Open AccessAdaptive neuro‐fuzzy sliding mode control guidance law with impact angle constraint
Author(s) -
Li Qingchun,
Zhang Wensheng,
Han Gang,
Yang Yehui
Publication year - 2015
Publication title -
iet control theory and applications
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 1.059
H-Index - 108
eISSN - 1751-8652
pISSN - 1751-8644
DOI - 10.1049/iet-cta.2014.1206
Subject(s) - control theory (sociology) , sliding mode control , law , missile , robustness (evolution) , lyapunov stability , adaptive neuro fuzzy inference system , fuzzy logic , adaptive control , constraint (computer aided design) , computer science , fuzzy control system , engineering , nonlinear system , control (management) , artificial intelligence , physics , mechanical engineering , biochemistry , chemistry , quantum mechanics , political science , gene , aerospace engineering
This study presents a guidance law to intercept non‐manoeuvring targets at a desired impact angle. The desired impact angle, defined in terms of a desired line‐of‐sight angle, is achieved by selecting the missile's lateral acceleration to enforce the sliding mode on a sliding surface. Then, the authors use the Lyapunov stability theory to prove the stability of the proposed non‐linear sliding surface. Furthermore, they introduce the adaptive neuro‐fuzzy inference system (ANFIS) to adaptively update the additional control command and reduce the high‐frequency chattering of sliding mode control (SMC). The proposed guidance law, denoted ANFSMC guidance law with impact angle constraint, combines the SMC methodology with ANFIS to enhance the robustness and reduce the chattering of the system. The effectiveness of the ANFSMC guidance law is also verified by the numerical simulations.