Design, analysis, and experimentation of SMA-driven multi-state variable camber wing
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摘要:
变弯度作为变形机翼最典型的一种变形形式，在未来智能飞行器设计领域具有广阔应用前景。针对多状态、连续变弯度机翼的设计需求，提出一种结合模块化刚柔耦合结构、交叉簧片式铰链、多级形状记忆合金(SMA)驱动器的新型变弯度机翼设计方案。针对该方案，结合交叉簧片式铰链等效刚度计算方法，推导单级、多级模块单元的等效刚度结构力学模型，并通过有限元分析完成对比验证；搭建准静态流固耦合分析模型，通过SMA完全相变驱动方式验证所提变弯度机翼方案的多状态调节能力、多工况适应性，并给出各变形状态对气动系数的影响规律；研制原理样机并搭建测试平台，完成基于前馈开环控制策略的多状态变形控制效果，验证了所提多状态变弯度机翼设计的工程可行性。
Abstract:The most common type of morphing wing in the field of intelligent aircraft design for the future is variable camber, which offers a wealth of opportunities. This paper addresses the design requirements of a multi-state, continuously variable camber wing and proposes a novel design scheme integrating a modular rigid-flexible coupling structure, cross-leaf hinge, and multi-stage shape memory alloy (SMA) actuators. According to the scheme, the equivalent stiffness structural mechanics model of single-stage and multi-stage modular elements is derived by combining the equivalent stiffness calculation method of the cross-leaf hinge, and the comparison and verification are completed by finite element analysis. Furthermore, a quasi-static fluid-structure coupling analysis model was established, verifying the proposed variable camber wing scheme’s multi-state adjustment capability and adaptability under various conditions using SMA’s full phase transition driving, and providing the impact patterns of each deformation state on aerodynamic coefficients. Finally, a conceptual prototype was developed, and a testing platform was constructed. A feedforward open-loop control technique based on multi-state deformation control was successfully implemented, confirming the engineering feasibility of the suggested multi-state variable camber wing design.
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Key words:
- variable camber wing /
- cross-leaf hinge /
- multi-state /
- shape memory alloy /
- experimental verification
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图 2 SMA升温段温度与力的关系
Figure 2. The relationship between temperature and force in SMA during heating
图 3 后缘结构及其子模块单元受力示意图
Figure 3. The force diagram depicting the trailing edge structure and its sub-module units
图 4 后缘结构有限元网格及载荷作用位置示意图
Figure 4. Finite element mesh and load application position diagram of the trailing edge structure
图 5 理论模型与有限元模型分析结果对比
Figure 5. Comparison of analysis results between theoretical model and finite element model
图 6 后缘结构多状态变形效果示意图
Figure 6. Schematic diagram of multi-state deformation effect of the trailing edge structure
图 8 机翼各状态气动系数变化
Figure 8. The aerodynamic coefficient variations across various wing states
图 11 机翼结构实验与仿真变形趋势
Figure 11. Experimental and simulation deformation trend in wing structure
图 14 机翼多状态变形控制策略
Figure 14. Multi-state wing deformation control strategy for aircraft wings
表 1 机翼多状态变形
Table 1. Multiple-state deformation of the wing
加热位置 变形状态 SET1 状态1 SET2 状态2 SET3 状态3 SET1、SET2 状态4 SET2、SET3 状态5 SET1、SET2、SET3 状态6 
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表 3 实验数据与仿真数据相对误差
Table 3. Relative error between experimental and simulation data
变形状态 相对误差/% 状态1 3.88 状态2 3.09 状态3 2.59 状态4 7.36 状态5 7.08 状态6 8.96
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表 4 机翼各变形状态的等效偏转角
Table 4. The equivalent deflection angles of the wing in various deformation states
变形状态 等效偏转角/（°） 状态1 5.0 状态2 8.0 状态3 10.5 状态4 11.8 状态5 15.6 状态6 17.8
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