带移动滑块的太阳帆航天器动力学建模与姿态控制  

Dynamics Modeling and Attitude Control of Moving-Mass Based Solar Sail Spacecraft

作　　者：张震亚[1] 韩艳铧[1] 贾杰[2] 

机构地区：[1]南京航空航天大学航天学院,南京210016 [2]南昌航空大学信息工程学院,南昌330063

出　　处：《航天控制》2014年第5期29-35,共7页Aerospace Control

基　　金：国家自然科学基金(61263012)

摘　　要：针对以移动滑块为控制执行机构的太阳帆航天器,基于拉格朗日分析力学建立了航天器—滑块两体系统非线性耦合动力学模型。为简化控制律设计,将控制回路分为内外环,并分别设计控制律。外环以航天器姿态为受控变量,滑块位移为控制输入;内环以滑块位移为受控变量,滑块驱动力为控制输入。最终将控制律代入系统原非线性模型,以行星际太阳帆航天器姿态控制任务为例进行数值仿真。仿真结果表明,以移动滑块为执行机构,采用所设计控制律,可以实现太阳帆航天器快速姿态调整及长期姿态保持。The Solar sail spacecraft which employs moving-mass system is studied about in this paper. The nonlinear coupling dynamics model of Solar sail moving-mass two-body system is established by using Lagrange＇s equations. In order to simplify the design of control law, the control loop is divided into outer- loop and inner-loop and attitude controllers for both outer-loop and inner-loop are designed. The outer-loop chooses attitude angle and velocity as state variables and displacement of moving-mass as control input, while the inner-loop chooses displacement of moving mass as state variable and driving force as control in- put. The simulation results show that the moving-mass based attitude control system by using the designed control law has good performance on solar sail＇ s large angle attitude maneuvering and attitude keeping.

关 键 词：太阳帆 姿态控制 动力学建模 移动滑块 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]