摘要
某型号卫星的有效载荷支架结构在验收级振动试验时振动超标。在对结构不做大的修改的前提下,采用约束阻尼层用对原结构进行处理。对不同的约束阻尼层方案采用有限元方法进行计算,综合考虑各种影响因素,如阻尼比和附加质量等,得到合理的约束阻尼减振方案,并在结构星上进行试验,确定最终实施方案。实施方案后,正样星在0.1g振动条件下,最大振动幅值下降了22.3%,保证了卫星的顺利发射。该卫星已经成功发射,并且在轨运行正常。该问题的成功解决和解决问题的方法与过程为今后解决类似问题提供了经验。
In the final check-and-accept level test, the vibration of a payload bracket in a satellite failed to be qualified for the launch. Without redesigning and changing the original structure, the constrained damping layer （CLD）, which was arranged on the outer surface of the structure components, was adopted as a means of suppressing the vibration. In the design procedure of the CLD, the technique of finite element analysis was used for selecting the project, which includes the thickness of damping layer and constrained layer and the position of arrangement. Then with all factors considered, such as damping ratio and additional mass, a rational project of constrained damping layer is gained. After first tested in a tested satellite to confirm the final CDL project, the CLD project was performed on the final-model satellite. With this treatment, the maximum vibration amplitude of the satellite has been decreased 22.3% in the 0. 1g level vibration test, which is acceptable for the launch. The satellite was launch successfully and has been working normally in the orbit since then. The technique and the procedure of design provide valuable experience for treating similar problems in the future.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2006年第3期503-506,共4页
Journal of Astronautics
关键词
支架
约束层阻尼
模态应变能
Payload bracket
Constrained layer damping
Modal strain energy
