摘要
针对高超声速飞行器纵向静不稳定和低频结构模态下的气动伺服弹性控制问题,设计了一种双回路结构的鲁棒控制器。内环基于线性变参数(LPV)理论设计变增益控制器,将弹性模型表示成具有仿射参数依赖结构的LPV模型,采用线性矩阵不等式(LMI)求解变增益控制器以保证在任何载荷条件飞行器都具有足够的结构阻尼;外环设计鲁棒控制器实现飞行器对攻角指令的准确跟踪。仿真结果表明,该方法能够主动对结构模态进行阻尼从而达到抑制伺服弹性的效果,同时实现了飞行器纵向短周期模态稳定和对控制指令的高精度跟踪。
For the control problem of hypersonic vehicle with longitudinal static instability and Low frequency structure mode, a robust controller with a dual-loop structure is designed. Variable gain controller for inner loop is designed based on LPV theory, expressing the elastic model as LPV model with affine parameter-dependent structures, then Linear matrix inequality （LMI） is used to solve variable gain controller to ensure that the aircraft have sufficient structural damping under any loading conditions; robust controller for the outer loop is designed to realize the accurate tracking to the angle of attack of the aircraft. Simulation results show that the proposed method can achieve the effect of the suppression of the servo elasticity with the active damping of the structure mode, and realize the stability of the longitudinal short period mode of the aircraft and the high precision tracking to the control command.
出处
《战术导弹技术》
北大核心
2016年第2期77-83,共7页
Tactical Missile Technology
关键词
伺服弹性
静不稳定
线性变参数
高超声速飞行器
servo elasticity
static instability
linear parameter-varying
hypersonic vehicle
