复合材料层合壳结构多体系统动力学理论研究和实验验证

Recently, composite material is widely used in the research field of aeronautics, astronautics and mechanical engineering. The rotating blade of helicopter, wind turbine blade，aircraft wing, satellite antenna and satellite plate can be regarded as composite laminated shells. It was found that the anisotropic characteristics of the composite material may cause coupling among large overall motion and different kinds of deformations, such as stretch deformation, bending deformation, torsion deformation, transverse deformation and section warping, which leads to high nonlinearity of the system.. In this project, considering anisotropic effect, heterogeneous characteristics of different layers, transverse shear deformation, section warping deformation and geometric nonlinear effect, more accurate dynamic model of composite laminated shell multibody system with large deformation is established based on the theory of nonlinear continuum mechanics and flexible multibody system dynamics. In order to reduce the simulation cost of composite shell multibody system, efficient numerical method for the simulation of composite shell multibody system are proposed. Rigid-flexible coupling dynamic experiments of hub and laminated shell multibody system are carried out to verify the correctness of the proposed theory. Based on this, applicability of the traditional one-dimensional model of composite cylinderical shell is analyzed. The proposed modeling theory can be used for accurate simulation of complicated multibody system, such as wind turbine, helicopter and other thin-walled structure.

目前，复合材料广泛应用于航空航天和机械工程领域。直升机的旋翼、风力发电机的桨叶、飞机的机翼、航天器的天线和太阳翼均可视为复合材料层合壳结构柔性附件，复合材料的各向异性性质将引起大范围运动和拉伸变形、弯曲变形、扭转变形、剪切变形和翘曲变形的相互耦合，呈现高度非线性特征。.本项目考虑材料的各向异性、各层之间的非均匀性、横向剪切变形、断面的翘曲变形和几何非线性效应，基于非线性连续介质力学理论和柔性多体系统动力学理论建立大变形复合材料层合壳结构多体系统的动力学模型。为了解决复合材料壳结构多体系统计算量大的问题，研究快速收敛的数值计算方法。通过气浮台和复合材料层合壳结构多体系统的刚-柔耦合动力学实验验证建模理论的正确性。在此基础上对复合材料圆柱壳的一维有限元近似模型的适用性进行分析。本项目提出的动力学建模方法可应用于风力发电机和直升机等复杂结构多体系统的高精度数值仿真。

目前，复合材料广泛应用于航空航天和机械工程领域。直升机的旋翼、风力发电机的桨叶、飞机的机翼、航天器的天线和太阳翼均可视为复合材料层合壳结构柔性附件，复合材料的各向异性性质将引起大范围运动和拉伸变形、弯曲变形、扭转变形、剪切变形和翘曲变形的相互耦合，呈现高度非线性特征。. 本项目考虑材料的各向异性、各层之间的非均匀性、横向剪切变形、断面的翘曲变形和几何非线性效应，基于非线性连续介质力学理论和柔性多体系统动力学理论建立大变形复合材料层合壳结构多体系统的动力学模型。为了解决复合材料壳结构多体系统计算量大的问题，研究快速收敛的数值计算方法。通过气浮台和复合材料层合壳结构多体系统的刚-柔耦合动力学实验验证建模理论的正确性。在此基础上对复合材料圆柱壳的一维有限元近似模型的适用性进行分析。本项目提出的动力学建模方法可应用于风力发电机和直升机等复杂结构多体系统的高精度数值仿真。. 为了拓宽建模理论的应用范围，进一步对柔性多体系统接触碰撞动力学建模，考虑刚-柔-热耦合复合材料层合板动力学建模，空间薄膜展开过程的动力学建模和考虑滑动铰间隙的伸展式太阳翼展开动力学建模方法开展研究。