【摘要】 卫星天线向着大尺寸、轻量化方向发展，其惯性特性在卫星整体中占较大比例，导致姿态运动与结构振动的耦合效应突出，采用柔性结构的部件级模态进行分析会产生较大误差。为此，本文以装配有平面相控阵大型天线的卫星模型为例，提出了一种携带铰接多板柔性卫星的低维、高精度结构动力学解析建模方法，并以铰链刚度为例研究系统关键参数对动力学特性的影响。研究表明，本方法可使用一组统一广义坐标对大天线卫星各个部件的刚体运动和弹性振动进行精确描述，且该方法对系统模态特性的分析可在特征正交多项式7阶截断的条件下稳定收敛，并保证频率偏差相比有限元仿真模型不超过2%；通过对铰链刚度的分析可知，系统振动频率随铰链刚度的增大而升高，并且在铰链刚度从500变化至5000 N·m/rad的过程中，系统发生模态跃迁现象。结果证明，本文方法克服了铰接多板组合结构弹性振动和板间铰链刚体转动的耦合效应，给出了多点约束下非经典边界的多板解析全局模态的一般方法，突破了现有杆梁组合结构全局模态方法的局限，为精确获取柔性卫星的固有频率和全局模态函数，发展求解大型柔性卫星的刚柔耦合全局模态一般方法提供了有效途径。更多还原

【Abstract】 With the development of satellite antennas towards large size and lightweight,the inertial characteristics of satellite antennas would lead to significant effects throughout entire satellite, which results in prominent coupling effect between attitude motion and structural vibration. In that case,usinge component-level modes of flexible structures will cause huge errors in model analysis. To solve the problems mentioned above,a low dimensional and high-precision structural dynamics analytical modeling method for carrying articulated multi-plate flexible satellites is proposed, and the influence of key parameters of the system such as hinge stiffness on its dynamic characteristics is studied,taking a satellite model equipped with a large planar phased array antenna as example. Research shows that the rigid motion and elastic vibration of various components of a large antenna satellite can be accurately described by a set of unified generalized coordinates,and the analysis of the system modal characteristics can stably converge under the condition of 7 th order truncation of the characteristic orthogonal polynomial,while ensuring that the error of frequency does not exceed 2% compared to the finite element simulation model. Through the analysis of hinge stiffness, it is known that the vibration frequency of the system increases with the increase of hinge stiffness, and the phenomenon of modal transition occurs with the hinge stiffness changing from 500 to 5000 N·m/rad. The result proves that the difficulty of model analysis caused by the coupling effect of elastic vibration and rotation of the hinged multi-plate structures can be overcome by the method proposed, and a general method for analyzing the global mode of multi-plate structure under non-classical boundaries with multi-point constraints has been provided. The limitations of existing global mode methods for rod beam composite structures has been broken through,as well an effective approach for solving the rigid flexible coupling global mode of large flexible satellites has been provided.更多还原