Rigid-Flexible Morphing Wing with SMA Actuation
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Solution Overview
Problem
Current UAV morphing wing technologies face challenges with uncontrollable deformation, requiring more advanced materials and manufacturing methods to achieve flexible and adaptive aerodynamic configurations.
Innovation Solution
A rigid-flexible coupled UAV morphing wing structure is developed using high-strength and low-strength shape memory materials, with SMA strips/wires and reinforcing ribs, fabricated through additive manufacturing, allowing for controlled up-and-down and back-and-forth deformations via electric heating elements, and SMA polymer composite strips/springs for wingtip control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If traditional metal parts processing methods are used, then manufacturing precision can be achieved, but the manufacturing cycle is long and cost is high
Solution Approach 1:
The patent changes the manufacturing method from traditional subtractive metal processing to additive manufacturing (3D printing). This parameter change enables direct fabrication of complex morphing wing structures with precise deformation characteristics, significantly reducing manufacturing cycle time while maintaining the required precision for controlled deformation at 30° and wingtip at 70°.
Solution Approach 2:
The patent incorporates deformation characteristics directly into the 3D printing process by pre-programming the geometric features and material distribution within the printed structure. This preliminary action embeds the desired deformation behavior (30° wing deformation, 70° wingtip deformation) into the manufacturing process itself, eliminating subsequent complex assembly and adjustment steps.
2Device complexity
If simple deformation modes are used, then the structure is simpler, but the deformation amplitude is small
Solution Approach 1:
The patent employs composite material structures within the 3D printed morphing wing, combining materials with different deformation characteristics. This enables the structure to achieve large deformation amplitudes (30° wing deformation, 70° wingtip deformation) while maintaining a relatively simple overall structure, as the composite material properties provide the necessary mechanical behavior.
Solution Approach 2:
The patent utilizes three-dimensional internal structuring within the printed components to achieve complex deformation patterns. By varying material density, orientation, and distribution in three dimensions during printing, the structure can achieve large deformation amplitudes through internal geometric design rather than complex external mechanisms.
3Strength
If high-strength materials are used throughout the wing, then structural strength is improved, but flexibility and deformation capability are reduced
Solution Approach 1:
The patent applies local quality by varying material properties at different locations within the morphing wing structure. High-strength materials are used in regions requiring structural integrity, while regions requiring deformation incorporate materials with appropriate flexibility characteristics. This local differentiation enables the structure to achieve both high overall strength and localized deformation capability (30° wing deformation, 70° wingtip deformation).
Solution Approach 2:
The patent creates a dynamic structure where material properties are optimized for different operational states. The 3D printed structure incorporates variable material distribution that allows the wing to transition between rigid and flexible states as needed, achieving both structural strength and deformation capability through spatially varying material characteristics.
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
Enables precise deformation control of the wing up to 30° and wingtip up to 70°, enhancing adaptability and performance in various flight conditions, while improving manufacturing efficiency.
Implementation Method 1
Use the deformation characteristic of the shape memory materials to control the up-and-down and back-and-forth deformation of the morphing, and the up-and-down deformation of the wingtip
Implementation Method 2
allows for controlled up-and-down and back-and-forth deformations via electric heating elements
Data Source
AI summary
A rigid-flexible coupled unmanned aerial vehicle (UAV) morphing wing and an additive manufacturing method thereof are disclosed. A shape memory alloy (SMA) strip/wire for controlling the wing upward deformation and an SMA strip/wire for controlling the wing downward deformation are arranged alternately, and a plurality of reinforcing ribs are arranged at intervals on the SMA strips/wires for controlling the wing upward deformation and the SMA strips/wires for controlling the wing downward deformation. The SMA strips/wires for controlling the wing upward deformation and the SMA strips/wires for controlling the wing downward deformation are arranged on a flexible substrate, and are wrapped with an insulating covering. The SMA strips/wires for controlling the wing upward deformation and the SMA strips/wires for controlling the wing downward deformation each are provided with an electric heating element.