带移动滑块太阳帆航天器姿态控制技术研究及仿真  

Attitude Control and ADAMS-MATLAB United Simulation 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,江苏南京210016 [2]南昌航空大学信息工程学院,江西南昌330063

出　　处：《上海航天》2014年第5期1-6,共6页Aerospace Shanghai

基　　金：国家自然科学基金(61263012);中国博士后基金(2012M510593);航空科学基金(20120156001)

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。分外环和内环回路,各自设计了基于增益调度的变增益LQR控制器和带非线性补偿的PD控制器。建立ADAMS实体仿真模型,在MATLAB/Simulink软件中建立姿态控制系统仿真平台,以行星际太阳帆航天器轨道转移过程中姿态控制任务为例进行ADAMS-MATLAB动力学联合仿真实验。结果表明:设计的控制律能有效抑制光压干扰力矩对航天器姿态的影响,可实现太阳帆航天器的大角度快速姿态机动及长期姿态稳定。The nonlinear coupling dynamic model of solar sail-moving mass two-body system was established using Lagrange^s equations for the solar sail spaceflight which employed moving-mass system in this paper. The control loop was divided into outer-loop and inner-loop. The variable gain LQR control based on gain scheduling for outer-loop and PD control with nonlinear compensation for inner-loop were designed. The simulation model was established by ADAMS, and attitude control platform was built in MATLAB. The ADAMS-MATLAB united simulation results of attitude control mission in interplanetary solar sail spacecraft＇s orbit transfer showed that the moving-mass based attitude control system using designed control law had ability to suppress influence of solar light disturbance torque and had a good performance on solar sail＇s large angle attitude maneuver and attitude keeping.

关 键 词：太阳帆 姿态控制 动力学建模 移动滑块 联合仿真 

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]