Aerodynamic Design, Analysis and Validation of a Small Blended-Wing-Body Unmanned Aerial Vehicle

Wang, Kelei; Zhou, Zhou

doi:10.3390/aerospace9010036

Cited by 8 publications

(2 citation statements)

References 20 publications

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“…where AR ≈ 3 for the delta wing aircraft. Using the value of the aspect ratio in Equation ( 4), C Lα = 3.78 rads, which is similar to what is reported by Wang et al [30]. Additionally,…”

Section: Dynamic Modellingsupporting

confidence: 86%

Mathematical Modelling and Fluidic Thrust Vectoring Control of a Delta Wing UAV

Tanveer

Ahmad

2023

Aerospace

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Pitch control of an unmanned aerial vehicle (UAV) using fluidic thrust vectoring (FTV) is a relatively novel technique requiring no moving control surfaces, such as elevators. In this paper, the authors’ previous work on the characterization of a static co-flow FTV rig is further validated using the free to pitch dynamic test bench. The deflection of a primary jet after injection of a high-velocity secondary jet was captured using the tuft flow visualization technique, along with the experimental recording of subsequent normal force impinged on the Coanda surface resulting in the pitching moment. The effect of primary and secondary flow velocities on exhaust jet deflection, as well as on the pitch angle of the aircraft, is examined. Aerodynamic gain as well as the inertia of a delta wing UAV test bench are computed through experiments and fed into the equation of motion (e.o.m). The e.o.m developed aided in the design of a model-based PID controller for pitch motion control using the multi-parameter root locus technique. The root locus tuned controller serves as a benchmark controller for performance evaluation of the genetic algorithm (GA) and particle swarm optimization (PSO) tuned controllers. Furthermore, the frequency domain metric of gain and phase margins were also employed to reach a robust control design. Experiments conducted in a simulation environment reveal that PSO-PID results in a better response of the UAV in comparison to the baseline pitch controller.

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“…where AR ≈ 3 for the delta wing aircraft. Using the value of the aspect ratio in Equation ( 4), C Lα = 3.78 rads, which is similar to what is reported by Wang et al [30]. Additionally,…”

Section: Dynamic Modellingsupporting

confidence: 86%

Mathematical Modelling and Fluidic Thrust Vectoring Control of a Delta Wing UAV

Tanveer

Ahmad

2023

Aerospace

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“…The design of a trim distributed electric propulsion-based blended wing body configuration by CFD simulation and Wind tunnel testing to evaluate the design quality and obtained the lift-to-drag ratio of 22.31 at an angle of attack of 4°. The cruise condition's pitching moment and static margin met the required design requirements (Wang & Zhou, 2022). The design of agricultural use of unmanned aerial vehicles concluded that the UAVs did not require a separate navigation station and airport since they could be landed on the edge of the agricultural land.…”

Section: Introductionmentioning

confidence: 94%

Energy Industry and Industrial Design (Innovations in Energy Utilization and Equipment Design)

2024

JST

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This study represents the aerodynamic design of an Unmanned aerial vehicle intended for surveillance or agriculture with a maximum take weight of 125 kg. Weight estimation and constraint analysis were done based on the Mission profile. Design of Computer-Aided Design (CAD) models were generated for three different configurations using CATIA V5R20 as a high wing, mid-wing, and low wing. Flow analysis was done for the above configurations at various angles of attack. ANSYS 15 was used for the flow Analysis. A Tetrahedron element meshed the model with the minimum required orthogonal quality. Five microns were given to the initial layer height of the prism mesh. Spalart Allmaras model is used as the Turbulence model in the solver. The aerodynamic characteristics of the above configuration obtained from Computational Fluid Dynamics (CFD) results were compared with the DATCOM program and validated with the wind tunnel experimental test data. The open-circuited suction-type Subsonic wind tunnel was employed for the test. The aerodynamic properties for the angle of attack in the range of -2° to 14° angle of attack are calculated using a six-component balance.The study aims to find the Unmanned Aerial Vehicle (UAV) configuration based on the aerodynamic characteristics obtained from the CFD and DATCOM results. High-wing UAVs have better aerodynamic efficiency than the other two configurations.

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An Integrated Preliminary Approach Elaboration for the Analysis of a Blended Wing Body Aerostructure Concept

Hakim

Choukri

2023

Lecture Notes in Mechanical Engineering

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Aerodynamic Design, Analysis and Validation of a Small Blended-Wing-Body Unmanned Aerial Vehicle

Cited by 8 publications

References 20 publications

Mathematical Modelling and Fluidic Thrust Vectoring Control of a Delta Wing UAV

Mathematical Modelling and Fluidic Thrust Vectoring Control of a Delta Wing UAV

Energy Industry and Industrial Design (Innovations in Energy Utilization and Equipment Design)

An Integrated Preliminary Approach Elaboration for the Analysis of a Blended Wing Body Aerostructure Concept

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