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学者姓名：雷瑶
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Abstract ：
This paper presents a novel orthogonal octo-rotor Unmanned Aerial Vehicle (UAV) and addresses the aerodynamics of the UAV with varied rotor spacing by both numerical simulations and experiments. Compared with the traditional planar multirotor UAV, this novel orthogonal octo-rotor UAV features a compact structure with four horizontal main rotors for stability and thrust and four vertical auxiliary rotors for lateral movement. Additionally, the attitude and translation dynamics are decoupled with easy manipulations. To obtain a better hover performance, the flow field and hover performance of the UAV were analyzed with rotor spacing ratios i = D/L ranging from 0.55 to 0.9 (i = 0.55, 0.59, 0.63, 0.67, 0.71, 0.77, 0.83, 0.90) and a rotor speed ranging from 1500 to 2300 RPM. The results showed that a rotor spacing ratio of i = 0.55 achieves a better hover efficiency, increasing hover efficiency by 11.27% at 2000 RPM, where the maximal thrust increment is 3.92% and the power consumption decreased by 5.68% at the same time. Computational Fluid Dynamics (CFD) simulations were further validated by streamlines and velocity distributions. It indicated that the rotor interference from the outflow was decreased with the rotor spacing while the increasing rotor speed aggravated the influence of the auxiliary rotor on the downwash airflow of the main rotor. The potential benefit of the rotor interference from the main rotor and the auxiliary rotor improved the hover efficiency of the orthogonal octo-rotor UAV with a higher thrust increment, which offers it the unique capability of resisting wind gusts or even rotor failure, which will be validated with more field flight tests.
Keyword ：
aerodynamic interference aerodynamic interference numerical simulations numerical simulations rotor spacing rotor spacing unmanned aerial vehicle (UAV) unmanned aerial vehicle (UAV)
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| GB/T 7714 | Lei, Yao , Yang, Hengxing , Hu, Jifu et al. Aerodynamic Optimization Design of an Orthogonal Octo-Rotor UAV in a Hovering State [J]. | DRONES , 2025 , 9 (4) . |
| MLA | Lei, Yao et al. "Aerodynamic Optimization Design of an Orthogonal Octo-Rotor UAV in a Hovering State" . | DRONES 9 . 4 (2025) . |
| APA | Lei, Yao , Yang, Hengxing , Hu, Jifu , Li, Xuan , Qiu, Jiafu , Zhang, Yuanfeng . Aerodynamic Optimization Design of an Orthogonal Octo-Rotor UAV in a Hovering State . | DRONES , 2025 , 9 (4) . |
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Abstract ：
The present work is aimed at investigating the arrangement design of an inner tilted-rotor hexacopter to optimize aerodynamic performance with different rotor spacing ratios (s/D) and dihedral angles (beta). Both experiments and numerical simulations were applied for different rotor arrangements, and the better rotor agreement was related to both higher thrust and lower power consumption. The results show that hovering efficiency is mainly affected by rotor spacing ratios and dihedral angles. Appropriate rotor spacing with moderate rotor interference from the blade tip vortices, as well as downwash flow, reduce vortex distortion and fragmentation. The results show that a hexacopter with inner tilted-rotors obtains a larger thrust and smaller power with a high factor of merit (FM) at s/D = 1.6 and beta = 40 degrees, and this is considered to be the optimal arrangement for a hexacopter with excellent aerodynamic characteristics.
Keyword ：
aerodynamic aerodynamic CFD CFD dihedral angle dihedral angle hexacopter hexacopter tilted-rotor tilted-rotor
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| GB/T 7714 | Lei, Yao , Luan, Chunfeng . Aerodynamic Analysis of a Hexacopter with an Inner Tilted-Rotor Configuration During Hovering [J]. | AEROSPACE , 2025 , 12 (4) . |
| MLA | Lei, Yao et al. "Aerodynamic Analysis of a Hexacopter with an Inner Tilted-Rotor Configuration During Hovering" . | AEROSPACE 12 . 4 (2025) . |
| APA | Lei, Yao , Luan, Chunfeng . Aerodynamic Analysis of a Hexacopter with an Inner Tilted-Rotor Configuration During Hovering . | AEROSPACE , 2025 , 12 (4) . |
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Abstract ：
Distributed electric propulsion (DEP) with four propellers distributed along the rear edge of the wing (pusher DEP configuration) promote aerodynamic interactions to a higher level. To study the aerodynamic performance of DEP with the rear wing through simulations and experiments, the multi-reference frame (MRF) with sliding grid is combined with wind tunnel tests. The obtained results demonstrate that the lift and drag of DEP increase with the angle of attack (AoA) and are related to the relative position of the propellers and wing. The propeller has no significant effect on the lift of the wing, and the lift and the AoA remain linear when the AoA is less than 16 degrees. By contrast, the lift coefficient is much higher than the baseline (isolated wing), and the lift is greatly improved with the increasing drag when the AoA is greater than 16 degrees. This is because the flow around the wing of the pusher configuration remains attached due to the suction of the inflow of the propeller on the trailing edge vortex. In addition, the acceleration effect on the free flow improves the kinetic energy of the airflow, which effectively delays the separation of the airflow in the slipstream region.
Keyword ：
aerodynamic interactions aerodynamic interactions distributed propulsion distributed propulsion numerical solution numerical solution wind tunnel tests wind tunnel tests
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| GB/T 7714 | Lei, Yao , Zhao, Xiangzheng . Aerodynamic Performance Assessment of Distributed Electric Propulsion after the Wing Trailing Edge [J]. | APPLIED SCIENCES-BASEL , 2024 , 14 (1) . |
| MLA | Lei, Yao et al. "Aerodynamic Performance Assessment of Distributed Electric Propulsion after the Wing Trailing Edge" . | APPLIED SCIENCES-BASEL 14 . 1 (2024) . |
| APA | Lei, Yao , Zhao, Xiangzheng . Aerodynamic Performance Assessment of Distributed Electric Propulsion after the Wing Trailing Edge . | APPLIED SCIENCES-BASEL , 2024 , 14 (1) . |
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Abstract ：
A novel octocopter with an overlapping rotor arrangement is proposed in this paper to increase the payload with a limited size. The aerodynamic performance was obtained by both experiments and numerical simulations with the rotor spacing ranging from 1.2 D to 2.0 D (L= 1.2 D, 1.4 D, 1.6 D, 1.8 D, 2.0 D). Also, the aerodynamic parameter was evaluated by the thrust, power consumption, thrust coefficient, power coefficient, and figure of merit (FM) in hover. Compared with a traditional co-axial octocopter, the results indicated that the overlapping octocopter at L= 1.8 D presented an increasing thrust up to 15.98%, and the FM increment was up to 6%. Additionally, the streamline distribution showed that the symmetry of the vortex movement in the downwash flow for the overlapping rotors will offset the rotor interference with an increase in thrust. Meanwhile, the vortex deformation resulting from the induced velocity from the upper rotor also led to an increase in power consumption. Finally, the optimal aerodynamic performance of the overlapping octocopter was obtained with a rotor spacing of L= 1.8 D at 1800 RPM.
Keyword ：
aerodynamic performance aerodynamic performance CFD CFD hover hover overlapping octocopter overlapping octocopter rotor interference rotor interference
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| GB/T 7714 | Lei, Yao , Zhao, Xiangzheng . The Aerodynamic Performance of a Novel Overlapping Octocopter in Hover [J]. | AEROSPACE , 2024 , 11 (9) . |
| MLA | Lei, Yao et al. "The Aerodynamic Performance of a Novel Overlapping Octocopter in Hover" . | AEROSPACE 11 . 9 (2024) . |
| APA | Lei, Yao , Zhao, Xiangzheng . The Aerodynamic Performance of a Novel Overlapping Octocopter in Hover . | AEROSPACE , 2024 , 11 (9) . |
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Abstract ：
A new multirotor aerial vehicle with two rotor arms formed in a V-shape configuration is introduced in this paper. To figure out the aerodynamic interference effects between rotors as an implication of the control method, this paper discusses the aerodynamic performance of the V8 Octorotor MAV with different rotor spacing using both experiments and simulations. A hovering experiment platform is applied to obtain the thrust, power consumption and rotational speed. PL (power loading) is promoted to characterize the aerodynamic performance of the V8 Octorotor MAV. The velocity vector, streamline and turbulent vortices' distribution of the V8 Octorotor MAV are presented as the simulation results, which indicates that turbulence intensity generated by the MAV dissipates faster in a large rotor spacing. Therefore, rotor vibration is reduced with an increased hovering stability, and the power loading is much improved at G3 (1.2D-1.4D-1.6D-1.8D) with a better aerodynamic performance both with a thrust increment and power decrement.
Keyword ：
aerodynamic performance aerodynamic performance CFD CFD rotor interference rotor interference rotor spacing rotor spacing V8 Octorotor MAV V8 Octorotor MAV
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| GB/T 7714 | Lei, Yao , Feng, Zhicheng , Ma, Chensong . Aerodynamic Performance of V8 Octorotor MAV with Different Rotor Configurations in Hover [J]. | MACHINES , 2023 , 11 (4) . |
| MLA | Lei, Yao et al. "Aerodynamic Performance of V8 Octorotor MAV with Different Rotor Configurations in Hover" . | MACHINES 11 . 4 (2023) . |
| APA | Lei, Yao , Feng, Zhicheng , Ma, Chensong . Aerodynamic Performance of V8 Octorotor MAV with Different Rotor Configurations in Hover . | MACHINES , 2023 , 11 (4) . |
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Abstract ：
This study focused on the in-hover aerodynamics of a small rotor with a thin circular-arc airfoil and a convex structure at a low Reynolds number. The method combined computational fluid dynamics (CFD) with the blade element momentum theory (BEMT). The former was used for studying the two-dimensional parametric aerodynamics of the airfoil at a low Reynolds number and the latter was used for the prediction of the rotor's hover performance. A novel thin circular-arc airfoil with a convex structure with a high aerodynamic performance, high structural strength, light weight and easy manufacturing process is presented in this paper. A convex curve on the upper surface was adopted to increase the thickness of the airfoil at partial chord, and a stiffener in the airfoil was installed to improve the structural strength of rotor span-wise. The aerodynamic performance of the airfoil was numerically simulated by the two-dimensional steady and incompressible Navier-Stokes equations. The in-hover performance of the rotor for small-scale vehicles was predicted by an improved version of the blade element momentum theory (BEMT). Finally, a carbon-fiber rotor with the presented airfoil was manufactured that had a diameter of 40 cm and a pitch of 6.2 inches. The analysis results were verified by experiments. It was shown that the maximum calculation errors were below 6%. The improved BEMT can be used in the analysis of in-hover micro-rotor aerodynamics at low Reynolds numbers.
Keyword ：
aerodynamics aerodynamics convex structure convex structure hover hover low Reynolds number low Reynolds number small rotor small rotor
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| GB/T 7714 | Lei, Yao , Wang, Jie , Li, Yazhou et al. In-Hover Aerodynamic Analysis of a Small Rotor with a Thin Circular-Arc Airfoil and a Convex Structure at Low Reynolds Number [J]. | MICROMACHINES , 2023 , 14 (3) . |
| MLA | Lei, Yao et al. "In-Hover Aerodynamic Analysis of a Small Rotor with a Thin Circular-Arc Airfoil and a Convex Structure at Low Reynolds Number" . | MICROMACHINES 14 . 3 (2023) . |
| APA | Lei, Yao , Wang, Jie , Li, Yazhou , Gao, Qingjia . In-Hover Aerodynamic Analysis of a Small Rotor with a Thin Circular-Arc Airfoil and a Convex Structure at Low Reynolds Number . | MICROMACHINES , 2023 , 14 (3) . |
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Abstract ：
本发明提出一种全驱万向四旋翼飞行器及其控制方法，其由两对旋翼组成，能够在任何位置和任何方向飞行。通过框架式的设计能够同时修改所有螺旋桨的倾斜角，从而解耦位置和姿态运动。在机架上安装了四个转子，通过两个转动接头转动机架，实现了两轴(滚动和俯仰)框架机构。这样就避免了采用复杂的闭链机构。这种解决方案不同于其他倾斜螺旋桨的全驱动UAV，它避免了由于螺旋桨轴不平行而产生的内力和能量耗散。具有抵消水平面扰动的能力，提高了飞行的稳定性。特别适用于需要UAV携带夹持器或机械臂来执行操作任务的应用当中。
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| GB/T 7714 | 雷瑶 , 雒栋华 , 李亚洲 et al. 全驱万向四旋翼飞行器及其控制方法 : CN202111366979.0[P]. | 2021-11-18 00:00:00 . |
| MLA | 雷瑶 et al. "全驱万向四旋翼飞行器及其控制方法" : CN202111366979.0. | 2021-11-18 00:00:00 . |
| APA | 雷瑶 , 雒栋华 , 李亚洲 , 王杰 . 全驱万向四旋翼飞行器及其控制方法 : CN202111366979.0. | 2021-11-18 00:00:00 . |
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Abstract ：
本发明涉及一种可以在空中抓取和停留的四旋翼飞行器，所述四旋翼飞行器下部设有用于抓取物体的被动侵入式卡具，以使四旋翼飞行器可以在飞行过程中与环境交互，允许四旋翼飞行器栖息在停靠物上以降低四旋翼飞行器的能耗；所述四旋翼飞行器上设有控制器，所述控制器用于估算飞行器质量和质心的偏移量，以提高跟踪性能。该四旋翼飞行器有利于在空中抓取物体以停留其上，进而提高与环境的交互能力。
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| GB/T 7714 | 雷瑶 , 李亚洲 , 雒栋华 et al. 一种可以在空中抓取和停留的四旋翼飞行器 : CN202111679780.3[P]. | 2021-12-31 00:00:00 . |
| MLA | 雷瑶 et al. "一种可以在空中抓取和停留的四旋翼飞行器" : CN202111679780.3. | 2021-12-31 00:00:00 . |
| APA | 雷瑶 , 李亚洲 , 雒栋华 , 王杰 . 一种可以在空中抓取和停留的四旋翼飞行器 : CN202111679780.3. | 2021-12-31 00:00:00 . |
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Abstract ：
本实用新型涉及一种缆索悬挂式空中机械臂系统，包括若干钢丝绳和固定架，所述固定架上设有若干用以控制各钢丝绳长度的绞盘装置，所述固定架周部连接有若干向外伸出的旋翼臂，所述旋翼臂上安装有伺服电机A，所述伺服电机A的转轴上连接有旋翼；所述固定架底部安装有机械臂。本实用新型缆索悬挂式空中机械臂系统设计合理，使用方便，可以悬挂在直升机或大旋翼无人机上使用，自身只需要与环境进行交互而不需要考虑自身重力，通过控制钢丝绳的长度可以完成翻转、俯仰和停留在不同高度，稳定性好，安全性高。
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| GB/T 7714 | 雷瑶 , 李亚洲 . 缆索悬挂式空中机械臂系统 : CN202223386376.X[P]. | 2022-12-15 00:00:00 . |
| MLA | 雷瑶 et al. "缆索悬挂式空中机械臂系统" : CN202223386376.X. | 2022-12-15 00:00:00 . |
| APA | 雷瑶 , 李亚洲 . 缆索悬挂式空中机械臂系统 : CN202223386376.X. | 2022-12-15 00:00:00 . |
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Abstract ：
为设计合理的旋翼布局来展现出共轴双旋翼系统的气动性能,通过搭建试验平台测量了共轴双旋翼飞行器的间距比为0.32R-0.75R的功耗和升力.另外,采用ANSYS建立了共轴双旋翼飞行器的全尺寸模型,并进行了一系列仿真,得到了不同间距下共轴双旋翼的压强、速度和流线分布.分析结果表明:共轴双旋翼间的气动干扰在合适的间距下被削弱,此时桨尖涡流完整.同时,整体的升力比单旋翼至少可以提升58％,最高可以提升72％.此外,还发现在产生相同升力时,在较低转速下产生的功率载荷PL值比较大.最后,值得注意的是,在旋翼间距h为0.385R时的气动性能较良好,是共轴双旋翼单元最佳的布局.
Keyword ：
共轴双旋翼 共轴双旋翼 功率载荷 功率载荷 旋翼布局 旋翼布局 旋翼间距 旋翼间距 气动性能 气动性能
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| GB/T 7714 | 雷瑶 , 叶艺强 , 王恒达 . 共轴双旋翼单元不同旋翼间距的气动性能分析 [J]. | 机械设计与制造 , 2023 , 384 (2) : 81-85 . |
| MLA | 雷瑶 et al. "共轴双旋翼单元不同旋翼间距的气动性能分析" . | 机械设计与制造 384 . 2 (2023) : 81-85 . |
| APA | 雷瑶 , 叶艺强 , 王恒达 . 共轴双旋翼单元不同旋翼间距的气动性能分析 . | 机械设计与制造 , 2023 , 384 (2) , 81-85 . |
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