Partial Integrated Guidance and Control for Missiles Considering Actuator Fault and Saturation

In this paper, we propose a partial integrated guidance and control (PIGC) scheme for missiles. Firstly, the model including the outer and inner loop models is derived. Then the outer controller where the pitch rate is regarded as the virtual control input is designed to send the line-of-sight angle tracking error and its derivatives to zero (hence the missile will be on a desired collision course). Next, the inner loop controller is proposed to make the actual pitch rate track the pitch rate command from the outer loop, which is robust to the actuator fault. More importantly, by the introduction of the auxiliary dynamic, the outer and inner loop commands are both within the reasonable limits. Finally, a simulation example is presented to illustrate the effectiveness of the proposed method.