Design, fabrication &amp; performance analysis of an unmanned aerial vehicle

Khan, Muhammad; Salam, Md. Abdus; Afsar, Md. Rayhan; Huda, M. Nazmul; Mahmud, Tanveer

doi:10.1063/1.4958448

Cited by 4 publications

(3 citation statements)

References 2 publications

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“…Physics based analysis to generate feasible aircraft models has been designed using CAD model bases of optimal design for a mission (Locascio et al, 2016). Well-thought-of demonstrated flight handling qualities, practical and affordable manufacturing requirements providing a high vehicle performance has been studied and the requirement of ferry flight mission was to fly as many laps as possible within 4 minutes has been observed (Khan et al, 2016). For such application presented a conceptual design of a UAV with a battery powered propulsion system.…”

Section: Literature Surveymentioning

confidence: 99%

Design and Fabrication of Unmanned Arial Vehicle for Multi-Mission Tasks

al.¹

2018

IJMPERD

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The design for UAV was planned taking into account the real-life engineering problems such as different phases involved in developing a product. Here the task is to design, create, build and test a remote-control airplane. The planning and designing of an aircraft must start from the scratch, with lots of restrictions and parameters, like a specific motor to be used from the wing profile, dimensions, centre of gravity, materials and other features which are all involved in the process. The main objective of this UAV is to design an aircraft which is efficient during emergency situations and is capable of dropping packages from a minimum height of 100 feet off the ground. A vision-based control strategy is used in this to track and follow objects using an unmanned aerial vehicle (UAV). This unmanned aerial vehicle is created in such a way that it can be used in multi-mission tasks too. The most favorable design must be of one which can perform efficiently, cost-effectively and carry as many payloads as possible, and all these without negotiating on the safety of the aircraft.

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Section: Literature Surveymentioning

confidence: 99%

Design and Fabrication of Unmanned Arial Vehicle for Multi-Mission Tasks

al.¹

2018

IJMPERD

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“…In this study, they proposed a design procedure consisting of: the definition of the mission requirement, the explanation of the design, the detailed design of the vehicle components, the configuration of the navigation system, and the final design. Similar to the previous authors, Khan et al [6] proposed a design procedure that includes the following steps: the preliminary design, which includes the selection of the aerodynamic profile of the wing and empennage and the sizing and design of components; the determination of stability characteristics; and the detailed design. Likewise, Kontogiannis et al [7] proposed four main design stages: conceptual design, preliminary design, aerodynamic analysis and optimization, and final design.…”

Section: Introductionmentioning

confidence: 99%

Design and Determination of Aerodynamic Coefficients of a Tail-Sitter Aircraft by Means of CFD Numerical Simulation

et al. 2022

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Vertical take-off and landing (VTOL) aircraft have become important aerial vehicles for various sectors, such as security, health, and commercial sectors. These vehicles are capable of operating in different flight modes, allowing for the covering of most flight requirements in most environments. A tail-sitter aircraft is a type of VTOL vehicle that has the ability to take off and land vertically on it elevators (its tail) or on some rigid support element that extends behind the trailing edge. Most of the tail-sitter aircraft are designed with a fixed-wing adaptation rather than having their own design. The design of the tail-sitter carried out in this work had the particularity of not being an adaptation of a quad-rotor system in a commercial swept-wing aircraft, but, rather, was made from its own geometry in a twin-rotor configuration. The design was performed using ANSYS SpaceClaim CAD software, and a numerical analysis of the performance was carried out in ANSYS Fluent CFD software. The numerical results were satisfactorily validated with empirical correlations for the calculation of the polar curve, and the performance of the proposed tail-sitter was satisfactory compared to those found in the literature. The results of velocity and pressure contours were obtained for various angles of attack. The force and moment coefficients obtained showed trends similar to those reported in the literature.

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“…The origin and growth are highlighted in this review study... This review study emphasizes the creation and evolution of UAVs, their classification and comparison, as well as the difficulties in designing hardware and software for UAVs with a range of capabilities for both civil and military purposes [2] for an international aircraft design competition, a fully functional unmanned aerial vehicle, was created after extensive design, analysis, and fabrication. The goal was to produce a refined look that has high vehicle performance, feasible and inexpensive manufacturing needs, and good demonstrated flight handling qualities.…”

Section: Introductionmentioning

confidence: 99%

UAV Structure and Aerodynamic Character Research on two different Airfoils

2021

Webology

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The geometry and wing profile of an aircraft has a direct bearing on the aerodynamic forces, namely lift and drag, operating on it. As part of this experiment, we first created a fixed-wing UAV (IAI Heron 1) and then ran a CFD analysis on it. We developed two designs based on two different aerofoils, concentrating on the lift-to-drag ratio in Cruise circumstances. For computing various lift to drag ratios, these two designs will have three different angles of attack. Simulations were run using the ANSYS FLUENT program. We measured three input velocities to determine whether an increase or decrease in values would have an impact on the ratio while maintaining atmospheric pressure. The values for the Lift force Velocity and Pressure Contours were also discovered. Usable equations were utilized to estimate drag in the post-CFD results. The most efficient configuration and angle of attack are identified using the graphs that display the uplift to drag proportion and direction of attack.

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Design, fabrication & performance analysis of an unmanned aerial vehicle

Cited by 4 publications

References 2 publications

Design and Fabrication of Unmanned Arial Vehicle for Multi-Mission Tasks

Design and Fabrication of Unmanned Arial Vehicle for Multi-Mission Tasks

Design and Determination of Aerodynamic Coefficients of a Tail-Sitter Aircraft by Means of CFD Numerical Simulation

UAV Structure and Aerodynamic Character Research on two different Airfoils

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