Optimal Electric Power System Architectures for Wide Body All Electric Aircraft
Optimal Electric Power System Architectures for Wide Body All Electric Aircraft
复制标题
宽体全电动飞机的最佳电力系统架构
DOI：
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发表时间：
2022
期刊：
影响因子：
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通讯作者：
M. Saghafi
中科院分区：
文献类型：
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作者：
M. Ghassemi;M. Saghafi
为了使传统的宽体飞机成为AEA，应该提供大约25 MW的电力，其中几乎所有这些电力都用于将完全由电化学能量单元（EEU）提供的推力功率。这是一个相当大的功率（对于具有非电推力功率的更多电动飞机（MEA）来说，是最先进技术（SoA）的25倍），需要开发革命性的AEA电力系统（EPS）架构。在本文中，第一次，不同的EPS体系结构的宽体AEA进行了研究。将评估非推进负荷和EEU的位置，估计负荷和母线之间的距离，并针对每种情况，进行正常条件和单一突发事件下的负荷流研究。开关设备安装的各种电路配置，包括H连接和各种环形母线配置，将在功率密度、可靠性、功率损耗和成本方面进行研究和比较，以确定最佳架构。
To make conventional wide body aircraft become AEA, electric power of around 25 MW should be provided where almost all this power is for thrust power that will fully be provided by electrochemical energy units (EEUs). This is a significant amount of power (25x state-of-the-art (SoA) for more electric aircraft (MEA) having non-electric thrust power) that requires the development of revolutionary AEA electric power system (EPS) architectures. In this paper, for the first time, different EPS architectures for wide body AEA are studied. The location for the non-propulsion loads and EEUs will be evaluated, the distances between loads and busbars will be estimated, and for each scenario, load flow studies under normal conditions and single contingencies will be carried out. Various circuit configurations for switchgear installations, including H connection and various ring busbars configurations, will be studied and compared in terms of power density, reliability, power loss, and cost to determine optimal architecture(s).