Notice of RetractionA unified approach to optimal proportional navigation

Notice of Retraction

After careful and considered review of the content of this paper by a duly constituted expert committee, this paper has been found to be in violation of IEEE´s Publication Principles.

We hereby retract the content of this paper. Reasonable effort should be made to remove all past references to this paper.

The presenting author of this paper has the option to appeal this decision by contacting TPII@ieee.org.

A unified approach to optimal proportional navigation for missile is purposed based on guidance performance according to the case of attacking the target without any maneuverability. The mathematic model of guidance system is built according to nonlinear relative movement relationship between missile and target, based on zeroing relative distance and zeroing the rate of line of sight. Due to the model, the optimal true proportional navigation law of guidance system is derived by using optimizing the linear quadratic performance in the case of intercepting nonmaneuvering target, at the same time the unified optimal proportional guidance law is obtained according to optimizing the different linear quadratic performance. Finally, the target is intercepted applying the guidance law through the mathematic simulation, the performance of guidance system under two optimal proportional guidance law is compared on a common basis.