摘要
针对高超声速飞行器具有强烈的非线性、耦合及不确定性等特点,且存在系统噪声和量测噪声,使姿态控制变得困难的问题,提出了采用LQG/LTR控制方法进行全通道姿态控制的思路。首先,在平衡点通过小偏差线性化方法建立多变量耦合的控制模型;然后,运用LQG/LTR控制方法设计姿态控制器。仿真结果表明,在有高斯噪声情况下,所设计的姿态控制系统实现了指令精确跟踪,具有较强的鲁棒性。
Consider that hypersonic vehicle has the characteristic of strong nonlinearity, coupling and uncertainty; in addition exist the system noise and measurement noise, which is making attitude control dif- ficult, the LQG/LTR control method is used to accomplish the whole-channel attitude control. Firstly, the multivariable coupling control model is established by the small deviation linearization method at the equilibrium point. Then, the design of the LQG/LTR control method is used to design. Simulation results show that the designed attitude control system realize the precise tracking of the command in the case of Gauss noise, and the system has strong robustness.
作者
杜立夫
陈宜成
闵勇
李冬
DU Li-fu CHEN Yi-cheng MIN Yong LI Dong(Beijing Aerospace Automatic Control Institute, China Academy of Launch Vehicle Technology, Beijing 100854, China)
出处
《飞行力学》
CSCD
北大核心
2017年第5期66-69,共4页
Flight Dynamics
基金
国家自然科学基金资助(61403355)
