CAJ | 학술논문

根据有限时间收敛控制理论，应用滑模控制方法设计了一种考虑导弹自动驾驶仪二阶动态特性的有限时间收敛导引律，其最终表达式中不含有视线角速率的高阶导数，更易于实际应用。该导引律有效地克服了导弹控制系统的动态延迟对制导精度的影响。将该导引律与未考虑导弹自动驾驶仪动态的自适应滑模导引律比较，对目标非机动和正弦机动进行仿真。仿真结果表明，在目标机动加速度快速变化，而且导弹自动驾驶仪存在较大滞后情况下，考虑导弹自动驾驶仪二阶动态特性的有限时间收敛导引律仍能够导引导弹精确地拦截机动目标。
근거유한시간수렴공제이론，응용활모공제방법설계료일충고필도탄자동가사의이계동태특성적유한시간수렴도인률，기최종표체식중불함유시선각속솔적고계도수，경역우실제응용。해도인률유효지극복료도탄공제계통적동태연지대제도정도적영향。장해도인률여미고필도탄자동가사의동태적자괄응활모도인률비교，대목표비궤동화정현궤동진행방진。방진결과표명，재목표궤동가속도쾌속변화，이차도탄자동가사의존재교대체후정황하，고필도탄자동가사의이계동태특성적유한시간수렴도인률잉능구도인도탄정학지란절궤동목표。
@@@@Accounting for the missile autopilot as second-order dynamics, a guidance law with finite time convergence is designed using the sliding mode control method and finite time convergence control theory.The high-order derivatives of the line of sight angle are avoided in the expression of guidance law so that it can be implemented in practical applications .The proposed guidance law is effective in compen-sating the bad influence of the autopilot lag on guidance accuracy .In simulations of intercepting non ma-neuvering targets and targets with sinusoidal acceleration respectively , the guidance law is compared with the adaptive sliding mode guidance law in the presence of missile autopilot lag .Simulation results show that the proposed guidance law is able to guide a missile to accurately intercept a maneuvering target , e-ven if it escapes in a great and fast maneuver and the autopilot has a relatively large lag .