摘要
针对新型高速机动目标的拦截问题,提出了一种基于动态终端滑模控制理论的鲁棒制导律设计方案。首先,基于动态终端滑模控制的有限时间收敛特性,研究了一种带补偿因子的终端滑模切换函数;然后,将其通过微分环节构造了非线性动态滑模超平面;最后,设计了动态终端滑模制导律,并对其有限时间收敛特性进行了分析。该制导律不仅具有有限时间收敛特性,而且针对导弹指令加速度的导数进行设计,可将滑模控制中具有的不连续项转移到制导律的一阶导数当中去,有效消除了抖振。仿真结果表明,该制导律可使导弹视线角速率有限时间收敛,且具有更强的鲁棒性和更高的制导精度。
A design scheme of robust guidance law based on dynamic terminal sliding mode control was proposed for the inter-ception of new high speed and maneuvering targets. Firstly, based on the characteristics of finite time convergence of the dynamic terminal sling mode control, a terminal sliding mode switching function with compensating factor was studied,by which a non-linear sliding mode super-surface was proposed through differentiation element then. Finally, the guidance law based on dynamic terminal sliding mode was designed,and its characteristics of finite time convergence were analyzed. The new guidance law not only has the character of finite time convergence,but also is designed based on the derivative of the command acceleration,which could transfer the discrete term that is common in sliding mode control into the first-order derivatives of the guidance law,and remove the chatte-ring problems. Simulation results show that the proposed guidance law could guarantee the missile＇s line-of-sight finite time conver-gence and has better robustness and guidance precision.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2015年第2期160-165,共6页
Journal of Solid Rocket Technology
基金
航空科学基金(20130196004)
关键词
制导律
动态终端滑模
有限时间收敛
guidance law
dynamic terminal sliding mode
finite time convergence
