Nonlinear rule-based controller for missile terminal guidance

The design of a rule-based guidance law for homing missiles onto targets is presented. The stability of the missile-target dynamics is proven. Unlike conventional approaches that solve the Hamilton-Jacobi partial differential inequality associated with the missile guidance problem, the proposed guidance law is based on heuristic fuzzy rules. Furthermore, the proposed missile guidance control law guarantees that the missile can reach the impact region and destroy the target. An example is used to illustrate the application of the proposed design method.