Multi-Level Reliability Analysis and Multi-Objective Optimal Design for All-Electric Aircraft Power System

WEN Qidong; LIANG Deliang; ZHANG Lishi; LIANG Zhe

doi:10.7652/xjtuxb202211013

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Multi-Level Reliability Analysis and Multi-Objective Optimal Design for All-Electric Aircraft Power System

更新时间：2025-07-09

- Multi-Level Reliability Analysis and Multi-Objective Optimal Design for All-Electric Aircraft Power System
- Vol. 56, Issue 11, Pages: 126-137(2022)
- 作者机构：
  
  1. 西安交通大学电力设备电气绝缘国家重点实验室,西安,710049
  2. 西安交通大学电气学院陕西省智能电网重点实验室,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202211013
  CLC： TM351
- Online First：10 November 2022，
  
  Published：2022
- 稿件说明：
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WEN Qidong, LIANG Deliang, ZHANG Lishi, et al. Multi-Level Reliability Analysis and Multi-Objective Optimal Design for All-Electric Aircraft Power System[J]. 2022, 56(11): 126-137.
DOI：

WEN Qidong, LIANG Deliang, ZHANG Lishi, et al. Multi-Level Reliability Analysis and Multi-Objective Optimal Design for All-Electric Aircraft Power System[J]. 2022, 56(11): 126-137. DOI： 10.7652/xjtuxb202211013.

摘要

为了解决全电飞机电力系统对可靠性和安全性要求都较高的问题

本文提出了一种基于多级可靠性分析的全电飞机电力系统多目标优化设计方法。此方法首先将全电飞机中复杂的电力系统设计过程解耦为多级设计过程

每一级设计过程都在考虑成本、可靠性等指标的基础上建立一个非线性优化模型

然后利用层次分析法确定权重系数

将多目标优化问题转换为单目标优化问题

并将非线性模型线性化最终转化为01规划模型

通过求解该模型获得不同权重系数下对应的电力系统最优拓扑结构以及相应功率器件的额定功率。对不同权重系数下的设计结果分析得出:当可靠性指标权重较小时

全电飞机电力系统拓扑结构较为简单

同时电力系统总成本较低; 当可靠性权重较大时

电力系统拓扑结构较为复杂但是成本较高。仿真结果表明

该方法能在成本、可靠性等指标中进行优化设计

体现出该方法在全电飞机电力系统设计初期具有较好的指导意义。

Abstract

This paper proposes a multi-objective optimization design method based on multi-level reliability analysis to ensure higher reliability and safety of all-electric aircraft power system. With this method

the complex all-electric aircraft power system design process is decoupled into two levels

and a nonlinear optimization model is established for each level by considering such indexes as cost and reliability. Then hierarchic analysis is carried out to determine the weight coefficients and simplify the multi-objective optimization problem into a single-objective optimization problem by using such weight coefficients. Meanwhile

a nonlinear model is linearized into a 01 programming model and the optimal power system topology and rated power of each power device under different weight coefficients are obtained by solving this model. According to the analysis results of design under different weight coefficients

the following conclusions are made: Under a low weight coefficient of reliability

the all-electric aircraft power system has a simple topology with low costs; Under a high weight coefficient of reliability

the all-electric aircraft power system has a complex topology with high costs. Simulation results show that this method can optimize the design in cost

reliability and other indexes. This reflects that this method is of good guiding significance in the initial design of all-electric aircraft power system.

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