面向大包线导弹的分回路LPV姿态控制器设计

Loop Separate LPV Attitude Controller Design for Large Envelope Missile

针对导弹飞行过程中,马赫数、攻角大范围变化带来的系统特性快变等问题,本文给出一种分回路控制、具有自增益调节功能的鲁棒线性变参数(LPV)姿态控制方法。本文首先基于导弹的飞行包络给出了其LPV系统的建模方法,然后考虑到LPV控制器数据量将随着LPV模型维数和顶点个数呈指数形式增长,提出了基于分回路设计的控制方法,以降低控制器阶数和个数,从而使控制器更具工程意义。最后基于某导弹非线性六自由度模型,对导弹进行复合控制仿真,结果表明所设计的控制器具有良好的自适应能力和鲁棒性。

Considering the time-varying characteristics due to the wide range of Mach number andangle of attack during the process of missile flight, this paper introduces a robust Linear Parameter Var-ying （LPV） attitude controller design method, which is capable of loop separate controlling and self-scheduling. The modeling method of LPV vertex models is given firstly, and then, since the data volumeof LPV controller grows exponentially along with the increase of dimensions and number of vertices of LPVmodels, the control method based on loop separate design is introduced in order to improve the applicabil-ity of the controller by reducing its order and number. Finally, the 6-DOF nonlinear simulation of flightmission at high angle of attack conveys that the proposed attitude controller has shown good adaptive abili-ty and robustness within the operating envelope.