Design and Analysis of a Light Cargo UAV Prototype

Kovanis, Anastasios P.; Skaperdas, Vangelis; Ekaterinaris, John A.

doi:10.1061/(asce)as.1943-5525.0000120

Cited by 13 publications

(3 citation statements)

References 23 publications

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“…Multirotors can raise from 50 to 100 percent of their weight (Jones 2007). However, aircraft wing area and speed are usually higher than those of the other alternatives; so the maximum payload is greater (Faust et al 2013;Kovanis et al 2012).…”

Section: Mathematical Modelmentioning

confidence: 99%

Research of Remotely Piloted Vehicles for Cargo Transportation

Ragauskas¹,

Bručas²,

Visockienė

2016

Aviation

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Remotely piloted vehicles (RPV) are used in various fields. The article analyses RPV usage for aerial cargo transportation. The first part is an overview of RPVs used across the world as cargo transportation, their examples and prototypes, as well as the comparison of their advantages and disadvantages. The second part is an analysis of aircraft structural components, by comparing their various configurations. The best cargo delivery method is analysed; and a mathematical model of cargo drop from vehicle is presented.

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Section: Mathematical Modelmentioning

confidence: 99%

Research of Remotely Piloted Vehicles for Cargo Transportation

Ragauskas¹,

Bručas²,

Visockienė

2016

Aviation

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“…Indeed, to achieve the same capability as current delivery methods, the UAV must be capable of reaching all types of terrain in a short time. Recent research, such as (Yolcu and Akdağ, 2021;Ashish et al, 2020;Kovanis et al, 2012) test and present conceptual designs of small and light cargo Vertical Take-Off Landing (VTOL) UAVs able to carry payload for civilian purposes. Moreover, (Ashish et al, 2020) designed and described the potential of hybrid power VTOL for emergency delivery, (Finger, 2016) and collected data from 250 VTOL and Conventional Take-Off Landing (CTOL) UAVs for performance comparison (Nugroho et al, 2022) to analyze different Tails configurations for UAVs and (Khadka et al, 2020) presents the benefits of an inverted V-tail for a UAV.…”

Section: Introductionmentioning

confidence: 99%

Preliminary Design and Performance-Stability Analysis of a Fixed-Wing UAV Using XFLR5

Victor Antonio,

Yan

2023

Journal of Aircraft and Spacecraft Technology

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This research aims to find the best airfoil and tail configuration for the designing of a UAV of 30 kg capable of carrying a payload of at least 5 kg; for this purpose, work focuses on the analysis of different airfoils for low Reynolds numbers in specific do airfoils with an under cambered design and capable of reaching high lift at low altitudes at subsonic speeds, at the same time four different tail configuration of similar sizes are contrasted to each other to find out what configuration gives the best design in terms of performance and stability. XFLR5, specialized software for analyzing airfoils, wings, and planes operating at low Reynolds numbers, is used for all simulations. This study successfully determined the Eppler 216 as the best airfoil along with the conventional tail configuration while providing a valuable methodology for designing future and similar UAVs.

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“…Since ACC is a demanding multidisciplinary design problem, no single work has been published covering all relevant coupled disciplines. Among the few published works, excluding academic bachelor and master theses, the most significant scientific documents reveal emphasis on singular disciplines, such as aerodynamic design [2,3], mass prediction models [4], parametric geometric definition [5] or flight dynamics and control [6].…”

Section: Introductionmentioning

confidence: 99%

Concurrent Trajectory Optimization and Aircraft Design for the Air Cargo Challenge Competition

Matos

Marta

2022

Aerospace

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A coupled aerostructural aircraft design and trajectory optimization framework is developed for the Air Cargo Challenge competition to maximize the expected score based on cargo carried, altitude achieved and distance traveled. Its modular architecture makes it easily adaptable to any problem where the performance depends not only on the design of the aircraft but also on its flight trajectory. It is based on OpenAeroStruct, an aerostructural solver that uses analytic derivatives for efficient gradient-based optimization. A trajectory optimization module using a collocation method is coupled with the option of using b-splines to increase computational efficiency together with an experimentally-based power decay model that accurately determines the aircraft propulsive response to control input depending on the battery discharge level. The optimization problem totaled 206 variables and 283 constraints and was solved in less than 7 h on a standard computer with 12% reduction when using b-splines for trajectory control variables. The results revealed the need to consider the multi-objective total score to account for the different score components and highlighted the importance of the payload level and chosen trajectory. The wing area should be increased within allowable limits to maximize payload capacity, climb to maximum target height should be the focus of the first 60 s of flight and full throttle should be avoided in cruise to reduce losses and extend flight distance. The framework proved to be a valuable tool for students to easily obtain guidelines for both the model aircraft design and control to maximize the competition score.

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Design and Analysis of a Light Cargo UAV Prototype

Cited by 13 publications

References 23 publications

Research of Remotely Piloted Vehicles for Cargo Transportation

Research of Remotely Piloted Vehicles for Cargo Transportation

Preliminary Design and Performance-Stability Analysis of a Fixed-Wing UAV Using XFLR5

Concurrent Trajectory Optimization and Aircraft Design for the Air Cargo Challenge Competition

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