Observer-based guidance law against maneuvering targets without line-of-sight angular rate information

被引:11
作者
He, Shaoming [1 ]
Lin, Defu [1 ]
机构
[1] Beijing Inst Technol, Sch Aerosp Engn, 5 Zhongguancun South Rd, Beijing 100081, Peoples R China
基金
中国国家自然科学基金;
关键词
Missile guidance; maneuvering targets; line-of-sight angular rate estimation; finite-time convergence; adaptive super-twisting algorithm; SLIDING MODE CONTROL; FINITE-TIME STABILITY; MISSILE GUIDANCE;
D O I
10.1177/0954410015613739
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
This paper presents a robust observer-based finite-time convergent guidance law to intercept maneuvering targets. To avoid the undesired chattering phenomenon existing in classical sliding mode control, the adaptive super-twisting algorithm is first introduced to design a robust guidance law to drive the line-of-sight (LOS) angular rates to a small region around the origin in finite time. The important feature of the proposed adaptation algorithm is in nonoverestimating the values of the guidance law gains, which is achieved by using a detector' scheme in the updating law. Moreover, with the proposed adaptive law, the presented guidance law requires no information on target maneuvers. Since the LOS angular rate is difficult for a pursuer to measure accurately for some seekers, a novel adaptive super-twisting observer is proposed to estimate it and a composite guidance law is then synthesized. Detailed finite-time stability analysis and comparison results with other guidance laws demonstrate the superiority of the proposed formulation.
引用
收藏
页码:1827 / 1839
页数:13
相关论文
共 39 条
[1]  
[Anonymous], TACTICAL STRATEGIC M
[2]   Differential Games Missile Guidance With Bearings-Only Measurements [J].
Battistini, Simone ;
Shima, Tal .
IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS, 2014, 50 (04) :2906-2915
[3]   Finite-time stability of continuous autonomous systems [J].
Bhat, SP ;
Bernstein, DS .
SIAM JOURNAL ON CONTROL AND OPTIMIZATION, 2000, 38 (03) :751-766
[4]   Proportional Guidance and CDM Control Synthesis for a Short-Range Homing Surface-to-Air Missile [J].
Budiyono, Agus ;
Rachman, Harapan .
JOURNAL OF AEROSPACE ENGINEERING, 2012, 25 (02) :168-177
[5]   Nonsingular Sliding Mode Guidance for Impact Time Control [J].
Cho, Dongsoo ;
Kim, H. Jin ;
Tahk, Min-Jea .
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 2016, 39 (01) :61-68
[6]   On adaptive sliding mode control without switching gain overestimation [J].
Cong, B. L. ;
Chen, Z. ;
Liu, X. D. .
INTERNATIONAL JOURNAL OF ROBUST AND NONLINEAR CONTROL, 2014, 24 (03) :515-531
[7]   Design of three-dimensional nonlinear guidance law with bounded acceleration command [J].
Du, Runle ;
Meng, Kezi ;
Zhou, Di ;
Liu, Jiaqi .
AEROSPACE SCIENCE AND TECHNOLOGY, 2015, 46 :168-175
[8]  
Garnell P., 1980, GUIDED WEAPON CONTRO
[9]   Application of Finite-Time Integral Sliding Mode to Guidance Law Design [J].
Golestani, Mehdi ;
Mohammadzaman, Iman ;
Yazdanpanah, Mohammad Javad ;
Vali, Ahmad Reza .
JOURNAL OF DYNAMIC SYSTEMS MEASUREMENT AND CONTROL-TRANSACTIONS OF THE ASME, 2015, 137 (11)
[10]   Finite-time convergent guidance law based on integral backstepping control [J].
Golestani, Mehdi ;
Mohammadzaman, Iman ;
Vali, Ahmad Reza .
AEROSPACE SCIENCE AND TECHNOLOGY, 2014, 39 :370-376