Missile autopilots for aerodynamic angle control and acceleration control are designed for fin-controlled missiles during the boost phase. In the boost phase, the speed change and the parameter variation of the missile are fast and large. To deal with the time-varying characteristics of the missile, the time-varying parameters are considered in nonlinear dynamics, and the parametric uncertainties are modeled. A state-feedback controller is designed for aerodynamic angle control based on a robust-backstepping scheme. Also, an output feedback controller is designed for acceleration control, where the acceleration dynamics are derived using input–output linearization. Numerical simulations are performed to demonstrate the performance of the proposed controllers.
Robust-Backstepping Missile Autopilot Design Considering Time-Varying Parameters and Uncertainty
IEEE Transactions on Aerospace and Electronic Systems ; 56 , 6 ; 4269-4287
01.12.2020
2403910 byte
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch