一种非对称充气机翼的设计方法与力学分析

Research of Designing Methods and Dynamics Analysis of Asymmetrical Inflatable Wing

充气机翼技术有着悠久的历史,作为一项可以有效减小存储体积的方法,在航空领域有着独特的发展优势。针对NACA4418翼型,通过编程确定并筛选翼型内接圆圆心组,进而通过三维建模软件完成该非对称充气机翼的设计,然后利用ANSYS对该充气机翼进行静力学分析和模态分析,之后用FLUENT对该机翼翼型进行气动特性仿真分析,同时与相应的标准翼型进行了对比。最后对得到的仿真数据进行了分析,得出了充气机翼的刚度随着充气压力的增加而增加且充气机翼翼型的升力系数比标准翼型低,同时阻力系数比标准翼型高的结论。

Inflatable wings technology had a long and rich history. As a method of available decreasing the packing volume of vehicles, it has unique advantage in the field of aviation. This paper provided a design for NACA4418 inflatable wings. The circle center group of the inner circle of the airfoil was determined and selected by programming, and the design of the asymmetric inflatable wing was completed by three-dimensional modeling software.The static analysis and modal analysis of the inflatable wing were carried out by ANSYS. Then, the aerodynamic characteristics of the wing were simulated and analyzed by fluent, and compared with the corresponding standard airfoil.In the end, it came to a conclusion by analyzing that the stiffness of inflatable wings increases with the increase of inlet pressure. And there was also a conclusion that the lift coefficient of the inflatable wing is lower than the standard wing, while the drag coefficient of the inflatable wing is higher than the standard one.