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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。
Aiming at the solar sail spacecraft with moving slider as the control actuator, a nonlinear coupling dynamics model of spacecraft-slider two-body system is established based on Lagrangian analytical mechanics. In order to simplify the control law design, the control loop is divided into inner and outer rings, and the control laws are respectively designed. The outer ring takes the attitude of the spacecraft as a controlled variable and the displacement of the slider as a control input. The displacement of the inner slider is a controlled variable, and the driving force of the slider is a control input. Finally, the control law is substituted into the original nonlinear model of the system, and the numerical simulation is carried out with the attitude control mission of the interplanetary solar sail spacecraft as an example. The simulation results show that using the moving slider as the actuator and adopting the designed control law, the attitude adjustment and the long-term attitude keeping of the solar sail spacecraft can be realized.