Query：
学者姓名：雷瑶
Refining：
Year
Type
Indexed by
Source
Complex
Co-
Language
Clean All
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
Cite：
Copy from the list or Export to your reference management。
| 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 等. "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) . |
| Export to | NoteExpress RIS BibTex |
Version ：
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
Cite：
Copy from the list or Export to your reference management。
| 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 等. "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 . |
| Export to | NoteExpress RIS BibTex |
Version ：
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
Cite：
Copy from the list or Export to your reference management。
| 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) . |
| Export to | NoteExpress RIS BibTex |
Version ：
Abstract ：
In this paper, the aerodynamic performance of an orthogonal octorotor UAV considering horizontal wind disturbances is investigated with numerical simulations and experiments. To obtian the effect of horizontal wind on the flight efficiency of the orthogonal octorotor UAV, the power consumption and thrust with different wind speeds (0-4 m/s) and rotational speeds (1500-2300 RPM) are measured in a low-speed wind tunnel. Also, the velocity distribution of downwash flow, blade tip vortex distribution, streamline distribution and rotor blade tip pressure distribution of the orthogonal octorotor UAV were simulated by the computational fluid dynamics (CFD). The test results show that the thrust is increased at lower wind speed compared with 0 m/s. Specifically, it increased by 8.1% at 2 m/s and 8.8% at 4 m/s, respectively. It is interesting to note that the increased power consumption caused by the interference of horizontal wind at a higher rotor speed leads to a decrease in power loading (PL). Additionally, the thrust increased with a higher PL at low speed, where the PL achieved the maximum for the wind of 2.5 m/s and obtained a better aerodynamic performance. Compared with traditional octorotor UAVs and eight equivalent isolated rotors, the orthogonal octorotor UAV has also been proven to obtain good wind resistance. Simulation results show that the increase in wind speed and rotor speed will make the flow field more complex and the airflow interference between rotors more intense, which leads to changes in rotor thrust and power consumption.
Keyword ：
aerodynamic interference aerodynamic interference horizontal wind horizontal wind multi-rotor multi-rotor orthogonal octorotor UAV orthogonal octorotor UAV wind tunnel tests wind tunnel tests
Cite：
Copy from the list or Export to your reference management。
| GB/T 7714 | Lei, Yao , Li, Yazhou , Wang, Jie . Aerodynamic Analysis of an Orthogonal Octorotor UAV Considering Horizontal Wind Disturbance [J]. | AEROSPACE , 2023 , 10 (6) . |
| MLA | Lei, Yao et al. "Aerodynamic Analysis of an Orthogonal Octorotor UAV Considering Horizontal Wind Disturbance" . | AEROSPACE 10 . 6 (2023) . |
| APA | Lei, Yao , Li, Yazhou , Wang, Jie . Aerodynamic Analysis of an Orthogonal Octorotor UAV Considering Horizontal Wind Disturbance . | AEROSPACE , 2023 , 10 (6) . |
| Export to | NoteExpress RIS BibTex |
Version ：
Abstract ：
Experimental tests and numerical simulations were typically presented with a rotor spacing of 1.2 times the diameter to investigate the effect of disc angle (DA) on the hover performance of non-planar multi-rotor unmanned aerial vehicles (UAVs). Torque, thrust coefficient, power coefficient, and power loading measurements were performed to evaluate the performance of the vehicles with different rotor rational speeds and DAs. The hovering performance exhibits a maximum improvement of 10.3 % when DA = 50 degrees compared with the traditional planar muti-rotor system. The flow fields were also simulated by unsteady Reynolds-averaged Navier-Stokes solver. The downwash shifts, flow contractions, pressure difference enlargements, and wake inclinations were discovered and contributed to the interference reduction with the increasing DA. Based on these observations, the tilt-rotor configuration has a noticeable enhancement on the hovering performance of UAVs with proper DA. The insights gained can be applied as guidance for further UAV design.
Keyword ：
Aerodynamic interaction Aerodynamic interaction Multi-rotor UAV Multi-rotor UAV Numerical simulations Numerical simulations Rotor aerodynamics Rotor aerodynamics Tilt-rotor Tilt-rotor
Cite：
Copy from the list or Export to your reference management。
| GB/T 7714 | Lei, Yao , Wang, Jiading , Yang, Wenjie . Aerodynamic performance of a non-planar multi-rotor air-craft in hover [J]. | JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY , 2023 , 37 (6) : 2933-2940 . |
| MLA | Lei, Yao et al. "Aerodynamic performance of a non-planar multi-rotor air-craft in hover" . | JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY 37 . 6 (2023) : 2933-2940 . |
| APA | Lei, Yao , Wang, Jiading , Yang, Wenjie . Aerodynamic performance of a non-planar multi-rotor air-craft in hover . | JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY , 2023 , 37 (6) , 2933-2940 . |
| Export to | NoteExpress RIS BibTex |
Version ：
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
Cite：
Copy from the list or Export to your reference management。
| 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) . |
| Export to | NoteExpress RIS BibTex |
Version ：
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。
Cite：
Copy from the list or Export to your reference management。
| 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 . |
| Export to | NoteExpress RIS BibTex |
Version ：
Abstract ：
This paper investigates the aerodynamic performance of an overlapping octocopter with the effect of horizontal wind ranging from 0 to 4 m/s using both low-speed wind tunnel tests and numerical simulations. The hovering efficiency and the potential control strategies of the octocopter under the effect of horizontal wind are also validated using blade element momentum theory. The velocity distribution, rotor pressure and vortex of the downwash flow with the horizontal wind are presented using the Computational Fluid Dynamics (CFD) method. Finally, wind tunnel tests were performed to obtain the thrust and power consumption with the rotor speed ranging from 1500 to 2200 rpm for horizontal winds at 0 m/s, 2.5 m/s and 4 m/s. The results showed that horizontal wind decreased the flight efficiency of the planar octocopter and had little effect on the coaxial octocopter. It is also interesting to note that horizontal wind is beneficial for thrust increments at a higher rotor speed and power decrements at a lower rotor speed for the overlapping octocopter. Specifically, the horizontal wind of 2.5 m/s for a lower rpm is presented with a power decrement with proper aerodynamic interference between the rotor blades. Additionally, the overlapping octocopter obtains a higher hover efficiency at 4 m/s compared to traditional octocopters, which is more suitable for flying in a cross wind with a more compact structure.
Keyword ：
aerodynamics aerodynamics horizontal wind horizontal wind hover hover overlapping octocopter overlapping octocopter UAV UAV
Cite：
Copy from the list or Export to your reference management。
| GB/T 7714 | Lei, Yao , Wang, Jie , Li, Yazhou . The Aerodynamic Performance of a Novel Overlapping Octocopter Considering Horizontal Wind [J]. | AEROSPACE , 2023 , 10 (10) . |
| MLA | Lei, Yao et al. "The Aerodynamic Performance of a Novel Overlapping Octocopter Considering Horizontal Wind" . | AEROSPACE 10 . 10 (2023) . |
| APA | Lei, Yao , Wang, Jie , Li, Yazhou . The Aerodynamic Performance of a Novel Overlapping Octocopter Considering Horizontal Wind . | AEROSPACE , 2023 , 10 (10) . |
| Export to | NoteExpress RIS BibTex |
Version ：
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。
Cite：
Copy from the list or Export to your reference management。
| 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 . |
| Export to | NoteExpress RIS BibTex |
Version ：
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。
Cite：
Copy from the list or Export to your reference management。
| 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 . |
| Export to | NoteExpress RIS BibTex |
Version ：
Export
| Results： |
Selected to |
| Format： |
