Homogenous Observer-Based Second-Order Sliding Mode Guidance Law

被引：1
|
作者：
He, Shaoming [1 ]
Lin, Defu [1 ]
Wang, Jiang [1 ]
机构：
[1] Beijing Inst Technol, Sch Aerosp Engn, Beijing 100081, Peoples R China
来源：
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES | 2016年 / 59卷 / 02期
关键词：
Missile Guidance; Line-of-Sight Angular Rate Estimation; Homogenous Theory; Second-Order Sliding Mode; Finite-Time Convergence; INTERCEPTING MANEUVERING TARGETS; FINITE-TIME STABILITY; MISSILE GUIDANCE; ANGLE CONSTRAINT; HOMING MISSILE; AUTOPILOT LAG; DELAY CONTROL;
D O I：
10.2322/tjsass.59.91
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
A new homogenous observer-based finite-time convergent guidance law is proposed to intercept maneuvering targets without line-of-sight (LOS) angular rate information. The presented formulation is obtained via a combination of homogenous theory and second-order sliding mode (SOSM) method. Different from some existing observers, the proposed algorithm can estimate the lumped uncertainty and the LOS angular rate in an integrated manner. By virtue of the principle of SOSM, the undesired chattering is mitigated significantly without any sacrifice in performance. Detailed stability shows that the LOS angular rate can be stabilized in a small region around zero in finite time. Numerical simulations with some comparisons are carried out to demonstrate the superiority of the proposed method.
引用
收藏
页码：91 / 99
页数：9
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