重庆理工大学学报2026，Vol.40Issue(15)：28-33,6.DOI:10.3969/j.issn.1674-8425(z).2026.08.004
航空器电推进系统多工况热仿真分析
Multi-scenario thermal simulation analysis of aircraft electric propulsion systems
摘要
Abstract
With the electrification of the aviation industry,efficient thermal management is key to ensuring the performance and safety of electric rotorcraft.This paper focused on the thermal behavior patterns of electric propulsion systems under severe power fluctuations,taking a typical electric propulsion system of an electric rotorcraft as the research object to investigate thermal behaviors.By building detailed three-dimensional geometric models of permanent magnet synchronous motors and lithium battery packs and coupling equivalent thermal circuit models with the Arrhenius formula,quantitative characterization of heat sources was achieved.Based on fluid-solid-thermal multi-physical simulations,the temperature characteristics under hover,cruise,climb,and vertical descent conditions were revealed(temperature rose 45 K,30 K,60 K,and 40 K respectively).Results show the climb phase exhibits the highest temperature rise,with thermal accumulation triggering increased motor winding losses and activating battery BMS power limit protection,forming a positive feedback loop of"temperature rise-efficiency decline".With the optimization strategy transitioning from"passive cooling"to"system-level coordination",this paper may provide some insights into the thermal design and applications of electric propulsion systems.关键词
电动旋翼航空器/电推进系统/热流场/流固热耦合/多工况分析Key words
electric rotorcraft/electric propulsion system/thermal flow field/fluid-structure-thermal coupling/multi-condition analysis分类
航空航天引用本文复制引用
胡志栋,徐海,王懿鑫,马松,耿昊,谷峰..航空器电推进系统多工况热仿真分析[J].重庆理工大学学报,2026,40(15):28-33,6.基金项目
国家自然科学基金项目(51805108) （51805108）
民航安全能力建设基金项目(AADSA2023012) （AADSA2023012）
黑龙江省重点研发计划项目(GZ20220097) （GZ20220097）
