Abstract
A third-order state equation with consideration of autopilot dynamics is formulated. A nonlinear coordinate transformation is used to change the state equation into the normal form. Adaptive sliding mode control theory is depicted and its stability analyses are proved. Applying this theory on the normal form equation, an adaptive nonlinear guidance law is proposed. The presented law adopts the sliding mode control approach can effectively solve the guidance problem against target maneuver and effects caused by autopilot dynamics. Simulation results show that under the circumstance of target escaping with high acceleration and big autopilot dynamics, the proposed guidance law still has high precision.
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References
Pastric, H.J., Setlzer, S., Warren, M.E.: Guidance laws for short range homing missile. Journal of Guidance, Control, and Dynamics, 98–108 (1981)
Siouris, G.M.: Comparison between proportional and augmented proportional navigation. Nachritentechnische Zeitschrift, 278–228 (1974)
Yang, C.D., Yeh, E.B., Chen, J.H.: The closed-form solution of generalized proportional navigation. Journal of Guidance and Control AES-10(2), 216–218 (1987)
Yuan, P.J., Chern, J.S.: Solutions of True Proportional Navigation For Maneuvering And Nonmaneuvering Targets. Journal of Guidance, Control, and Dynamics 15(1), 268–271 (1992)
Yang, C.D., Yeh, F.B.: Optimal proportional navigation. Journal of Guidance, Control, and Dynamics 11(4), 375–377 (1988)
Choi, J.Y., Chwa, D., Kim, M.S.: Adaptive Nonlinear Guidance Law Considering Control Loop Dynamics. IEEE Transactions on Aerospace and Electronic Systems 39(4), 1134–1143 (2003)
Zhou, D.: New Guidance Law for Homing Missile. National Defence Industrial Press, Beijing (2002)
She, W.X., Zhou, J., Zhou, F.Q.: An Adaptive Variable Structure Guidance Law Considering Missile’s Dynamics of Autopilot. Journal of Astronautics 24(3), 245–249 (2003)
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© 2011 Springer-Verlag Berlin Heidelberg
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Yang, D., Qiu, L. (2011). Adaptive Nonlinear Guidance Law Considering Autopilot Dynamics. In: Wang, Y., Li, T. (eds) Knowledge Engineering and Management. Advances in Intelligent and Soft Computing, vol 123. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-25661-5_2
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DOI: https://doi.org/10.1007/978-3-642-25661-5_2
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-25660-8
Online ISBN: 978-3-642-25661-5
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