Electromagnetic-Thermal Integrated Design Optimization for Hypersonic Vehicle Short-Time Duty PM Brushless DC Motor

High reliability is required for the permanent magnet brushless DC motor (PM-BLDCM) in an electrical pump of hypersonic vehicle. The PM-BLDCM is a short-time duty motor with high-power-density. Since thermal equilibrium is not reached for the PM-BLDCM, the temperature distribution is not uniform and...

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Main Authors: Quanwu Li, Manfeng Dou, Bo Tan, Haitao Zhang, Dongdong Zhao
Format: Article
Language:English
Published: Wiley 2016-01-01
Series:International Journal of Aerospace Engineering
Online Access:http://dx.doi.org/10.1155/2016/9725416
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author Quanwu Li
Manfeng Dou
Bo Tan
Haitao Zhang
Dongdong Zhao
author_facet Quanwu Li
Manfeng Dou
Bo Tan
Haitao Zhang
Dongdong Zhao
author_sort Quanwu Li
collection DOAJ
description High reliability is required for the permanent magnet brushless DC motor (PM-BLDCM) in an electrical pump of hypersonic vehicle. The PM-BLDCM is a short-time duty motor with high-power-density. Since thermal equilibrium is not reached for the PM-BLDCM, the temperature distribution is not uniform and there is a risk of local overheating. The winding is a main heat source and its insulation is thermally sensitive, so reducing the winding temperature rise is the key to the improvement of the reliability. In order to reduce the winding temperature rise, an electromagnetic-thermal integrated design optimization method is proposed. The method is based on electromagnetic analysis and thermal transient analysis. The requirements and constraints of electromagnetic and thermal design are considered in this method. The split ratio and the maximum flux density in stator lamination, which are highly relevant to the windings temperature rise, are optimized analytically. The analytical results are verified by finite element analysis (FEA) and experiments. The maximum error between the analytical and the FEA results is 4%. The errors between the analytical and measured windings temperature rise are less than 8%. It can be proved that the method can obtain the optimal design accurately to reduce the winding temperature rise.
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institution Kabale University
issn 1687-5966
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language English
publishDate 2016-01-01
publisher Wiley
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series International Journal of Aerospace Engineering
spelling doaj-art-1cd915bfa16b4ff39f2c39f98a874ade2025-02-03T01:11:13ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742016-01-01201610.1155/2016/97254169725416Electromagnetic-Thermal Integrated Design Optimization for Hypersonic Vehicle Short-Time Duty PM Brushless DC MotorQuanwu Li0Manfeng Dou1Bo Tan2Haitao Zhang3Dongdong Zhao4School of Automation, Northwestern Polytechnical University, Xi’an 710072, ChinaSchool of Automation, Northwestern Polytechnical University, Xi’an 710072, ChinaSchool of Automation, Northwestern Polytechnical University, Xi’an 710072, ChinaSchool of Automation, Northwestern Polytechnical University, Xi’an 710072, ChinaSchool of Automation, Northwestern Polytechnical University, Xi’an 710072, ChinaHigh reliability is required for the permanent magnet brushless DC motor (PM-BLDCM) in an electrical pump of hypersonic vehicle. The PM-BLDCM is a short-time duty motor with high-power-density. Since thermal equilibrium is not reached for the PM-BLDCM, the temperature distribution is not uniform and there is a risk of local overheating. The winding is a main heat source and its insulation is thermally sensitive, so reducing the winding temperature rise is the key to the improvement of the reliability. In order to reduce the winding temperature rise, an electromagnetic-thermal integrated design optimization method is proposed. The method is based on electromagnetic analysis and thermal transient analysis. The requirements and constraints of electromagnetic and thermal design are considered in this method. The split ratio and the maximum flux density in stator lamination, which are highly relevant to the windings temperature rise, are optimized analytically. The analytical results are verified by finite element analysis (FEA) and experiments. The maximum error between the analytical and the FEA results is 4%. The errors between the analytical and measured windings temperature rise are less than 8%. It can be proved that the method can obtain the optimal design accurately to reduce the winding temperature rise.http://dx.doi.org/10.1155/2016/9725416
spellingShingle Quanwu Li
Manfeng Dou
Bo Tan
Haitao Zhang
Dongdong Zhao
Electromagnetic-Thermal Integrated Design Optimization for Hypersonic Vehicle Short-Time Duty PM Brushless DC Motor
International Journal of Aerospace Engineering
title Electromagnetic-Thermal Integrated Design Optimization for Hypersonic Vehicle Short-Time Duty PM Brushless DC Motor
title_full Electromagnetic-Thermal Integrated Design Optimization for Hypersonic Vehicle Short-Time Duty PM Brushless DC Motor
title_fullStr Electromagnetic-Thermal Integrated Design Optimization for Hypersonic Vehicle Short-Time Duty PM Brushless DC Motor
title_full_unstemmed Electromagnetic-Thermal Integrated Design Optimization for Hypersonic Vehicle Short-Time Duty PM Brushless DC Motor
title_short Electromagnetic-Thermal Integrated Design Optimization for Hypersonic Vehicle Short-Time Duty PM Brushless DC Motor
title_sort electromagnetic thermal integrated design optimization for hypersonic vehicle short time duty pm brushless dc motor
url http://dx.doi.org/10.1155/2016/9725416
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AT manfengdou electromagneticthermalintegrateddesignoptimizationforhypersonicvehicleshorttimedutypmbrushlessdcmotor
AT botan electromagneticthermalintegrateddesignoptimizationforhypersonicvehicleshorttimedutypmbrushlessdcmotor
AT haitaozhang electromagneticthermalintegrateddesignoptimizationforhypersonicvehicleshorttimedutypmbrushlessdcmotor
AT dongdongzhao electromagneticthermalintegrateddesignoptimizationforhypersonicvehicleshorttimedutypmbrushlessdcmotor