Zhang Haibo, Yang Haolin, Yang Yongjian, Song Chen, Yang Chao
School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China.
Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang 621900, China.
Biomimetics (Basel). 2024 Oct 18;9(10):641. doi: 10.3390/biomimetics9100641.
The in-plane folding wing is one of the important research directions in the field of morphing or bionic aircraft, showing the unique application value of enhancing aircraft maneuverability and gust resistance. This article provides a structural realization of an in-plane folding wing and an aeroelasticity modeling method for the folding process of the wing. By approximating the change in structural properties in each time step, a method for calculating the structural transient response expressed in recursive form is obtained. On this basis, an aeroelasticity model of the wing is developed by coupling with the aerodynamic model using the unsteady panel/viscous vortex particle hybrid method. A wind-tunnel test is implemented to demonstrate the controllable morphing capability of the wing under aerodynamic loads and to validate the reliability of the wing loads predicted by the method in this paper. The results of the gust simulation show that the gust scale has a significant effect on the response of both the open- and closed-loop systems. When the gust alleviation controller is enabled, the peak bending moment at the wing root can be reduced by 5.5%∼47.3% according to different gust scales.
平面折叠机翼是变形或仿生飞行器领域的重要研究方向之一，展现出增强飞行器机动性和抗阵风能力的独特应用价值。本文给出了一种平面折叠机翼的结构实现方式以及机翼折叠过程的气动弹性建模方法。通过近似每个时间步长内结构特性的变化，得到了一种以递归形式表示的结构瞬态响应计算方法。在此基础上，采用非定常面板/粘性涡粒子混合方法，通过与气动模型耦合建立了机翼的气动弹性模型。开展了风洞试验，以展示机翼在气动载荷作用下的可控变形能力，并验证本文方法预测的机翼载荷的可靠性。阵风模拟结果表明，阵风尺度对开环和闭环系统的响应均有显著影响。启用阵风减缓控制器后，根据不同的阵风尺度，机翼根部的峰值弯矩可降低5.5%∼47.3%。
