摘要
为了评估航天器上存在的反作用轮产生微振动力学环境对其有效荷载的指向精度和稳定度的影响,提出一种数值模拟航天器振动控制中激励源的新思路。以Ithaco B-wheel测试实验为背景模拟功率谱数据,对航天器飞轮干扰力经典线性稳态模型进行参数识别。在此基础上,推导了飞轮干扰力功率谱函数,并采用修正傅里叶谱法得到飞轮干扰力的时程曲线,作为研究航天器隔减振系统的激励源。结果表明,模拟的时程曲线符合反作用轮干扰力作为微振动力学环境的特征。
In order to evaluate the performance degradation of satellite instrument caused by many possible disturbance source environments on a precision spacecraft,a new method of jitter simulation for vibration control of spacecraft is proposed.Then a database is set at the background of Ithaco B-wheel test,and then a steady-state empirical model consisting of discrete harmonics of the wheel speed is used and its power spectral density(PSD)function is derived with the determined parameters in Matlab.Finally,the modified Fourier Spectrum method is employed to obtain the reaction wheel assembly force in time-domain.The result suggests that it is reasonable for reaction wheel assembly to be simulated by this method.
出处
《振动．测试与诊断》
EI
CSCD
北大核心
2013年第5期881-885,917,共5页
Journal of Vibration,Measurement & Diagnosis
基金
国家基础研究发展计划("九七三"计划)资助项目
国家自然科学基金资助项目(11176008)
江苏省高校优势学科建设项目
常州市科技支撑资助项目(CE20120035)
关键词
微振动
时程曲线
修正傅里叶谱法
反作用轮干扰力经典稳态模型
仿真分析
jitter
travel-time curve
modified Fourier spectrum method
steady-state empirical model of reaction wheel assembly
simulation
