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An optimal approach to the preliminary design of small hybrid-electric aircraft

机译：小型混合动力飞机初步设计的最佳方法

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Hybrid-electric propulsion is an interesting alternative for the light aviation market, carrying the advantages of electric propulsion in terms of lower noise and pollutive emissions in terminal maneuvers, while not renouncing to the flight performance - especially range - typical to conventional propulsion, based on hydrocarbon fuel. Some difficulty in the spreading of this new technology in light aviation may be ascribed to the lack of consolidated techniques to preliminary design hybrid-electric aircraft, complicating the negotiation of specifications and making design choices difficult. This is also the effect of a notable increase in the number of design variables needed to describe the hybrid-electric power train, which include characteristics of both its thermal and electric parts, with respect to conventionally powered aircraft. The present paper presents a methodology to efficiently cope with this design problem. The procedure is based on an optimal approach where take-off weight is minimized, and constraints are included to assure meeting the mission performance requirements while not exceeding any technological limit. The paper recalls at first some simple mathematical models, allowing to translate flight performance requirements into constraints on the power-train. Then the proposed optimal design approach is thoroughly presented at a theoretical level. Finally, an example design of a hybrid-electric motor-glider is shown, where the optimal design tool is used both to find a baseline solution and to investigate the sensitivity of that design point with respect to constraints due to performance requirements and technological specifications. (C) 2018 Elsevier Masson SAS. All rights reserved.
机译：混合动力电动推进技术是轻型航空​​市场的一个有趣替代方案，它具有电动推进技术的优势，因为它具有降低终端操纵中的噪声和污染排放的优点，同时又不放弃传统推进力所具有的飞行性能-特别是航程-碳氢燃料。这项新技术在轻航空中的推广存在一定的困难，可能是由于缺乏对混合动力飞机进行初步设计的统一技术，使规格的谈判变得复杂，使设计选择变得困难。这也是显着增加描述混合动力总成所需的设计变量数量的效果，相对于常规动力飞机，该混合动力总成包括其热部件和电气部件的特性。本文提出了一种有效解决此设计问题的方法。该程序基于一种最佳方法，在这种方法中，起飞重量被最小化，并且包括约束条件以确保在不超出任何技术限制的情况下满足任务绩效要求。本文首先回顾了一些简单的数学模型，可以将飞行性能要求转化为对动力总成的约束。然后在理论层面上全面介绍了所提出的最佳设计方法。最后，给出了混合动力电动滑翔机的示例设计，其中使用了最佳设计工具来查找基准解决方案，并研究该设计点相对于由于性能要求和技术规格而受到限制的敏感性。 （C）2018 Elsevier Masson SAS。版权所有。

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