摘要
反作用轮是影响航天器姿态控制系统精度的主要扰动源之一。为了研究反作用轮扰动对在轨航天器产生的影响,并采取相应的控制方法和隔离系统,分析了引起反作用轮扰动的原因,建立了基于反作用轮扰动试验模型的扰动精细模型。在此基础上建立了航天器整星在轨状态结构有限元模型,将反作用轮扰动作为激励源,进行了整星在轨状态结构动态特性仿真,详细地分析了反作用轮扰动对整星结构动态特性的影响。仿真分析结果可以准确地预测反作用轮扰动对在轨航天器动态特性的影响,有利于航天器星载设备的分布和安装,可以提高星载设备的精度和性能,并为航天器姿态控制系统设计和地面试验提供了参考和依据。
Reaction wheel is one of the main disturbance sources for the attitude control system accuracy of spacecraft. In order to study the effects of reaction wheel disturbance to spacecraft on orbit, and take corresponding control methods and isolation system, the reaction wheel disturbance precise model is established based on experimental model of disturbance and analyzing the causes of the disturbance. And then the finite element model of spacecraft on orbit is established. The structure dynamics characters simulation is made and the reaction wheel disturbance is as driving source. The effects of reaction wheel disturbance on structure dynamics characters of spacecraft on orbit are analysed in detail. The sim- ulation results can be accurately predict reaction wheel disturbance to the dynamic characteristics of satellites, which is useful for the distribution of satellite equipment installation, and can improve the accuracy and satellite equipment performance. It is useful for engineering design of spacecraft attitude control system and ground text.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2009年第5期2073-2079,共7页
Journal of Astronautics
关键词
反作用轮
扰动
动态特性
有限元模型
频响分析
Reaction wheel
Disturbance
Dynamics characters
Finite element model
Frequency analysis
