Attitude Controller Design for Launch Vehicle Based on Parameter Optimization
To accomplish accurate injection, the attitude control system of launch vehicle must precisely control the attitude angles and angular rates.However, the attitude control problem for launch vehicle is challenging because of the elastic properties and the coupling characteristics.To improve the performance of attitude control system, a new attitude controller design method is developed based on parameter optimization.First, PID controller is chosen for the rigid properties, while high-order filter are set for elastic stability.Then, the parameters of attitude controller are optimized using simplex algorithm, and the constraints to define the initial simplex are the ranges of all the variables.To enhance design efficiency, an automatic controller design method is proposed and an integrated software based on it is currently under developement.
Attitude Control Parameter Optimization Launch Vehicle
Yan Zhang Shipeng Li Yong Wang Jingjing Rong
Beijing Institute of Space System Engineering,Beijing,China,100076
国际会议
黄山
英文
1-6
2012-06-18（万方平台首次上网日期，不代表论文的发表时间）