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.
Sliding Mode and Inertial Delay Control Based Missile Guidance
IEEE Transactions on Aerospace and Electronic Systems ; 48 , 4 ; 3331-3346
01.10.2012
6578673 byte
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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