Abstract
The most used guidance law for short-range homing missiles is proportional navigation (PN). In PN, the acceleration command is proportional to the line-of-sight (LOS) angular velocity. Indeed, if a missile and a target move on a collision course with constant speeds, the LOS rate is zero. The speed of a highly maneuverable modem missile varies considerably during flight. The performance of PN is far from being satisfactory in that case.
In this article we analyze the collision course for a variable-speed missile and define a guidance law that steers the heading of the missile to the collision course. We develop guidance laws based on optimal control and differential game formulations, and note that both optimal laws coincide with the Guidance to Collision law at impact. The performance improvement of the missile using the new guidance law as compared to PN is demonstrated.
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Gazit, R., Gutman, S. Development of guidance laws for a variable-speed missile. Dynamics and Control 1, 177–198 (1991). https://doi.org/10.1007/BF02169549
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DOI: https://doi.org/10.1007/BF02169549