The reliability performance of electrical machines (EMs) and power electronics converters (PECs) is generally verified separately even if the two components are meant to be part of the same electric drive. Depending on the application, however, it might be necessary that the whole drive fulfills a certain reliability target, which is predefined by the application itself. An appropriate design approach should involve joint efforts between machine and converter designers so that the final product is as optimized as possible while still satisfying reliability constraints. In this work, a system-level reliability study for short duty electric drives is proposed and implemented using an aerospace electromechanical actuator as a case study. Concepts of statistical postprocessing for the lifetime prediction of power modules are discussed throughout. In addition, accelerated lifetime tests on EM windings are performed for predicting the motor insulation’s time to failure. For the short duty aerospace drive under investigation, i.e., case study, it is finally verified that the PEC represents the reliability bottleneck.

中文翻译：

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航空航天短负荷电力驱动的系统级可靠性评估

电机 (EM) 和电力电子转换器 (PEC) 的可靠性性能通常是分开验证的，即使这两个组件是同一个电力驱动的一部分。然而，根据应用程序，整个驱动器可能需要满足特定的可靠性目标，该目标由应用程序本身预定义。适当的设计方法应涉及机器和转换器设计人员之间的共同努力，以便在满足可靠性约束的同时尽可能优化最终产品。在这项工作中，使用航空航天机电执行器作为案例研究，提出并实施了短负荷电力驱动的系统级可靠性研究。用于功率模块寿命预测的统计后处理概念贯穿始终。此外，还对 EM 绕组进行了加速寿命测试，以预测电机绝缘失效的时间。对于正在研究的短负荷航空航天驱动器，即案例研究，最终验证了 PEC 代表了可靠性瓶颈。