According to the requirements of impact angle constraint of the missile, a new terminal guidance law was deduced base on the Lyapunov method to null miss distance and to achieve a desired impact attitude angle, simultaneously. The impact angle constraint was turned to line of sight angle constraint in this method. The proposed guidance law contains two parts that base on line of sight angle rate and the difference between the line of sight angle and the required line of sight angle, respectively. To adjust the two parts portion reasonably the guidance goal with the overload constraint can be realized. The proposed guidance law is simple and convenient to be realized in engineering. Besides that, the best initial condition when the guidance law imported was analyzed considering the missile-s overload availability and the seeker-s performance. The simulation result for model of some missiles shows the effectiveness of this proposed guidance law.
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