Abstract
The most widely-used guidance law for short range homing missiles is Proportional Navigation (Pro. Nav.). In Pro. Nav. the acceleration command is proportional to the line of sight angular velocity (L.O.S rate). Indeed, if a missile and a target move on collision course with constant speeds the L.O.S rate is zero.
The speed of a highly maneuverable modern missile varies cnsiderably during flight. The performance using Pro. Nav. is far from being satisfactory.
In this work we analyze the collision course for a variable speed missile and define a guidance law that turns the heading of the missile towards a collision course. We develop guidance laws based on optimal control and differential games, and note that the optimal laws coincide with the ‘Guidance to Collision’ law at the moment of impact.
We demonstrate the improvement in the missile performance using the new guidance law, relative to Pro. Nav. .
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© 1991 Springer-Verlag
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Gazit, R., Gutman, S. (1991). Development of guidance laws for accelerating missile. In: Skowronski, J.M., Flashner, H., Guttalu, R.S. (eds) Mechanics and Control. Lecture Notes in Control and Information Sciences, vol 151. Springer, Berlin, Heidelberg. https://doi.org/10.1007/BFb0006723
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DOI: https://doi.org/10.1007/BFb0006723
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