A nonlinear guidance problem of an acceleration-constrained missile isdealt with. The feedback linearization method is applied to derive a new3D all-aspect guidance law, which enables the missile to intercept amaneuvering target under any initial heading conditions. The newguidance law takes into account time-varying velocities and ischaracterized by an exponential convergence to a collision course.Simulation analysis shows the performance of the proposed law, whencompared with APN, and indicates of a larger capture zone.
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