上海交通大学学报

上海交通大学学报 >

2025 , Vol. 59 >Issue 6: 867 - 876

DOI: https://doi.org/10.16183/j.cnki.jsjtu.2023.425

新型电力系统与综合能源

电动飞机轻量化推进系统可靠性分配方法

  • 李靖豪 ,
  • 李然 ,
  • 华浩 ,
  • 黄文焘 ,
  • 高飞 ,
  • 邰能灵
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  • 上海交通大学 电力传输与功率变换控制教育部重点实验室, 上海 200240
李靖豪(1997—),硕士生,从事电动飞机可靠性研究.
李 然,教授,博士生导师;E-mail:rl272@sjtu.edu.cn.

收稿日期: 2023-08-28

  录用日期: 2023-12-11

  网络出版日期: 2024-01-02

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Reliability Allocation Method for Electric Aircraft Lightweight Propulsion System

  • LI Jinghao ,
  • LI Ran ,
  • HUA Hao ,
  • HUANG Wentao ,
  • GAO Fei ,
  • TAI Nengling
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  • Key Laboratory of Control of Power Transmission and Conversion of the Ministry of Education, Shanghai Jiao Tong University, Shanghai 200240, China

Received date: 2023-08-28

  Accepted date: 2023-12-11

  Online published: 2024-01-02

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摘要

针对电动飞机电推进系统轻量化与高可靠性之间的矛盾,首次提出一种考虑轻量化约束的可靠性分配方法.构建质量与可靠性之间的解析表达,以此为约束考虑电动飞机运行工况的不确定性,提出基于典型飞行剖面的“质量-可靠性”多场景均衡优化方法,实现了可靠性约束下的质量最轻和质量约束下的可靠性最高.以“创新精神”号电动飞机为例,所提方法可在保证系统可靠性的同时,通过对各子系统的可靠性分配,将电动飞机推进系统总质量减轻3.5%;通过设计不同场景验证所提方法的有效性,为电动飞机高功重比发展提供技术支撑.

关键词： 可靠性; 轻量化; 不确定性; 电推进系统; 电动飞机

本文引用格式

李靖豪 , 李然 , 华浩 , 黄文焘 , 高飞 , 邰能灵 . 电动飞机轻量化推进系统可靠性分配方法[J]. 上海交通大学学报, 2025 , 59(6) : 867 -876 . DOI: 10.16183/j.cnki.jsjtu.2023.425

Abstract

In order to solve the contradiction between lightweight and high reliability in the electric aircraft electric propulsion system, a reliability allocation method considering lightweight constraint is proposed for the first time. An analytical expression between weight and reliability is integrated into the electric propulsion system design model as constraints, and a flexible “weight-reliability” optimization method is proposed, considering the uncertainty of the operating conditions of electric aircraft. This method achieves minimum weight under reliability constraints and maximum reliability under weight constraints. Taking the “Spirit of Innovation” electric aircraft as an example, the results show that the proposed method can reduce the total weight of the power system of the electric aircraft by 3.5% while ensuring the reliability of the system. The applicability of the proposed method is verified in different scenarios designed, providing technical support for the development of high power-to-weight ratio in electric aircrafts.

Key words： reliability; lightweight; uncertainty; electric propulsion system; electric aircraft

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