An observer-based missile guidance law
Proceedings of the 2011 Chinese Control and Decision Conference, CCDC 2011, Page: 1282-1287
2011
- 2Citations
- 4Captures
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Conference Paper Description
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. © 2011 IEEE.
Bibliographic Details
Institute of Electrical and Electronics Engineers (IEEE)
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