基于分数阶滑模控制的挠性航天器姿态跟踪及主动振动抑制研究  

Study on attitude tracking and active vibration suppression of a flexible spacecraft based on fractional order sliding mode control

作　　者：邓立为[1] 宋申民[1] 陈兴林[1] 

机构地区：[1]哈尔滨工业大学航天学院,黑龙江哈尔滨150001

出　　处：《振动工程学报》2015年第1期9-17,共9页Journal of Vibration Engineering

基　　金：国家自然科学基金资助项目(61174037);国家自然科学基金创新群体基金资助项目(61021002);国家"973"计划资助项目(2012CB821205)

摘　　要：针对挠性航天器姿态跟踪控制问题,提出一种具有模糊自适应理论、分数阶理论、滑模控制理论和主动振动补偿综合特性的复合控制律。首先,在传统挠性航天器姿态控制模型基础上,推导出姿态模型的具有复合扰动的一般非线性系统形式,利用模糊自适应理论对复合扰动进行万能逼近,结合分数阶理论与滑模控制理论设计分数阶滑模控制律,进一步使用Lyapunov理论与分数阶稳定性理论证明了整个系统的稳定性。其次,针对航天器挠性模态模型,利用压电智能材料的控制方法,设计具有应变速率反馈特性的挠性模态补偿器。最后,数值仿真验证了模糊自适应分数阶滑模控制律的有效性与良好的控制性能。A complex controller is proposed for flexible spacecraft attitude tracking control,in which the advantages of fuzzy adaptive scheme,fractional control,sliding mode control,and active vibration compensation are all combined.First,ageneral nonlinear system form with the integrated disturbance is deduced from the traditional flexible spacecraft attitude control model.The integrated disturbance is approximated by the fuzzy adaptive theory and the universal approximation.A fractional order sliding mode controller is designed by the fractional order control theory and the sliding mode control,and the stability of the whole system is proved by Lyapunov theory and fractional stability theory.Second,a flexible mode compensator with strain rate feedback is given for flexible mode of spacecraft based on the control method of piezoelectric intelligent materials.Finally,numerical simulations are carried out to verify the analytical results and the effectiveness of the fuzzy adaptive fractional sliding mode controller.

关 键 词：航天器 姿态控制 分数阶滑模 分数阶微积分 模糊自适应 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计] TB53[理学—物理]