低空飞行时改进的自适应鲁棒滑模姿态控制器

Research on Attitude Controller Based on Modified Adaptive Robust Sliding Mode in Low-flying

针对低空飞行时转动惯量的不确定性、外界的干扰以及多通道的强耦合性及非线性的问题,设计具有宽适应性的控制策略,在有限时间内能够快速地、高精度地实现飞行器姿态跟踪控制。基于飞行器姿态非线性模型,对各通道(俯仰、偏航、滚转通道)设计了一种改进的自适应鲁棒滑模控制器,控制器是连续可导的,为了防止控制器输出过大,对自适应控制率算法进行了改进。仿真结果表明:所设计的姿态控制器能够保证飞行器快速、精确地跟踪指令,并且对滑模的抖振现象具有较强的抑制作用;此外,在外加干扰时,姿态角的波动幅度不超过0.1%,可见控制器具有较强的鲁棒性能。

Regarding inertia uncertainties, external disturbances and severe nonlinear coupling factors among the three channels including pitching, yawing and rolling at low-flying, controller design of wide adaptability could quickly and precisely realize the spacecraft attitude tracking control in a limited time. Based on the nonlinear model of the aircraft attitude, a kind of modified controllers was designed based on a robust adaptive sliding mode controller in the finite time convergence among three channels, the controller is continuous and differentiable. The adaptive controller was improved to stop a large controller output. Simulation results show that the designed attitude controller can ensure that the aircraft quickly and accurately tracks the given command, and vibration phenomenon of sliding mode is strongly restrained. Furthermore, the fluctuation range of the attitude angle is less than 0.1% when external disturbances are added to systems, showing the controller has strong robustness.