Abstract：In view of the development needs of the new generation of missiles with high speed and large maneuverability, as well as the shortcomings of traditional air control method in response time, maneuverability and stability, the attitude control problem of the missile with defectable nose in supersonic and large maneuvering flight conditions is studied, and an attitude stability control method based on backstepping sliding mode is proposed .First, the dynamic model of the missile with defectable nose was established，and then the aerodynamic characteristics of the missile with defectable nose were analyzed. The variation law of its main aerodynamic parameters with the change of aerodynamic configuration is studied. The attitude control system of the missile with defectable nose was designed by using the backstepping sliding mode control method, and the extended state observer is used to observe and compensate the "total disturbance" of the system including model uncertainty and external disturbance. Finally, the effectiveness of the attitude control algorithm is verified by simulation. The simulation results show that the missile attitude control system based on backstepping sliding mode can track the attitude commands quickly.
吕硕, 张庆振, 郭云鹤, 丰硕. 基于反步滑模的偏转弹头导弹姿态控制[J]. 空天防御, 2022, 5(4): 30-37.
LYU Shuo, ZHANG Qingzhen, GUO Yunhe, FENG Shuo. Attitude Control of Missile with Deflectable Nose Based on Backstepping Sliding Mode Control. Air & Space Defense, 2022, 5(4): 30-37.
