Outline

  • I. Introduction
  • II. Analysis of a Slotted Pmbldc Motor
  • III. Analysis of a Slotless Pmbldc Motor
  • IV. Comparison of Slotted and Slotless Pmbldc Machine Configurations
  • V. Conclusion

رئوس مطالب

  • چکیده
  • کلیدواژه ها
  • I. مقدمه
  • II. تجزیه و تحلیل موتور PMBLDC شیاردار
  • A. مدلسازی تحلیلی
  • B. نتایج تحلیلی
  • C. بهینه سازی FE و نتایج
  • III. تجزیه و تحلیل یک موتور PMBLDC فاقد شیار
  • A. مدلسازی تحلیلی
  • B. نتایج و بحث تحلیلی
  • C. نتایج و بحث FE
  • IV. مقایسه پیکربندی دستگاه PMBLDC شیاردار و فاقد شیار
  • V. نتیجه گیری
  • VI. قدردانی

Abstract

This paper presents the optimal design of a surface mounted permanent-magnet (PM) Brushless direct-current (BLDC) motor meant for spacecraft applications. The spacecraft applications requires the choice of a motor with high torque density, minimum cogging torque, better positional stability and high torque to inertia ratio. Performance of two types of machine configurations viz Slotted PMBLDC and Slotless PMBLDC with Halbach array are compared with the help of analytical and finite element (FE) methods. It is found that unlike a Slotted PMBLDC motor, the Slotless type with Halbach array develops zero cogging torque without reduction in the developed torque. Moreover, the machine being coreless provides high torque to inertia ratio and zero magnetic stiction.

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Conclusions

The optimal design of a surface mounted PMBLDC meant for spacecraft applications is carried out. Two types of machine configurations such as slotted PMBLDC and slotless PMBLDC with Halbach array were compared with analytical and FE results. It is found that unlike that of slotted PMBLDC motor a slotless PMBLDC motor with Halbach array develops zero cogging torque without much reduction in the developed torque. Moreover the use of Halbach array helps in achieving high Torque to inertia ratio and reduces core losses. The machine being coreless has zero magnetic stiction. The optimal design of Slotless Halbach Array PMBLDC machine is found to develop a peak torque of 0.84 Nm at 1 A excitation and meet the required design requirements for spacecraft applications.

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