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十字形四倾转旋翼无人机过渡飞行空气动力学的数值模拟

Numerical simulation of the transition flight aerodynamics of cross-shaped quad-tiltrotor UAV.

作者信息

Du Siliang, Zha Yi

机构信息

Faculty of Mechanical and Material Engineering, HuaiYin Institute of Technology, Huaian, 223003, China.

National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing, 210016, China.

出版信息

Sci Rep. 2024 Aug 2;14(1):17878. doi: 10.1038/s41598-024-68927-1.

DOI:10.1038/s41598-024-68927-1
PMID:39095504
原文链接:https://pmc.ncbi.nlm.nih.gov/articles/PMC11297341/
Abstract

In order to enhance the stability of the tilt transition process, a new configuration of Quad-Tiltrotor UAV was presented in this paper. Firstly, numerical simulation was used to calculate and analyze the aerodynamic interaction between the front rotor/fuselage/rear rotor during the transition state mode. The calculation model of the isolated rotor, front-rear rotor, front rotor-fuselage, and front rotor-rear rotor-fuselage combination states are established. Besides, the effects of pitch, roll, and yaw moment on the fuselage at different tilt angles are analyzed. It is concluded that the front rotor is the leading factor in the aerodynamic interference of the whole UAV in the different combination states. The research results can provide a reference for the optimization design of the overall layout, structure, and flight control strategy of the cross-shaped quad-tiltrotor UAV, and can also provide solutions for the logistics application of urban air traffic.

摘要

为提高倾转过渡过程的稳定性，本文提出了一种新型四倾转旋翼无人机构型。首先，采用数值模拟方法对过渡状态模式下前旋翼/机身/后旋翼之间的气动相互作用进行计算分析。建立了孤立旋翼、前后旋翼、前旋翼-机身以及前旋翼-后旋翼-机身组合状态的计算模型。此外，分析了不同倾斜角度下俯仰、滚转和偏航力矩对机身的影响。得出结论：在不同组合状态下，前旋翼是整个无人机气动干扰的主导因素。研究结果可为十字形四倾转旋翼无人机的总体布局、结构及飞行控制策略的优化设计提供参考，也可为城市空中交通的物流应用提供解决方案。

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