Autopilot Design for Agile Missile Using LTV Control and Nonlinear Dynamic Inversion

This paper is concerned with autopilot design for an agilemissile with aerodynamic fin, thrust vectoring control, andside-jet thruster. Two-time scale dynamic inversion is used as anonlinear flight control law. To deal with the weak robustness ofdynamic inversion, Ackermann-like formula which is a time-varyingversion of Ackermann formula for LTI system is applied to controlthe aerodynamic fin to stabilize LTV tracking error dynamics. In addition,control allocation algorithms for the effective distribution of total controldemand to the individual actuators are suggested, which arecapable of extracting the maximum performance by combining eachcontrol effector. Finally, the main results are validated throughthe nonlinear simulations with aerodynamic data.