Abstract
The application of the optimal control theory in the homing missile guidance has resulted in powerful yet relatively easy to implement guidance law that outperform the classical guidance laws such as proportional navigation (PN). The worthwhile improvements that may be gained by the use of the modern guidance laws compared with that achievable using PN is critically evaluated in the chapter. A two dimensional linear design model of the interception scenario that deals with the guidance and control part in the terminal homing phase of the flight is developed. Comparison of the different guidance laws in deterministic environment against maximum missile acceleration capability and autopilot time constant variation and uncertainty has shown that the optimal guidance law (OGL) is more superior to the classical PN and is worth the effort to implement in real systems. The comparative study is carried out based upon a mathematical model of the guidance system that includes the critical and often neglected missile characteristics of autopilot dynamics and limited missile maneuvering capability.
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