航天器薄壳柔性附件展开耦合行为特性研究

为研究大范围运动柔性附件几何非线性和耦合效应与中心刚体的精确动力学行为，以薄壳结构柔性附件为研究对象，引入非线性应变和位移关系，利用虚功原理推导了做大范围运动带柔性附件航天机构的完整非线性动力学模型，所构建的模型包含了非线性几何变形及附加非线性项。针对线性和非线性模型，相应开展了大范围运动航天机构刚柔耦合数值分析。结果表明，随着转速增大，线性与非线性模型动力学特性产生根本差异，指出线性模型忽略了非线性耦合项的不足，而非线性模型可精确地预测大范围运动带柔性附件航天机构动力学行为。结论对航天机构定向和跟踪操作的动力学与控制具有重要的理论价值及工程实际意义。

Study on Coupling Behavior of Spacecraft Deployment with Flexible Appendages of Shell Structure

A dynamics modeling method is presented for spacecraft with flexible appendages. The dynamics equations are derived taking into account the geometric nonlinearity and coupling deformation terms caused by a large overall motion. And then the nonlinear strain-displacement relations are introduced, and the nonlinear dynamics model of spacecraft is deduced according to the virtual work principle. The complete expressions of geometric nonlinearity and dynamic stiffness terms are considered in the dynamics equations. Spacecraft dynamics are analyzed for linear model and nonlinear model respectively. By comparing these models, both correctness and accuracy of present nonlinear model are verified. Because geometric nonlinearity and dynamic stiffness terms are ignored in the traditional linear model, it is not suitable for dealing with large deformation rigid-flexible problems under the condition of a large overall motion. Furthermore, as the rotational speed increases, efficient and accurate prediction of dynamics behavior for spacecraft with flexible appendages is achieved by using the present nonlinear model. The above conclusion has important academic value and engineering significance.