On the Design of a Fuzzy-PD Based Missile Guidance Law
A novel fuzzy logic-based missile terminal guidance law is proposed based on the specific feature of the fuzzy logic system. The guidance is partitioned into three stages in accordance with the relative range between the interceptor and target. Estimated line-of-sight (LOS) angle, LOS angle rate, LOS angular acceleration and relative range are used to constitute the rule antecedent of the guidance law to shape flight trajectories for effective engagement. Asymmetric membership functions and guidance rules are used in the proposed design to guarantee satisfactory performance