The ability of a trajectory control system to control an interceptor missile with combined control of lateral thrust and aerodynamics was investigated.Adynamical model for interceptor missile with combined control was established.After analyzing differences between various combinations of control for interceptor missiles

impacts of lateral thrust on the motion of interceptor missiles were presented.Amodel of relative movement between the target and interceptor missile was established.Addressing the particularities of combined control for interceptor missiles

a trajectory control algorithm was designed based on the sliding mode control theory.On the basis of which

fire logic was presented for pulse thrusters in order to improve limitation of simple control method.Simulation results show that this method can effectively implement precise guidance for interceptor missiles at the final guidance stage as well as providing preferable robust stability.