System design of hybrid distributed electric propulsion aircraft

被引：0

作者：

Li, Jiacheng ^{[1
]}

Sheng, Hanlin ^{[1
]}

Chen, Xin ^{[1
]}

Shi, Haolan ^{[1
]}

Zhang, Tianhong ^{[1
]}

机构：

[1] College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing,210016, China

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2024年 / 39卷 / 09期

关键词：

Aircraft models - Aircraft power systems - Electric machine control - Electric propulsion - Hybrid electric aircraft - Propellers;

D O I：

10.13224/j.cnki.jasp.20220693

中图分类号：

学科分类号：

摘要：

The Y-7 aircraft was used as the reference model to carry out the overall design and performance analysis of the distributed electric propulsion aircraft. The power system of the distributed electric propulsion aircraft was designed， including design of propeller parameters， correction of wing parameters，calculation of motor power and type selection and aerodynamic design of propeller，and finally the design of hybrid power system was completed. The mass increase and decrease of each part of the distributed electric propulsion aircraft were completely calculated and its flight performance was analyzed. Compared with the reference model，the range and duration increased by 540 km and 1.2 h respectively，up by 20%. Finally， the three-dimensional modeling was established and aerodynamic characteristics of the distributed electric propulsion aircraft were analyzed. The result provides a theoretical basis for the modeling，simulation and control of distributed electric propulsion aircraft and its engineering applications. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

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