DESIGN OF A FAULT TOLERANT SWITCHED RELUCTANCE MOTOR FOR AN AIRCRAFT FUEL PUMP APPLICATION | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 85, Volume 8, ASAT Conference, 4-6 May 1999, May 1999, Page 1-14 PDF (3.66 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.1999.25173 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
| Amged S. El-wakeer1; Said A. Gawish2; M. A. L. Badr3 | ||||
| 1M. Sc. , Dept. Of Elect. Power & Energy, Military Technical College. | ||||
| 2Associate professor, Dept. Of Elect, Power & Energy, Military Technical College. | ||||
| 3Professor, Dept. Of Elect. Power & Machines, Faculty of engineering, Ain Shams University, Cairo, Egypt. | ||||
| Abstract | ||||
| In military field, harsh environment, and aerospace applications, a fault must not lead to another fault or to the loss of any features of the system. The system must be automatically re-configurable i.e. it must be fault tolerant system. Switched Reluctance Motor (SRM) drives are gaining increasing interest mainly due to the simple technology involved in its manufacture, with low cost and high reliability. Also, SRMs have been researched for safety critical applications, due to their inherent fault tolerance characteristics. This paper focuses on the engineering design and simulation of a 16 KW, 270 V DC, 13000 rpm SRM which can be used as an aircraft fuel pump. This paper explains the principal electromagnetic motor and drive faults and their critical operating conditions. The design approach and the motor design parameters are discussed briefly to explain the design methodology. Finally, a combination of simulation results and design motor dimensions is provided to verify the required motor performance. | ||||
| Keywords | ||||
| Electric Machines; Switched Reluctance Motor and Fault Tolerant Drives | ||||
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