Numerical SDRE Approach for Missile Integrated Guidance - Control

Numerical state-dependent Riccati equation based integrated guidance-control formulation is developed for an internally actuated missile. The dynamic system under consideration is of tenth order, making it tedious to algebraically manipulate the equations of motion into the state-dependent coefficient form central to the design methodology. A numerical approach based on previous research is developed to derive the state dependent parameterization of the system. The approach works directly with an input-state numerical simulation model of the system. The state-dependent Riccati equation is solved numerically at the instantaneous values of the state vector. The approach provides a fully numerical methodology for implementing state-dependent Riccati equation controllers for arbitrarily complex dynamic systems. The proposed approach is applied for the design of integrated guidance-controller of an internally actuated missile. Closed-loop simulation results for three-dimensional target interceptions are presented.