Author
Abstract
In this paper, the design and simulation of a combined navigation guidance law for two-dimensional ground-to-air missile autopilot is presented. In the proposed guidance law, in the missile guidance phase, the proportional navigation guidance method is used for the active guidance system of the ground-to-air defense missile. Since autopilot must be designed to control the path of the missile, we use the linear two-regulator (LQR) method to design the missile autopilot. The design of the closed-loop system is completed using the guidance and autopilot system, as well as the use of a search engine to estimate the range and speed of the missile approaching the target. The simulation results of the designed system show that using the proposed design for the overall control system, the missile was able to track and hit the target at a constant speed.
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