运载火箭姿控对迭代制导适应性分析的仿真方法研究  

The Simulation Method Research on Iterative Guidance Adaptability of Attitude Control

作　　者：刘玉玺 张卫东[2] 丁秀峰 刘汉兵 张开宝 

机构地区：[1]上海宇航系统工程研究所,上海201109 [2]上海航天技术研究院,上海201109

出　　处：《航天控制》2014年第5期24-28,共5页Aerospace Control

摘　　要：首先给出了迭代制导方法,然后建立了姿态动力学全量数学模型,在考虑弹性振动和液体晃动的情况下,进行了制导与姿控系统的六自由度联合仿真。仿真结果表明,在迭代制导实时优化输出程序角的情况下,姿控系统具有良好的跟踪性能;在制导与姿控子系统相互作用的情况下,能够确保制导程序角的收敛和姿态的稳定。The model of iterative guidance and attitude dynamics is given in the paper. By considering the elastic vibration and liquid sloshing, six-degree-of-freedom simulation based on iterative guidance and atti- tude control is implemented. The simulation results show that the attitude control system can track program attitude angles which are optimized by iterative guidance. The simulation system can guarantee the program attitude angles convergence and attitude angles stabilization when the guidance subsystem and attitude con- trol subsystem interact each other.

关 键 词：迭代制导 姿控 数学模型 六自由度仿真 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]