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首页|期刊导航|南京航空航天大学学报(英文版)|基于自适应滑模反馈线性化的航空电动燃油泵预见控制器设计

基于自适应滑模反馈线性化的航空电动燃油泵预见控制器设计

孟祥硕 肖玲斐 马磊明

南京航空航天大学学报(英文版)2023,Vol.40Issue(1):47-59,13.
南京航空航天大学学报(英文版)2023,Vol.40Issue(1):47-59,13.

基于自适应滑模反馈线性化的航空电动燃油泵预见控制器设计

Design of Preview Controller for Aviation Electric Fuel Pump Based on Adaptive Sliding Mode Feedback Linearization

孟祥硕 1肖玲斐 1马磊明2

作者信息

  • 1. 南京航空航天大学能源与动力学院,南京210016,中国
  • 2. 浙江大学流体动力与机电系统国家重点实验室,杭州310027,中国
  • 折叠

摘要

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.

关键词

航空电动燃油泵/预见控制/自适应滑模控制/反馈线性化/建模不确定性

Key words

aviation electric fuel pump/preview control/adaptive sliding mode control/feedback linearization/modeling uncertainty

分类

航空航天

引用本文复制引用

孟祥硕,肖玲斐,马磊明..基于自适应滑模反馈线性化的航空电动燃油泵预见控制器设计[J].南京航空航天大学学报(英文版),2023,40(1):47-59,13.

基金项目

This work was supported by the Na-tional 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). (No.51876089)

南京航空航天大学学报(英文版)

OACSCDCSTPCD

1005-1120

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