Nonlinear autopilot and guidance for a highly maneuverable missile

In this paper, both guidance law and autopilot for the bank-to-turn (BTT) terminal homing missiles have been developed and been successfully integrated. Based on differential geometric control theory, the proposed autopilot offers the potential for improving the level of safety and the performance over those autopilot designs based on linearized models. And, according to the concept of the proportional navigation, but under milder constraint, a new guidance law is proposed to intercept a nonmaneuvering target in the aerial engagement scenario. To demonstrate the efficiency of our autopilot and guidance law, the computer simulation of the BTT missile is illustrated in several engagement scenarios and shows the satisfactory results.