Design feasability of the electrical network for turboelectric aircraft propulsion.
| dc.contributor.advisor | Sampath, Suresh | |
| dc.contributor.advisor | Nalianda, Devaiah | |
| dc.contributor.author | Ibrahim, Kingsley | |
| dc.date.accessioned | 2023-06-29T09:27:39Z | |
| dc.date.available | 2023-06-29T09:27:39Z | |
| dc.date.issued | 2020-01 | |
| dc.description.abstract | The motivation for this research is the need for safer and more environmentally friendly air transport system. Electrical propulsion systems have been identified as a potential method for improving aircraft performance going forward. The implementation of electrical drive trains for future aircraft propulsion comes with many challenges, due to the novelty and scale of the intended deployments. Major technological advancements and research are ongoing at system and component level to meet this ambition. However, the feasibility aspects of these studies have focused more on the engine side than on the electrical aspects, especially with regards to system reliability and stability. These have been considered in the earlier proposed sizing methods, using assumed fault and transient current magnitudes. Such assumption implies that the control and protection systems, may not properly handle abnormal operational scenarios. The aim of this research is to establish a procedure for sizing components of an electric propulsion system considering reliability and stability. The major objective is to properly quantify the operating parameters in non-steady state operations, like transients and fault scenarios, and establish that components are operating within their thermal limits at all operational stages. The contribution of this work is the development of a method that incorporates stability and reliability in the sizing process of electrical propulsion networks. The practicality of the proposed methods has also been validated experimentally, using a test facility set up for this study. The impact of this work is the reduction of the design uncertainties, resulting from assumed fault and transient characteristics of an electrical propulsion system. The results show that the assumptions in earlier researches do not suffice for the investigated architectures. A considerable mass penalty is incurred, with the power electronic devices having to be sized for slightly higher than the maximum transient currents. | en_UK |
| dc.description.coursename | PhD in Aerospace | en_UK |
| dc.identifier.uri | https://dspace.lib.cranfield.ac.uk/handle/1826/19908 | |
| dc.language.iso | en | en_UK |
| dc.rights | © Cranfield University, 2015. All rights reserved. No part of this publication may be reproduced without the written permission of the copyright holder. | |
| dc.subject | Fault | en_UK |
| dc.subject | temperature | en_UK |
| dc.subject | voltage | en_UK |
| dc.subject | motor | en_UK |
| dc.subject | generator | en_UK |
| dc.subject | sizing components | en_UK |
| dc.subject | electrical propulsion system | en_UK |
| dc.title | Design feasability of the electrical network for turboelectric aircraft propulsion. | en_UK |
| dc.type | Thesis | en_UK |