Fuzzy logic autopilot synthesis for a nonlinearly behaved thruster-controlled missile

A methodology to design a fuzzy logic based autopilot control system that works with vehicle nonlinearities (not merely accommodating them) is defined. The application is a forward propulsive controlled, nonlinearly behaved missile. The three distinct types of nonlinearities studied are nonlinear aerodynamics, impulsive thruster control, and aerodynamic and propulsive jet interaction. To permit sufficient fidelity of simulation models, an empirical approach to defining the jet interaction characteristics is developed and applied to the study missile configuration. The non-minimum phase trait of jet interaction coupled with the transient effects of impulsive control pose the greatest challenge to the autopilot design. The key innovation for controlling the coupled and destabilizing nonlinear missile behavior is to incorporate dynamic compensation into the inherently static fuzzy logic control structure. The autopilot structure is defined and an efficient path for finding a controller solution is identified. Acceleration step responses which respond more rapidly than the linearized airframe approximations with minimal airframe oscillation validate the achievement of the research goal.