Abstract
An energy optimal exo-atmospheric control guidance law against high speed target is proposed in this paper, and it can also satisfy the miss distance and impact angle constraints. As the main advantages, the proposed guidance law solves the problem of nonlinearity caused by the variability of missiles' velocity and the high speed of targets, which are non-negligible in reality but lack of theoretical research. In addition, it shows better performance in energy cost. Firstly, the kinematic model of missile-target and non-linear missile system equations are established. Then, the optimal guidance law is built, and it is solved by linearized methods. Finally, the performance of the guidance law is demonstrated by simulations.
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