Folding Articulating Wing Mechanism With Curvilinear Locking
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Solution Overview
Problem
Current deployable wing mechanisms face challenges in efficiently transitioning between fully retracted and fully deployed positions, requiring complex actuation systems and often compromising on structural integrity and aerodynamic efficiency.
Innovation Solution
A folding and locking wing mechanism featuring a base with an integrally formed cylindrical mounting hub and a wing made of impact-resistant materials, utilizing a multi-staged screw shaft and curvilinear surfaces for secure engagement and rotation, allowing for smooth deployment and locking without sharp transitions, and incorporating a torsion spring for assisted deployment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If complex actuation systems are used for deploying wings, then the wing can transition between retracted and deployed positions, but the device complexity increases
Solution Approach 1:
The wing is divided into multiple segments that can be independently controlled. Each segment has its own actuation mechanism, allowing the wing to be deployed in stages rather than as a single complex movement, thereby reducing overall system complexity while maintaining full deployment capability
Solution Approach 2:
The wing structure incorporates movable joints and articulation points that allow dynamic adjustment during deployment. The wing can transition from a retracted position to a deployed position through controlled rotation at multiple joints, enabling operation without requiring a complex fixed-geometry actuation system
2Speed
If sharp transitions are used in wing deployment, then the deployment speed increases, but structural stress increases
Solution Approach 1:
The wing structure incorporates curved surfaces and gradual transition zones instead of sharp angles or abrupt changes in geometry. The curvilinear design allows stress to be distributed more evenly during deployment, reducing peak stresses while maintaining high deployment speed through optimized curvature profiles
Solution Approach 2:
The wing structure includes built-in compliance elements and stress-distributing features positioned at critical locations before deployment occurs. These features are designed to absorb and distribute impact stresses that occur during rapid deployment, preventing stress concentration while maintaining deployment speed
3Productivity
If gap-free symmetric airfoil shape is maintained during deployment, then aerodynamic efficiency is improved, but the mechanism complexity increases
Solution Approach 1:
The wing employs asymmetric control surface arrangements and differential actuation of wing segments to achieve symmetric aerodynamic profiles during deployment. By using asymmetric mechanisms in a controlled manner, the wing can transition through intermediate positions while maintaining symmetric airfoil shapes, improving aerodynamic efficiency without requiring overly complex symmetric mechanisms
Solution Approach 2:
The deployment mechanism dynamically adjusts the position and orientation of wing segments in real-time to maintain a gap-free symmetric airfoil shape during transition. Control systems monitor wing position and adjust actuation commands to ensure symmetric profiles are maintained throughout deployment, achieving high aerodynamic efficiency through dynamic control rather than static mechanism design
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 mechanism enables reliable, high-speed deployment and locking of the wing with reduced structural stress and aerodynamic drag, maintaining a gap-free, symmetric airfoil shape, and can withstand rotational impacts, enhancing flight control and operational efficiency.
Implementation Method 1
incorporating a torsion spring for assisted deployment
Data Source
AI summary
Obliquely folding articulating wing mechanisms that include a wing rotatingly connected to a base.