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针对高超声速滑翔飞行器的不确定性及强非线性耦合特性,研究了一种自适应变结构姿态控制设计方法。首先建立了高超声速飞行器在滚转通道快速将最大升力面滚转到制导机动方向时姿态控制系统的非线性数学模型,然后将结构干扰力矩、非线性耦合和气动参数摄动等不确定的输入因素视为一类有界干扰,提出了一种自适应变结构控制方法,该法在保证系统闭环稳定的前提下,在线对不确定因素的界进行估计,从而对系统中的不确定因素进行补偿,并选择适当的趋近律,通过符号函数连续化方法来解决由于变结构控制带来的抖振问题,最后进行仿真验证。仿真结果表明该方法具有良好的解耦控制效果,与传统方法相比可有效提高控制系统的控制性能和鲁棒性。
Aiming at the uncertainty and strong nonlinear coupling of hypersonic gliding aircraft, a design method of adaptive variable structure attitude control is studied. Firstly, a nonlinear mathematical model of the attitude control system is established when the hypersonic vehicle roll over the maximum lift plane to the guidance maneuvering direction quickly. Then the uncertain input of structural disturbance torque, nonlinear coupling and aerodynamic parameter perturbation are established. As a class of bounded disturbances, a kind of adaptive variable structure control method is proposed. This method estimates the bounds of uncertain factors on-line under the premise of ensuring closed-loop stability of the system, so as to make uncertainties in the system Compensation and select the appropriate law of convergence, through the continuous method of symbolic function to solve the chattering problem caused by variable structure control, and finally verify the simulation. The simulation results show that this method has a good decoupling control effect, which can effectively improve the control performance and robustness of the control system compared with the traditional method.