Open AccessA Design Method of Missile Acceleration Autopilot Based on Active Disturbance Rejection Control
Author(s) -
Siyuan Chen,
Lihong Yang,
Yunfeng Liu
Publication year - 2020
Publication title -
iop conference series. materials science and engineering
Language(s) - English
Resource type - Journals
eISSN - 1757-899X
pISSN - 1757-8981
DOI - 10.1088/1757-899x/768/4/042011
Subject(s) - autopilot , control theory (sociology) , active disturbance rejection control , missile , robustness (evolution) , acceleration , inner loop , computer science , control engineering , state observer , engineering , controller (irrigation) , aerospace engineering , control (management) , nonlinear system , physics , artificial intelligence , classical mechanics , quantum mechanics , biology , gene , agronomy , biochemistry , chemistry
In order to solve the problem that the performance of the traditional two-loop acceleration autopilot is relatively large affected by the missile aerodynamic, an improved design method based on active disturbance rejection control (ADRC) is proposed. The ADRC acceleration autopilot adopts the extended state observer (ESO) to estimate the disturbance and eliminate the impact of the model uncertainties and external disturbances, which achieve good interference suppression and accurate tracking of command. Then the pole placement method is used for the ADRC autopilot parameter design. Finally, the ADRC autopilot is compared to traditional two-loop autopilot and two-loop autopilot with PI correction under parameters uncertainty and external disturbance, the simulation results demonstrate that the impact of these two factors on the performance of the ADRC autopilot is relatively small. Therefore, the ADRC autopilot is proved to have fast response speed, good transient process, strong anti-interference ability and robustness.