分布式动力翼-诱导翼面推进-气动耦合模型
收稿日期: 2023-07-03
修回日期: 2023-10-07
录用日期: 2023-10-27
网络出版日期: 2023-11-01
基金资助
装备预研项目(50911040803);国防基金(2021-JCJQ-JJ-0805);陕西省自然科学基金(2022JQ-060);基础加强计划(2022-173ZD-195)
Propulsion/aerodynamic coupling modeling for distributed-propulsion-wing with induced wing configuration
Received date: 2023-07-03
Revised date: 2023-10-07
Accepted date: 2023-10-27
Online published: 2023-11-01
Supported by
Equipment Pre-Research Project(50911040803);National Defence Fund(2021-JCJQ-JJ-0805);Natural Science Foundation of Shaanxi Province(2022JQ-060);Strengthening Basic Disciplines Program(2022-173ZD-195)
针对分布式动力垂直起降飞行器，提出了综合理论模型和工程经验假设的分布式动力翼-诱导翼面布局的推进-气动耦合模型，实现了对垂起-过渡-巡航全飞行包线内分布式动力翼-诱导翼面气动性能的实时快速计算。结合涵道流场模型和涵道推力增强系数发展了涵道喷流速度的快速计算方法，针对有/无动力输入状态完成了基于动量理论的推进-气动耦合模型推导，进行了推进-气动耦合模型特性分析，并开展了典型飞行工况下的CFD仿真校验与分析。结果表明，所建立的分布式动力翼-诱导翼面的推进-气动耦合模型具有较高精度，计算速度很快，能够满足动力学系统分析和飞行控制系统设计时的实时计算需求。
赵清风 , 周洲 , 李明浩 , 徐德 . 分布式动力翼-诱导翼面推进-气动耦合模型[J]. 航空学报, 2024 , 45(10) : 129252 -129252 . DOI: 10.7527/S1000-6893.2023.29252
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.
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