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Sliding Mode and Inertial Delay Control Based Missile Guidance

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2 Author(s)
Phadke, S.B. ; Dept. of Instrum. & Control, Coll. of Eng. Pune, Pune, India ; Talole, S.E.

A novel formulation of sliding mode control (SMC) based proportional navigation (PN) guidance law is presented. Unlike conventional SMC-based guidance laws, the law presented here does not need any knowledge of bounds of target acceleration. The target acceleration is estimated using the so-called inertial delay control (IDC). Closed-loop stability for the guidance loop is established. Simulations are carried out by considering highly-maneuvering targets and constant as well as varying missile velocity and the results are presented to demonstrate the effectiveness of the proposed formulation.

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Aerospace and Electronic Systems, IEEE Transactions on  (Volume:48 ,  Issue: 4 )