大型航天器结构-控制-光学一体化建模与微振动响应快速计算方法  

Model of Large Spacecraft Integrated Structure-Control-Optical and FastCalculation of Micro-vibration Response

作　　者：李建宏宇 庞贺伟[2] LI Jian-hong-yu;PANG He-wei(National key Laboratory of Science and Technology on Reliability and Environmental Engineering,Beijing Institute of Spacecraft Environment Engineering,Beijing 100094,China;China Academy of Space Technology,Beijing 100094,China)

机构地区：[1]北京卫星环境工程研究所可靠性与环境工程技术重点实验室,北京100094 [2]中国空间技术研究院,北京100094

出　　处：《装备环境工程》2020年第6期1-6,共6页Equipment Environmental Engineering

摘　　要：目的控制大型航天器一体化模型的计算成本。方法分别使用状态空间法和附加刚度法建立结构-控制-光学一体化模型,并求解微振动响应。使用稀疏矩阵LU分解法和迭代法求解线性方程来加速微振动响应的求解速度。结果对某大型航天器建立一体化模型,并求解微振动响应,总耗时10.35 s,其中使用迭代法计算2794个频率点耗时7.20s,使用稀疏LU分解法计算6个频率点耗时3.15s。结论数值算例证明了该方法的高效性,是适用于实际工程中大型航天器微振动预示的高效算法。The paper aims to control the calculation cost of integrated model for large spacecraft.The state-space method and the additional stiffness method were used to build the structure-control-optical integration model and solve the micro-vibration response.The sparse matrix LU decomposition method and iterative method were used to solve linear equations to accelerate the solution speed of the micro-vibration response.An integrated model was established for a large spacecraft and the micro vibration response was solved.The total time was 10.35s,among which the time used to calculate the 2794 frequency points by iterative method was 7.20s,and that used to calculate 6 frequency points by sparse LU decomposition method was 3.15s.Numerical examples show the efficiency of the method.It is an efficient algorithm for the prediction of micro vibration of large spacecraft in practical engineering.

关 键 词：一体化模型 微振动响应 附加刚度法 快速计算 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程]