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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。
Aiming at the aerodynamic servo-elasticity control of hypersonic vehicle in longitudinal static instability and low-frequency structure mode, a robust controller with double circuit structure is designed. The inner loop is designed as a variable gain controller based on the linear variable parameter (LPV) theory. The elastic model is expressed as an LPV model with an affine parameter dependent structure. Linear matrix inequalities (LMIs) are used to solve the variable gain controller to ensure that under any loading conditions, Have sufficient structural damping; outer loop design robust controller to achieve accurate tracking of aircraft angle of attack instructions. The simulation results show that this method can take the initiative to dampen the structure modal to achieve the effect of restraining the servo elasticity. At the same time, it realizes the short-period modal stability in the longitudinal direction of the aircraft and the high precision tracking of the control commands.