Conceptual Design of an Unmanned Fixed-Wing Aerial Vehicle Based on Alternative Energy

Escobar-Ruiz, Alan G.; López-Botello, Omar; Reyes, Luis A.; Zambrano‐Robledo, Patricia del Carmen; Amézquita-Brooks, Luis; Garcia‐Salazar, Octavio

doi:10.1155/2019/8104927

Cited by 19 publications

(10 citation statements)

References 29 publications

(33 reference statements)

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“…They further concluded that the efficiency is much improved due to the reduction in drag and increment in lift-to-drag ratio. Moreover, Escobar-Ruiz et al [ 28 ] have used solar cells specifically as the main power source in designing unmanned aerial vehicles (UAV). There are three basic building blocks in this mechanism: preliminary design, conceptual design, and computational fluid dynamics analysis.…”

Section: Related Workmentioning

confidence: 99%

Quality-of-Service-Centric Design and Analysis of Unmanned Aerial Vehicles

Jha

Prakash

Rathore

et al. 2022

Sensors

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Recent years have witnessed rapid development and great indignation burgeoning in the unmanned aerial vehicles (UAV) field. This growth of UAV-related research contributes to several challenges, including inter-communication from vehicle to vehicle, transportation coverage, network information gathering, network interworking effectiveness, etc. Due to ease of usage, UAVs have found novel applications in various areas such as agriculture, defence, security, medicine, and observation for traffic-monitoring applications. This paper presents an innovative drone system by designing and developing a blended-wing-body (BWB)-based configuration for next-generation drone use cases. The proposed method has several benefits, including a very low interference drag, evenly distributed load inside the body, and less radar signature compared to the state-of-the-art configurations. During the entire procedure, a standard design approach was followed to optimise the BWB framework for next-generation use cases by considering the typically associated parameters such as vertical take-off and landing and drag and stability of the BWB. Extensive simulation experiments were performed to carry out a performance analysis of the proposed model in a software-based environment. To further confirm that the model design of the BWB-UAV is fit to execute the targeted missions, the real-time working environments were tested through advanced numerical simulation and focused on avoiding cost and unwanted wastages. To enhance the trustworthiness of this said computational fluid dynamics (CFD) analysis, grid convergence test-based validation was also conducted. Two different grid convergence tests were conducted on the induced velocity of the Version I UAV and equivalent stress of the Version II UAV. Finite element analysis-based computations were involved in estimating structural outcomes. Finally, the mesh quality was obtained as 0.984 out of 1. The proposed model is very cost-effective for performing a different kind of manoeuvring activities with the help of its unique design at reasonable mobility speed and hence can be modelled for high-speed-based complex next-generation use cases.

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Section: Related Workmentioning

confidence: 99%

Quality-of-Service-Centric Design and Analysis of Unmanned Aerial Vehicles

Jha

Prakash

Rathore

et al. 2022

Sensors

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“…Existen áreas de oportunidad como aplicaciones de los VANTs en agricultura de precisión, inspección de infraestructura, valuación catastral, y diseño de nuevas configuraciones de VANTs, por ejemplo, aeronaves híbridas, aeronaves convertibles. En esta segunda área de oportunidad los resultados en México son limitados, algunas publicaciones en este sentido son Rodríguez-Cortés and Arias-Montaño (2012), Escobar-Ruiz et al (2019).…”

Section: Los Sensores Smem Se Masificanunclassified

Aportaciones al control de vehículos aéreos no tripulados en México

Rodriguez-Cortes

2022

Rev. iberoam. autom. inform. ind.

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El avance en el desarrollo de sistemas microelectromecánicos (MEMS) hizo posible el uso de sensores inerciales y visuales en vehículos aéreos no tripulados de pequeñas dimensiones y bajo costo. Este hecho potenciado con herramientas de la teoría de control automático y las ingenierías aeronáutica, mecatrónica e informática ha permitido lograr niveles de autonomía sorprendentes en este tipo de vehículos. Este trabajo describe una cronología sobre el desarrollo de vehículos aéreos no tripulados desarrollados por investigadores mexicanos. Además, se presenta una solución al problema de seguimiento de trayectorias para el vehículo multi rotor conocido como cuatrirotor. El algoritmo de control se sintetiza siguiendo la metodología conocida como sistema de control total de la energía (TECS). Finalmente, la estrategia de control propuesta se evalúa experimentalmente en tiempo real estricto utilizando un cuatrirotor hecho en casa.

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“…The airfoil of the wing used for the wind tunnel tests is modified from the MH32 asymmetric airfoil, 18 whose geometry is shown in Figure 2. The wingspan is 1 m. The wing has some taper, such that its chord is 0.25 m at the root and 0.2 m at the tip.…”

Section: Experiments Setupmentioning

confidence: 99%

Wind tunnel tests of a wing at all angles of attack

Smeur

Croon

2022

International Journal of Micro Air Vehicles

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Tailsitters have complex aerodynamics that make them hard to control throughout the entire flight envelope, especially at very high angle of attack (AoA) and reverse flow conditions. The development of controllers for these vehicles is hampered by the absence of publicly available data on forces and moments experienced in such conditions. In this paper, wind tunnel experiments are performed under different flap deflections and throttle settings at all possible AoA. The dataset is made open access. Our analysis of the data shows for the tested wing, flap deflections greatly affect the lift coefficient and stall occurs at [Formula: see text] AoA as well as [Formula: see text]. Wing-propeller interaction is studied by analyzing the propeller induced force in the axis orthogonal to the thrust axis, which is dependent on AoA, airspeed, flap deflections and thrust in a nonlinear and coupled manner. The influence of inverse flow on the wing is also discussed: The data confirm that when the airflow over the wing is reversed, flap deflections will affect the pitch moment in an opposite way compared to the non-reversed case, but this opposite effect can be avoided by increasing the throttle setting. The data show the exact relationship between flap deflections and forces in this condition. Moreover, it is found that the flap control effectiveness for a wing with or without spinning propellers is usually higher around zero degrees AoA than at [Formula: see text] and it is more effective to change the flaps from [Formula: see text] to [Formula: see text] than from [Formula: see text] to the respective [Formula: see text].

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Conceptual Design of an Unmanned Fixed-Wing Aerial Vehicle Based on Alternative Energy

Cited by 19 publications

References 29 publications

Quality-of-Service-Centric Design and Analysis of Unmanned Aerial Vehicles

Quality-of-Service-Centric Design and Analysis of Unmanned Aerial Vehicles

Aportaciones al control de vehículos aéreos no tripulados en México

Wind tunnel tests of a wing at all angles of attack

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