Transactions of Nanjing University of Aeronautics & Astronautics
Design of Preview Controller for Aviation Electric Fuel Pump Based on Adaptive Sliding Mode Feedback Linearization
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Abstract:
This study takes an aviation electric fuel pump with an external gear pump directly driven by a six-phase permanent magnet synchronous motor as an object. Its fuel flow control system is studied in this paper， and a preview controller design approach based on adaptive sliding mode feedback linearization is proposed. Firstly， the mathematical model of six-phase permanent magnet synchronous motor and external gear pump is established. Secondly， the nonlinear model of the electric fuel pump is processed using the feedback linearization method， which is helpful for the following preview controller design. Then， the linearization errors caused by the model uncertainty are eliminated using an adaptive sliding mode control method， which can separate the uncertainty brought on by modeling error and load disturbance and prevent chattering brought on by high switching gain. At the same time， it does not require accurate uncertainty boundary information， which improves control performance. Finally， the linearization model created by the feedback linearization method is used to construct the preview controller， which will reduce the time the control system takes to respond to a fuel command. The simulation results demonstrate that the proposed control method has a less response time， strong robustness， and excellent chattering suppression ability.
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Project Supported:
This work was supported by the National Natural Science Foundation of China （No.51876089）， the Postgraduate Research & Practice Innovation Program of Nanjing University of Aeronautics and Astronautics （No.xcxjh20210204）， and the Open Foundation of the State Key Laboratory of Fluid Power and Mechatronic Systems （No.GZKF-202005）.
Clc Number:
V233.7
CHINA AERO-SCIENCES
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