【摘要】 后缘可变弯度机翼在改善飞行器气动性能方面具有显著优势，采用光滑连续的柔性变形能够获得更好的气动性能。本文提出了一种基于力学超材料的柔性可变后缘结构，以NACA4418翼型为基本翼型分析机翼变形前后气动性能变化，通过对两种不同结构的力学超材料进行单元布局组合，开展了柔性机翼变形驱动的逆向结构分布式设计，基于增材制造技术制造装配了超材料单元机翼实物，试验结果表明，该方法设计的机翼样段结构较轻，变形响应速度快，能够在1s内实现柔性后缘偏转22.4°，整体结构易于制造装配，可有效实现机翼后缘的柔性变弯度。更多还原

【Abstract】 The trailing edge variable camber wing has significant advantages in improving the aerodynamic performance of aircraft. Using smooth and continuous flexible deformation can obtain better aerodynamic performance. In this paper,a flexible variable trailing edge structure based on mechanical metamaterial is proposed. NACA4418 airfoil is taken as the basic airfoil to analyze the changes of aerodynamic performance before and after wing deformation. Through the layout and combination of mechanical metamaterial elements with two different structures, the distributed design of the reverse structure driven by the deformation of the flexible wing is carried out. The real object of the metamaterial element wing is manufactured and assembled based on the additive manufacturing technology. The experimental results show that the wing sample structure designed by this method is light, the deformation response speed is fast, and the flexible trailing edge deflection of 22.4° can be achieved within 1s. The overall structure is easy to manufacture and assemble, and the flexible camber of the trailing edge of the wing can be effectively achieved.更多还原