运载器末助推段非线性姿态控制器设计  

Modeling and Nonlinear Control of Launcher with Fuel Slosh in Final Stage

作　　者：孙平[1] 刘昆[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,湖南长沙410073

出　　处：《上海航天》2011年第4期7-11,共5页Aerospace Shanghai

摘　　要：根据单摆模型近似晃动质量推导晃动运动与姿态运动的动力学方程,基于状态相关黎卡提方程方法,综合动态逆控制方法设计了运载器末助推段非线性姿态控制器,由状态反馈实现姿态跟踪和晃动抑制。因实际中模拟晃动运动的单摆状态无法测量,引入输出多采样率技术,通过在一个采样周期内多次检测被控对象的输出估计状态,实现设计的状态反馈控制律。数值仿真结果表明:控制器能实现高精度姿态角跟踪和晃动抑制。According to a pendulum analogy model of spacecraft with fuel slosh dynamics and nonlinear control for such a model, the dynamic inversion method was adopted to design the state feedback controller of the launcher based on the state dependent Riccati equation in this paper, in which the attitude tracking and fuel slosh suppress were realized by the state feedback. As a fiction state, the pendulum movement could not be observed, a method using a fast output sampling strategy was added to the controller while the state output of the controlling object was inspected many times in one sampling period. The proposed control methodology was practical and easy to implement. The numerical simulation results showed that the attitude angle tracking and fuel slosh suppressing would be realized by the designed controller with high accuracy.

关 键 词：运载器末助推段 推进剂晃动 状态相关黎卡提方程 快速输出采样 非线性姿态控制器 姿态角跟 踪 晃动抑制 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]