Electric propulsion system sizing methodology for an agriculture multicopter

被引：47

作者：

Ngoc Anh Vu ^{[1
]}

Duy Khang Dang ^{[1
]}

Tuan Le Dinh ^{[1
]}

机构：

[1] Vietnam Natl Univ, Ho Chi Minh City Univ Technol, Dept Aerosp Engn, Ho Chi Minh, Vietnam

来源：

AEROSPACE SCIENCE AND TECHNOLOGY | 2019年 / 90卷

关键词：

Multicopter design; Electrical propulsion sizing; Blade elements momentum theory; UAV; DESIGN; OPTIMIZATION;

D O I：

10.1016/j.ast.2019.04.044

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Using a suitable propulsion system for Drones capable of obtaining desired performance is one of the primary goals for designing electric multicopters. Choosing the right components for the electric system: Motor, ESC, battery, rotor (propeller) is always challenging because of the diversity of and misleading information on these products on the market. By studying specifications brought by manufacturers and experimental data, the relationship of the components in the propulsion system is given and parameterized. This paper presents a method to size the electric propulsion system for design and manufacturing a multicopter that is able to handle mission requirements. The sensitivity of design parameters to GTOW is given. An Agriculture Quadcopter is built and compared to the results of sizing and the difference stays within +/- 4% for gross take-off weight. The maximum thrust over weight ratio is introduced, and the cut of payload during operation of pesticide spraying is also accounted in the calculation for improvement of sizing the Quadcopter. (C) 2019 Elsevier Masson SAS. All rights reserved.

引用

页码：314 / 326

页数：13

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