Integrated Guidance and Control of Homing Missile with Impact Angular Constraint

For the case of homing missile against ground fixed target, a new scheme of integrated guidance and autopilot design is proposed with impact angular constraint. An integrated guidance and control model in the pitch plane is formulated, by combining the relative relationship between homing missile and target and the dynamic of autopilot, where the information is obtained directly from the instrument of the missile. By adopting the sliding mode control, an adaptive nonlinear control law of the system is designed so that the missile can hit the target accurately with a desired impact angle. The stability of the closed-loop system is also proven by utilizing the Lyapunov stability theory. Finally an illustrative example is given to confirm the usefulness of the proposed design scheme.