多电动飞机最优重量动力系统设计与综合

Angel A. Recalde, S. Bozhko, J. Atkin
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引用次数: 1

摘要

更电动飞机的配电架构的综合需要重量优化,以减少能源消耗。飞机配电系统的重量取决于各种因素,如功能和安全要求,以及组件的选择和位置。功能和安全需求可以转化为一组连接性和可靠性约束,从而产生代表电力系统抽象拓扑结构的体系结构。然而,组件选择和定位的目的是产生一个更接近最终实现的解决方案。然后,本文提出了一种基于优化的设计公式,该公式综合了电力系统的架构,考虑了元件的选择和位置,以缩短拓扑与物理实现之间的差距。考虑到生成和求解这种公式的复杂性,执行线性变换以使使用强大的商业求解器并达到最小重量的配电系统。因此,该设计作为一个混合整数线性规划问题提出,并通过一个案例研究来举例说明最优配电体系结构的综合。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Optimal Weight Power System Design and Synthesis for More Electric Aircraft
The synthesis of a power distribution architecture for More Electric Aircraft requires weight optimization in order to reduce energy consumption. The weight of an aircraft power distribution system depends on various factors such as the functional and safety requirements, as well as component selection and location. Functional and safety requirements can be translated into a set of connectivity and reliability constraints to produce an architecture that represents an abstract topology of the power system. However, component selection and location aims to produce a solution that is closer to a final implementation. Then, this paper presents an optimization based design formulation that synthesizes a power system architecture considering component selection and location in order to shorten the gap between the topology and the physical implementation. Given the complexity in producing and solving such formulation, linear transformations are performed to enable the use powerful commercial solvers and reach a minimum weight electrical distribution system. Therefore, the design is presented as a Mixed Integer Linear Programming problem and a case study is used to exemplify the synthesis of a power distribution architecture that is optimal.
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