目的 研究某航天器在运输过程中的动力学特性，以及适配器包装材料对其振动特性的影响。方法 以航天器-适配器-运输筒系统为研究对象，应用ABAQUS有限元软件建立柔性多体动力学模型，对模型进行模态分析和谐响应分析，得到系统的前四阶模态振型和航天器关键节点的位移响应曲线。最后分析适配器主体材料聚氨酯泡沫的弹性模量、阻尼以及适配器的海绵与聚氨酯泡沫的厚度比对航天器振动位移的影响。结果 航天器和运输筒的高阶固有频率对航天器结构的动态性能影响很小，其头部位置的谐响应振动位移最大，且振动位移随着适配器聚氨酯泡沫弹性模量和阻尼的增大而减小，厚度比接近7∶40的减振性能最好。结论 该方法可以准确有效地为适配器材料特性的选择和结构参数的设计提供依据。

The work aims to study the dynamic characteristics of a spacecraft during transportation and the influence of the adapter material on its vibration characteristics. With the spacecraft-adapter-transport cylinder system as the study object, the flexible multi-body dynamic model was established by the ABAQUS finite element software. The modal analysis and harmonic response analysis of the model were carried out. The first four-order mode shape of the system and the displacement response curve of the key nodes of the spacecraft were obtained. Finally, the elastic modulus, damping and the influence of the thickness ratio of the adapter sponge and polyurethane foam on the vibration displacement of the spacecraft were analyzed. The high-order inherent frequency of the spacecraft and transport cylinder had little impact on the dynamic performance of the spacecraft structure. The harmonic response vibration displacement of its head was the largest, and the displacement was reduced with the increase in the elastic modulus and damping of the adapter’s polyurethane foam. The damping performance was the best when the thickness ratio was approximate to 7∶40. Such method can provide the basis for the selection of the material characteristics of the adapter and the design of the structural parameters accurately and effectively.