摘要
给出了一种适合工程应用的挠性卫星在轨模态计算分析方法:先通过地面试验对有限元模型进行校核,求出挠性附件约束模态结果,再结合整星动力学将约束模态转换成非约束模态结果。实例计算结果表明该方法能够准确计算挠性卫星在轨模态。工程中卫星在轨模态频率计算误差可在15%以内。
A method of on-orbit modal calculation suitable for the engineering application is presented in this article. Firstly, the finite element model should be corrected through the ground test, and the constraint modal results of flexible appendages will be extracted. Combining with the dynamics equation of entire satellite, the constraint modal will be translated into unconstraint modal by using the eigenvalue method. The example shows that the method in this article can calculate the on-orbit modal frequency accurately. In engineering, the error of on-orbit frequency will be under 15%.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2014年第4期404-409,共6页
Journal of Astronautics
基金
国家973计划项目(2013CB834103)
关键词
挠性卫星
在轨动力学
非约束模态
Flexible satellite
On-orbit Dynamics
Unconstraint modal