New guidance laws and autopilot designs for intercepting missiles with TVC and DCS

In this paper, guidance law (GL) and autopilot system, the decision parts of an airframe, are discussed, and specially, the intercepting missiles are the plants considered. For a non-aerodynamically maneuvering airframe, a wingless structure based on thrust vector control (TVC) and divert control system (DCS) is used. To design a robust autopilot system, the sliding mode theory is applied. Besides, two new missile GLs are presented, which utilize the optimal control theory, inverse dynamics technique, and Lyapunov analysis. In addition, stability of the integrated guidance/autopilot (G/A) system and the design methodology of the system parameters are discussed. Finally, various simulations including aerodynamic model are demonstrated to examine the feasibility and performance of the missile's integrated G/A systems.