圆形薄膜太阳翼展开动力学分析与模态分析

Deployment Dynamic Analysis and Modal Analysis of Circular Membrane Solar Arrays

针对圆形薄膜太阳翼展开过程中存在的柔性大、非线性强、耦合程度高以及展开过程复杂等问题,本文以UltraFlex太阳翼为研究对象,使用膜单元模拟翼面,相比于壳单元获得了更好的展开效果,利用非线性有限元软件SAMCEF对其展开过程进行动力学仿真分析,通过分析系统展开过程中能量变化曲线,研究不同转角驱动函数对其展开稳定性的影响。对圆形薄膜太阳翼展开锁定状态进行模态分析,与NASA的ANSYS分析结果相一致。将分析结果与NASA UltraFlex样机试验结果进行对比,模态频率误差在6.77%以内,符合美国TRL6技术标准,验证了SAMCEF有限元数值仿真模型的准确性和有效性,具有一定的工程实际意义。

For the purpose of solving the problems such as large flexibility, strong nonlinearity, high coupling and complex deployment process of the circular membrane solar arrays, the UltraFlex solar wing is taken as the research object in this paper, using the membrane element to simulate the wings and get a better deployment effect than using the shell element. The nonlinear finite element software SAMCEF is used to carry out the dynamic simulation analysis of the expansion process of UltraFlex. By analyzing the energy change curve in the system expansion process, the influence of different rotation angle driving functions on its expansion stability is studied. The modal analysis for the locked state of the circular membrane solar arrays is also studied. The simulation results fit with ANSYS from NASA well, and these results are compared with the UltraFlex-175 prototype test from NASA. As the results shown, the error is within 6.77%, which conforms to the US TRL6 standard, validating the accuracy and the effectiveness of the FEM numerical model. This research has crucial practical significance.