Nonlinear Modeling and Hardware-in-the-Loop Implementation of Three-Stage Aircraft Power Generation Systems

LI Tianxing; DU Haoran; LIU Yongzhi; ZHU Peirong; JING Bo; WANG Long

doi:10.7652/xjtuxb202411020

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Nonlinear Modeling and Hardware-in-the-Loop Implementation of Three-Stage Aircraft Power Generation Systems

更新时间：2025-07-25

- Nonlinear Modeling and Hardware-in-the-Loop Implementation of Three-Stage Aircraft Power Generation Systems
- Vol. 58, Issue 11, Pages: 205-216(2024)
- 作者机构：
  
  空军工程大学航空工程学院,西安,710038
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202411020
  CLC： V242.2
- Online First：10 November 2024，
  
  Published：2024
- 稿件说明：
移动端阅览
LI Tianxing, DU Haoran, LIU Yongzhi, et al. Nonlinear Modeling and Hardware-in-the-Loop Implementation of Three-Stage Aircraft Power Generation Systems[J]. 2024, 58(11): 205-216.
DOI：

LI Tianxing, DU Haoran, LIU Yongzhi, et al. Nonlinear Modeling and Hardware-in-the-Loop Implementation of Three-Stage Aircraft Power Generation Systems[J]. 2024, 58(11): 205-216. DOI： 10.7652/xjtuxb202411020.

摘要

针对航空三级式发电系统在故障诊断与状态监控研究中进展缓慢的问题

对系统的非线性关系和信号传递逻辑进行了研究

建立了发电系统的非线性模型

构建了硬件在环测试平台。首先利用电流-磁链神经网络

拟合了电机电流-磁链的非线性关系; 其次提出变参数平均值模型的改进型

准确预测了旋转整流器的输出电压降; 最后分析了系统的信号传递逻辑

完成了对系统的非线性建模。结合航空三级式发电系统的非线性模型和RT-LAB实时仿真机完成了硬件在环测试平台的构建

并利用GJB 181B—2012标准对平台进行了有效性验证和控制能力的验证。验证结果表明

在小型单发飞机所需的发电系统输出功率为45 kV·A的条件下

平台输出三相交流电的稳态电压为113.017 4 V、电压不平衡度为0.253 2 V、电压调制幅度为2.059 6 V

满足GJB 181B—2012标准对供电品质的要求

并且还可以在30～50 kV·A内跟踪任意指定输出功率。该平台利用非线性建模技术、硬件在环技术打破了传统航空发电系统研究中对于实验环境的要求

可以降低研究成本、缩短研究周期

对于航空发电系统的控制器研究以及航空发电系统的更新换代具有加速功能。

Abstract

To address the sluggish progress in fault diagnosis and condition monitoring of three-stage aircraft power generation systems

this paper investigates the system's nonlinear relationships and signal transmission logic by developing a nonlinear model of the power generation system and a hardware-in-the-loop test platform. Initially

a current-flux linkage neural network is utilized to model the nonlinear relationship of motor current-flux linkage. Subsequently

an improved variable parameter average value model is introduced to accurately predict the output voltage drop of the rotary rectifier. Finally

the signal transmission logic of the system is analyzed to finalize the nonlinear modeling process. The hardware-in-the-loop test platform is established by combining the nonlinear model of the three-stage aircraft power generation system with the RT-LAB real-time simulator

and its effectiveness and control capability are verified against GJB 181B—2012. The verification results show that under the requirement of a 45 kV·A output power for small single-engine aircraft

the three-phase AC output maintains a stable voltage of 113.017 4 V

with a voltage unbalance of 0.253 2 V and a voltage modulation amplitude of 2.059 6 V

meeting the power supply quality standard required by GJB 181B—2012. Additionally

the platform can precisely track any specified output power within the 30 to 50 kV·A range. This platform leverages nonlinear modeling technology and hardware-in-the-loop methodology to eliminate the traditional requirements for experimental environments in aircraft power generation system research. It can lower research costs

shorten project durations

and expedite research on aircraft power generation system controllers and upgrades.

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