基于逆有限元的机翼蒙皮变形监测方法仿真研究

Simulation Study on Wing Skin Deformation Monitoring Based on Inverse Finite Element Method

针对机翼蒙皮变形动态监测需求,研究基于逆有限元法和应变信息的蒙皮变形重构方法。首先采用三节点三角形单元进行结构离散,并结合Kirchhoff板壳弯曲理论进行力学建模;然后通过理论推导得出应变与位移的关系,完成变形重构算法的构造,并开发出了实时显示机翼蒙皮结构变形的可视化软件平台;最后以翼形蒙皮结构和方形蒙皮结构为研究对象,通过仿真计算分析验证了重构算法的正确性和通用性。研究结果表明,在应变测点密度为2个/m^(2)条件下,结构变形重构均方根误差为1.2%,重构时间<20ms。基于逆有限元法的变形重构方法可用于机翼蒙皮变形重构,在飞行器结构变形监测领域具有应用前景。

Aiming at the dynamic monitoring requirements of wing skin deformation,a skin deformation reconstruction method based on inverse finite element method and strain information was studied.Firstly,the threenode triangular element was used to discretize the structure,and the Kirchhoff plate and shell bending theory was used to construct the mechanical model.Then,the relationship between strain and displacement is deduced theoretically,the reconstruction algorithm is constructed,and a visualization software platform is developed to display the deformation of wing skin structure in real time.Finally,the airfoil skin structure and square skin structure are taken as the research objects,and the correctness and versatility of the reconstruction algorithm are verified by simulation analysis.The results show that the root mean square error of structural deformation reconstruction is 1.2%and the reconstruction time is less than 20ms when the density of strain measuring points is 2/m^(2).The deformation reconstruction method based on the inverse finite element method can be used in the deformation reconstruction of wing skin,which has a promising application in the field of aircraft structural deformation monitoring.