Propulsion/aerodynamic coupling modeling for distributed-propulsion-wing with induced wing configuration

被引：0
作者：
Zhao, Qingfeng [1 ]
Zhou, Zhou [1 ]
Li, Minghao [1 ]
Xu, De [2 ]
机构：
[1] School of Aeronautics, Northwestern Polytechnical University, Xi’an
[2] School of Computer Science and Technology, Northwestern Polytechnical University, Xi’an
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2024年 / 45卷 / 10期
关键词：
distributed propulsion aircraft; distributed-propulsion-wing; dynamic modeling; induced wing; propulsion/aerodynamic coupling;
D O I：
10.7527/S1000-6893.2023.29252
中图分类号：
学科分类号：
摘要：
This paper proposes a propulsion/aerodynamic coupling model for the distributed-propulsion-wing with induced wing configuration based on the research on distributed-propulsion vertical takeoff and landing vehicles，combined theoretical models and engineering assumptions. This model enables real-time and rapid calculation of the aerodynamic performance of distributed-propulsion-wing with induced wing configuration within the entire flight envelope，including vertical takeoff，transition，and cruise phases. Firstly，a fast calculation method for ducted jet velocity is developed by combining the ducted flow field model and the ducted thrust enhancement coefficient. Then，based on the momentum theory，the propulsion-aerodynamic coupling model is derived for both powered and unpowered conditions. Finally，the characteristics of the propulsion-aerodynamic coupling model are analyzed，and CFD simulations and analyses conducted for typical flight conditions. The results show that the proposed propulsion/aerodynamic coupling model for the distributed-propulsion-wing with induced wing configuration exhibits high accuracy and fast computation speed，meeting the real-time calculation requirements for dynamic system analysis and flight control system design. © 2024 Chinese Society of Astronautics. All rights reserved.
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