中文摘要：

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.

英文摘要：

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.