Aircraft guidance method based on second-order sliding mode

The invention discloses an aircraft guidance method based on a second-order sliding mode, and the method comprises the steps: setting an aircraft kinetic equation, and building an aircraft guidance system; establishing a sliding mode surface, and adopting sliding mode control to obtain a guidance law of the guidance system; controlling the aircraft by adopting the obtained guidance law; according to the method, buffeting is effectively eliminated by setting a unique sliding mode surface and a sliding mode algorithm, accurate striking on a target under different angle constraints is realized, estimation and feed-forward compensation can be performed on the target under the condition of no prior information by setting a non-homogeneous disturbance observer, target maneuvering can be accurately obtained, and target striking accuracy is improved. 本发明公开了一种基于二阶滑模的飞行器制导方法，包括：设置飞行器动力学方程，建立飞行器制导系统；建立滑模面，采用滑模控制获得制导系统制导律；采用获得的制导律进行飞行器控制；其中，通过设置独特的滑模面以及滑模算法，有效消除抖振，实现不同角度约束下对目标的精确打击，通过设置一种非齐次干扰观测器，能够在没有先验信息的情况下，对目标进行估计和前馈