挠性飞行器姿态机动的振动抑制  

Vibration Reduction of Attitude Control for Flexible Spacecraft

作　　者：耿云海[1] 杨涤[1] 荆武兴[1] 

机构地区：[1]哈尔滨工业大学航天学院,哈尔滨150001

出　　处：《振动工程学报》2000年第4期655-659,共5页Journal of Vibration Engineering

基　　金：国家自然科学基金资助项目(编号:19782002)

摘　　要：研究了使用喷嘴作为执行机构的挠性飞行器姿态机动的时间次优控制设计方法。在机动过程中 ,挠性振动对机动时间和机动精度具有很大的影响 ,给出了挠性振动抑制手段 ,使机动完成的同时 ,振动得到有效抑制。由于振动频率和振动阻尼不易精确参数化 ,所以同时考虑挠性振动抑制设计方法对振动频率和振动阻尼的鲁棒性设计问题 。An attitude control system using reaction jet as actuator is studied. The time-optimal design method is investigated for the attitude maneuver of flexible spacecraft, which is modeled as an elastic mass-concentrated system. Approaches of reducing flexible vibration are provided so that the maneuver time and maneuver accuracy are improved efficiently. Since the vibration frequency and damping coeffieient are difficult to be parameterized accurately, the robust design problems are also considered. Simulation results show the feasibility and validity of the methods presented.

关 键 词：挠性 飞行器 鲁棒性 振动抑制 姿态机动 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]