A wide-range-input AC/DC converter for FADEC system application

JIANG Wen-liang; ZHU Yin-yu; JIN Zhao-sheng; HUANG Jin-quan

doi:10.13224/j.cnki.jasp.2014.11.032

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A wide-range-input AC/DC converter for FADEC system application

更新时间：2026-07-07

- A wide-range-input AC/DC converter for FADEC system application
- Vol. 29, Issue 11, Pages: 2774-2779(2014)
- 作者机构：
  
  1. 南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京,210016
  2. 中国航空工业集团公司航空动力控制系统研究所,江苏,无锡,214063
  3. 先进航空发动机协同创新中心,北京,100191
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.11.032
  CLC：
- Published：2014
- 稿件说明：
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蒋文亮, 朱银玉, 金招省, 黄金泉. 一种适用于FADEC系统的宽输入范围AC/DC变换器[J]. 航空动力学报, 2014, 29(11): 2774-2779.

doi: 10.13224/j.cnki.jasp.2014.11.032
蒋文亮, 朱银玉, 金招省, 黄金泉. 一种适用于FADEC系统的宽输入范围AC/DC变换器[J]. 航空动力学报, 2014, 29(11): 2774-2779. DOI： 10.13224/j.cnki.jasp.2014.11.032.

doi: 10.13224/j.cnki.jasp.2014.11.032 DOI：

摘要

针对航空发动机全权限数字电子控制(FADEC)系统专用发电机的输出特性

提出一种电流回馈型恒流变频AC/DC(交流/直流)变换技术

以适应专用发电机的宽输出范围

满足FADEC系统的供电需求.给出了该技术的控制策略、拓扑结构、工作原理、过压故障检测及保护设计方法.试验结果表明:该变换器工作稳定

在-55~125℃全温范围内

满足国家军用标准飞机供电特性(GJB181A)对电源的相关规定.研究成果已成功应用于某型航空发动机数字控制系统中

并通过了台架试车和飞行平台试验.

Abstract

According to the output characteristics of the special generator for full authority digital electronic control (FADEC) system of aero-engine

a constant current variable frequency control AC/DC (alternating current/direct current) transform technique based on current feedback was proposed with purpose of accommodating to the wide-range-output of the special generator

so as to meet the power supply requirements of FADEC system. The control strategy

topological structure and operation principles were embodied along with the overvoltage test and protection design. Experiments results prove the reliability of the converter in full temperature range from -55℃ to 125℃

and compliance with the stipulations of national military standard GJB181A covering aircraft electric power characteristics. Research findings has been successfully applied in certain aero-engine numerical control system and validated in both bench test and flight platform experiment.

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National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics

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