Abstract
This paper is concerned with autopilot design for an agile missile with aerodynamic fins, thrust vectoring control, and side-jet thrusters. Two-time scale dynamic inversion is used as a nonlinear flight control law. To deal with the inherently weak robustness property of dynamic inversion, Ackermann-like formula which is a time-varying version of Ackermann formula for LTI systems is applied to control the aerodynamic fins to stabilize LTV tracking error dynamics. In addition, control allocation algorithms for the effective distribution of the required total control efforts to the individual actuators are suggested, which are capable of extracting the maximum performance by combining each control effector. Finally, the main results are validated through nonlinear simulations with aerodynamic data.
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