Abstract
A trajectory shaping guidance law is proposed for a missile to intercept a stationary target considering terminal flight path angle and acceleration constraints. The proposed approach is to design a desired crossrange profile using a polynomial of downrange-to-go. The resulting trajectory shaping guidance law provides several benefits such as flexibility and ease of implementation. The proposed guidance law does not depend on linearized engagement kinematics, constant speed assumption, and time-to-go estimate. Numerical simulation is performed to demonstrate the effectiveness of the proposed guidance law.
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