| Study of different flight conditions on the performance of an unmanned aerial vehicle (UAV) |
| کد مقاله : 1266-AERO2024 |
| نویسندگان |
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Farshid Gheytoorian Nabikandi *1، Reza Esmaily2، Mahmoud Shamsborhan2، Amir Hassanzadeh3 1Department of Mechanical Engineering, Lahijan Branch, Islamic Azad University, Lahijan, Iran. 2Department of Mechanical Engineering, Mahabad Branch, Islamic Azad University, Mahabad, 59139-33137, Iran. 3Department of Mechanical Engineering, Urmia University, Urmia, Iran. |
| چکیده مقاله |
| The present study is a study of an unmanned aerial vehicle (UAV) based on the requirements of its mission and then conducting a parameter study that can relate the changes in aerodynamic and geometric parameters to the UAV's performance. In this research, it is assumed that the goal is to design a light delta-wing UAV, which can be used for mapping, patrolling and data collection purposes. Regarding the characteristics of this manuscript, it can be mentioned that by having the results of a quantitative study in the field of geometry and aerodynamics, then it is possible to move towards optimization and reduction of construction costs. In addition, the aerodynamic of the UAV is considered and the modeling of delta wing is done using simple algebraic equations that presents lift and drag forces quantity generally. In addition, the maximum speed of 280 km/h is suggested during the flight. The minimum flight altitude of the present UAV while carrying out a mission is more than 2000 meters. The power required for flight increases with increasing flight speed, but decreases with increasing altitude. |
| کلیدواژه ها |
| Unmanned aerial vehicle - Lift coefficient - Drag coefficient - Aerodynamic parameters - Angle of attack. |
| وضعیت: پذیرفته شده برای ارائه شفاهی |
