Original scientific paper
https://doi.org/10.1080/00051144.2018.1549696
Design of gain schedule fractional PID control for nonlinear thrust vector control missile with uncertainty
Mohamed Fawzy Ahmed
; Faculty of Engineering, Cairo University, Giza, Egypt
Hassen Taher Dorrah
; Faculty of Engineering, Cairo University, Giza, Egypt
Abstract
The purpose of this paper is to control the trajectory of the nonlinear missile model in the pitch channel by using Fractional PID controller (FPID) and Gain Schedule Fractional PID controller (GSFPID). FPID and GSFPID with nonlinear missile model are designed where their parameters are tuned by Simulink design optimization in the Matlab toolbox. This optimization method gives the optimal parameters that achieve the best tracking with step unit reference signal. The GSFPID controller compensates the restrictions that represent physical limits of actuators in the pitch channel. The GSFPID with nonlinear missile model is designed in two phases. The first phase is the boost phase where the thrust force is maximized and the second phase is sustain phase where
the thrust force is minimized. The equations of motion for nonlinear missile model with FPID and GSFPID are modelled mathematically in the Matlab-Simulink environment. The results of FPID and GSFPID controllers with the nonlinear missile model are presented and compared. The wind effect and the dynamic uncertainties effects are researched and the results are compared. The closed-loop nonlinear system is linearized by the Simulink linear analysis tool at critical operating point t = 5.8 sec and the stability is studied.
Keywords
Six degree of freedom missile (6-DOF); fractional PID controller (FPID); gain schedule fractional PID controller (GSFPID); Simulink design optimization; wind effect; dynamic uncertainties; stability analysis
Hrčak ID:
225214
URI
Publication date:
12.12.2018.
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