Synthesis of zero miss distance missile guidance via solution of an optimal tuning problem

摘要

In this paper, a new approach to guidance of homing missiles is considered. Instead of solving a dynamic optimization problem. which results in complex guidance laws that require the estimation of target maneuver and time-to-go, the guidance law is a priori chosen to be proportional navigation (PN). Then, an optimal tuning problem is solved. That is, the PN constant and the coefficients of the guidance transfer function are optimized to yield zero miss distance (ZMD) against any deterministic or random target maneuver subject to the constraint of limited missile maneuverability. It is shown that when the overall guidance transfer function is positive real, and the PN constant is some given function of the missile-target maneuver ratio, ZMD is obtained. A considerable part of this paper is devoted to a comprehensive treatment of the practical aspects of the theory. Implementation of the neu guidance law is illustrated using real-life missile models, and its performance is compared to PN and optimal guidance (derived from dynamic optimization) using both deterministic and statistical tests. The results obtained are promising.