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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。
Aim To study the dynamic characteristics of a spacecraft during transportation and the influence of adapter packing material on its vibration characteristics. Methods Taking the spacecraft-adapter-transport tube system as the research object, a flexible multi-body dynamic model was established by ABAQUS finite element software. The modal analysis and harmonic response analysis of the model were carried out. The first four modes of the system and spacecraft Displacement response curve of key nodes. Finally, the influence of the elastic modulus and damping of the main body of the adapter and the thickness ratio of the sponge to the polyurethane foam on the vibration displacement of the spacecraft are analyzed. Results The high-order natural frequencies of the spacecraft and the transport tube have little influence on the dynamic performance of the spacecraft structure. The harmonic response of the head position has the largest vibration displacement, and the vibration displacement increases with the increase of the elastic modulus and damping of the polyurethane foam Reduce, the damping ratio of the thickness ratio close to 7:40 is the best. Conclusion This method can provide the basis for the choice of material properties and the design of structural parameters accurately and effectively.