摘要
针对导弹末制导过程中的终端落角约束的问题,基于滑模控制和有限时间控制理论,设计了一种有限时间收敛末制导律。利用终端滑模控制中滑模面上的跟踪误差能够有限时间收敛到0的特点,选取终端滑模面,引入落角约束项,采用有限时间稳定性理论对导引律的有限时间收敛特性进行了证明,并给出了收敛时间的数学表达式。将该末制导律与其他2种带落角约束的导引律进行了对比仿真。结果表明,利用该制导律,制导武器能以更高的命中精度和更小的落角偏差命中目标。
Aiming at the requirements of the terminal impact-angle constraint during the terminal guidance phase of missile,a finite-time convergence terminal guidance law was designed based on the advanced theories of sliding mode control and finite-time control.Considering the specialty that the tracking error on the sliding surface can converge to zero in finite time by using the terminal sliding mode control,the terminal sliding mode surface was selected as the impact angle constraint.The finite-time stabilization-theory was used to analyze the guidance law and prove the finite time convergence feature of the guidance system,and the mathematics expression of the convergence time was given.This proposed guidance-law was compared with another two guidance laws with impact angle constraint.The result shows that the guided missile can hit the target with higher hit-accuracy and less impact-angle error by the proposed guidance.
出处
《弹道学报》
CSCD
北大核心
2015年第4期30-36,共7页
Journal of Ballistics
关键词
末制导律
落角约束
有限时间收敛
终端滑模控制
terminal guidance law
impact angle constraint
finite-time convergence
terminal sliding mode control