Page 37 - 《振动工程学报》2026年第2期
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第 39 卷第 2 期                       振 动 工 程 学 报                                       Vol. 39 No. 2
               2026 年  2 月                     Journal of Vibration Engineering                       Feb. 2026



                      卫   星    大   型   柔   性    天   线   全   局   模    态   法   力   学   特    性   分   析



                                  朱光楠 ， 何贵勤 ， 李晓蕊 ， 王俊喆 ， 韦常柱 ，
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                                         毛永飞 ， 王 涛 ， 张 玥 ， 董 晴                     4
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                     （1. 哈尔滨工业大学数学学院，黑龙江 哈尔滨 150001； 2. 哈尔滨工业大学航天学院，黑龙江 哈尔滨 150001；
                         3. 中国运载火箭技术研究院，北京 100076； 4. 中国空间技术研究院遥感卫星总体部，北京 100094）
              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。
              关键词： 全局模态法；平面相控阵天线；刚柔耦合；模态分析
              中图分类号：O313.7；O327；V474        文献标志码：A        DOI：10.16385/j.cnki.issn.1004-4523.202312017



                         Mechanical characteristics analysis of large flexible antenna satellite
                                              based on global mode method

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                               ZHU Guangnan ，HE Guiqin ，LI Xiaorui ，WANG Junzhe ，WEI Changzhu ，
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                                       MAO Yongfei ，WANG Tao ，ZHANG Yue ，DONG Qing   4
                        （1.School of Mathematics， Harbin Institute of Technology， Harbin 150001, China；2.School of Astronautics，
                Harbin Institute of Technology，Harbin 150001，China；3.China Academy of Launch Vehicle Technology，Beijing 100076，China；
                           4.Institute of Remote Sensing Satellite，China Academy of Space Technology，Beijing 100094，China）
              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 7th 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.

              Keywords：global mode method；planar phased array antenna；rigid-flexible coupling；modal analysis


                  收稿日期：2023-12-06；修订日期：2024-07-17
                  基金项目：五院     CAST  创新基金项目（1020J20220088）
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