Adaptive Sliding Mode Guidance Law with Terminal Angle Constraint

DOI

10.2991/lemcs-15.2015.155How to use a DOI?

Keywords

Guidance law; Terminal angle constraint; Sliding mode variable structure; Relative velocity deflection angle; Adaptive reaching law

Abstract

As it is important to attack the targets with terminal angle constraint for a lot of guided weapons, an adaptive sliding mode guidance law is proposed based on the sliding mode variable structure control theory. Considering the problems that the terminal line of sight angle speed changes rapidly and terminal angle constraint, the guidance law chooses relative velocity deflection angle as the sliding mode surface, introduces terminal angle constraint, regards the target maneuvering as limited disturbance, and uses Lyapunov stability theory to analyze the stability of the guidance law. In order to weaken the chattering phenomenon of variable structure control, the guidance law proposes a new method that combining the variable switch term with saturated function. Finally, the designed guidance law is applied to the missile actual model to make a contrastive simulation, the results show that compared with the traditional method, the proposed guidance law can attack the target with less miss distance and terminal angle error, and has strong robustness.

Copyright

© 2015, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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TY  - CONF
AU  - Kuanqiao Zhang
AU  - Suochang Yang
PY  - 2015/07
DA  - 2015/07
TI  - Adaptive Sliding Mode Guidance Law with Terminal Angle Constraint
BT  - Proceedings of the International Conference on Logistics, Engineering, Management and Computer Science
PB  - Atlantis Press
SP  - 792
EP  - 796
SN  - 1951-6851
UR  - https://doi.org/10.2991/lemcs-15.2015.155
DO  - 10.2991/lemcs-15.2015.155
ID  - Zhang2015/07
ER  -