挠性空间飞行器仿真装置的动力学与控制研究  

Dynamics and Control Research of a Simulation Device for Flexible Spacecraft

作　　者：曾志春[1] 金永德[1] 赵钧[1] 

机构地区：[1]哈尔滨工业大学空间飞行器设计教研室

出　　处：《哈尔滨工业大学学报》1997年第3期4-7,共4页Journal of Harbin Institute of Technology

基　　金：国家自然科学基金

摘　　要：用单轴气浮台和挠性梁分别模拟卫星本体和太阳帆板。推导了其动力学方程，采用惯性完整性准则进行了模态截断，给出了模态截断的动力学方程。用反作用飞轮作为控制执行机构，设计了控制器，进行了相关的计算机仿真。The behavior of the satellites and their flexible solar arrays are imitated on the single axis gas bearing turntable (SAGBT) and flexible beam separately. The dynamic equations of the SAGBT are derived.The analysis of inertial perfection index is given for non restrained modality with inertial perfection rule and the dynamic equations with modaltrumcation are got. The controller using reaction flywheel on the SABGT is designed and then computer simulation is obtained.

关 键 词：挠性梁 飞行器 仿真装置 动力学 控制 

分 类 号：V414[航空宇航科学与技术—航空宇航推进理论与工程]