Investigation and Improvement of Pusher-Propeller Installation Effect for Flying Wing UAV

Shi, Wenbo; Li, Jie; Zhao, Shuai; Yang, Zhao

doi:10.1007/s42405-020-00316-0

Cited by 3 publications

(1 citation statement)

References 15 publications

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“…According to the minimum dimensions of ball valve and ball joint bearing, the minimum length of vector bracket is determined to be 50mm. According to the existing literature on the mutual aerodynamic interactions between propellers and UAV, the research range for Sun(2021) is 5 30mm to 190mm [22] , for Shi et al(2020Shi et al( ,2021 it is 14mm to 90mm [23,24] , and for Zhang(2022), the range is 0.24 to 0.64R [25] ,…”

Section: Structure Of Uavmentioning

confidence: 99%

Structural design and parameter optimization of vector brackets for vertical take-off and landing unmanned Aerial Vehicle

Liu,

Quan,

Wang

et al. 2024

Preprint

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By carrying out a central composite design (CCD) test, 49 sample points of the four particular factors were constructed. The lift-to-drag ratio and thrust coefficient were simulated under different structural parameter combinations using the Computational Fluid Dynamics (CFD) method. CFD simulation was verified by carrying out a wind tunnel test, and the results revealed that the thrust coefficient error was less than 9% while the lift-to-drag ratio error was less than 8%. The response surface methodology (RSM) for the lift-to-drag ratio and thrust coefficient was established using a Kriging algorithm. A multi-objective genetic algorithm (MOGA) was used to optimize the parameters with regard to the maximum lift-to-drag ratio and maximum thrust coefficient. The optimal structural parameters were valve diameter at 31 mm, vector bracket length at 51 mm, fixed bracket width at 69 mm, and fixed bracket length at 168. Compared to the original model, the thrust coefficient increased by 19%, and the lift-to-drag ratio did not decrease.

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Section: Structure Of Uavmentioning

confidence: 99%

Structural design and parameter optimization of vector brackets for vertical take-off and landing unmanned Aerial Vehicle

Liu,

Quan,

Wang

et al. 2024

Preprint

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Aerodynamic Simulation of a Cargo UAV with Twin-Boom and Rear-Mounted Propeller

Chen,

Wang,

Liu

et al. 2024

2023 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2023) Proceedings

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Enhancing the Resolution of Blade Tip Vortices in Hover with High-Order WENO Scheme and Hybrid RANS–LES Methods

Shi

Zhang

2023

Aerospace

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The accurate prediction of blade tip vortices continues to be challenging for the investigation of rotor aerodynamics. In the current work, the blade tip vortex system of a Caradonna–Tung rotor in the hovering state is simulated on account of the framework of a high-order WENO scheme and hybrid RANS/LES method progressively. With the RANS method based on a fifth-order WENO–Roe scheme, the spatial resolution of wake age and capture the accuracy of tip vortices are improved significantly. However, the unsteadiness of the vortex system fails to be distinguished. Then, the DDES and IDDES methods, coupled with a fifth-order WENO–Roe scheme, are implemented to further enhance the resolution of the spatial turbulence. Compared with RANS, the improvement of spatial resolution is reflected in both the statistical and transient results with DDES. The identifiable vortex core distributions can be predicted at older wake ages. The asymmetrical characteristic of blade tip vortices is revealed along with the release of fluctuation while the predicted distribution of velocity profiles in the vortex core is enhanced. With the application of IDDES, the secondary turbulent structures are captured around the primary vortex core of blade tip vortices while the complex behaviors of the vortices are observed. However, the statistics of the averaged flow field are similar to DDES.

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Investigation and Improvement of Pusher-Propeller Installation Effect for Flying Wing UAV

Cited by 3 publications

References 15 publications

Structural design and parameter optimization of vector brackets for vertical take-off and landing unmanned Aerial Vehicle

Structural design and parameter optimization of vector brackets for vertical take-off and landing unmanned Aerial Vehicle

Aerodynamic Simulation of a Cargo UAV with Twin-Boom and Rear-Mounted Propeller

Enhancing the Resolution of Blade Tip Vortices in Hover with High-Order WENO Scheme and Hybrid RANS–LES Methods

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