction is reduced to improve endurance, then wing loading increases and structural strength decreases, making the aircraft vulnerable to gust conditions
Solution Approach 1:
The wing transitions from a static, fixed geometry to a dynamic structure that can change shape in response to varying aerodynamic conditions. The morphing capability allows the wing to adapt its aerodynamic characteristics real-time, optimizing performance across different flight regimes while maintaining structural efficiency.
Solution Approach 2:
The wing's geometric parameters (camber, twist, airfoil shape) are dynamically changed in response to aerodynamic loading conditions. By modifying these shape parameters passively, the structure optimizes its load distribution and aerodynamic efficiency without requiring active control systems, thereby maintaining reliability while reducing mass.
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 design effectively reduces structural mass fraction and wing loading, enhancing the endurance and reliability of HALE aircraft by allowing the wing to adapt passively to gust conditions, maintaining aerodynamic performance and stability while minimizing weight and complexity.
Implementation Method 1
A passive adaptive wing design utilizing buckling members that respond to aerodynamic loads by changing shape in a nonlinear, stepwise manner
Data Source
AI summary
Embodiments of the present airfoil systems comprise an airfoil with a leading edge, a trailing edge, an upper surface, a lower surface, and a skin surface, at least one structural element located within said airfoil, wherein said structural element supports the skin surface having an upper skin portion and a lower skin portion wherein said structural element can change its shape in response to external stimulus during flight operations, and an actuating means for selectively altering the curvature of said structural element which alters the curvature of said upper skin portion and of said lower skin portion to cause nonlinear deflection of said skin surface between an extreme raised position through a neutral position to an extreme lowered position; whereby the outer surface curvature of said airfoil and said skin surface is smooth and continuous over substantially the entirety thereof at all positions of said skin surface.