An Observer-Based Missile Guidance Law
Nonlinear sliding mode guidance laws with finite time convergence are derived for the missile interception in this paper. The proposed guidance laws guarantee that the missile can intercept a maneuverable target with unknown target acceleration. Specially, the control design consists of the estimation of the target acceleration by extended state observer (ESO) and thus it achieves the decrease of undesired chattering effectively. Also, simulation results are presented to illustrate the effectiveness of the control strategies.
Guidance law Sliding mode control ESO Finite-time control
Zheng Zhu Yuanqing Xia Mengyin Fu Shuo Wang
Department of Automatic Control, Beijing Institute of Technology, Beijing 100081, China Lab of Complex Systems and Intelligence Science, Institute of Automation, Chinese Academy of Science
国际会议
2011 China Control and Decision Conference(2011中国控制与决策会议 CCDC)
四川绵阳
英文
1282-1287
2011-05-23（万方平台首次上网日期，不代表论文的发表时间）