Sizing of Multicopter Air Taxis—Weight, Endurance, and Range
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Published:2024-03-01
Issue:3
Volume:11
Page:200
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ISSN:2226-4310
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Container-title:Aerospace
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language:en
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Short-container-title:Aerospace
Author:
Yang Yannian1ORCID, Liang Yu2, Pröbsting Stefan3ORCID, Li Pengyu4ORCID, Zhang Haoyu4, Huang Benxu1, Liu Chaofan5, Pei Hailong1ORCID, Noack Bernd R.67ORCID
Affiliation:
1. Key Laboratory of Autonomous Systems and Networked Control, Ministry of Education, Guangdong Engineering Technology Research Center of Unmanned Aerial Vehicle Systems, School of Automation Science and Engineering, South China University of Technology, Guangzhou 510640, China 2. Institute of Unmanned System, Beihang University, Beijing 100191, China 3. Department of Naval Architecture and Ocean Engineering, Shanghai Jiao Tong University, Shanghai 200240, China 4. Department of Mechanics and Aerospace Engineering, Southern University of Science and Technology, Shenzhen 518055, China 5. Rotor Aerodynamics Key Laboratory, China Aerodynamic Research and Development Center, Mianyang 621000, China 6. Chair of Artificial Intelligence and Aerodynamics, School of Mechanical Engineering and Automation, Harbin Institute of Technology, Shenzhen 518055, China 7. Guangdong Provincial Key Laboratory of Intelligent Morphing Mechanisms and Adaptive Robotics, Harbin Institute of Technology, Shenzhen 518055, China
Abstract
In the near future, urban air mobility (UAM) will let an old dream of human society come true: affordable and fast air transportation for almost everyone. Among the various existing designs, the multicopter configuration best combines the advantages of compactness, simplicity, and maturity. These aspects are important for actual use, particularly during the early stage of this market. This study elaborates on the design principles of UAM multicopters by examining existing models in terms of their configuration, weight, and range specifications. In particular, the weights of the different components are estimated based on empirical models, aerodynamic fundamentals for the analysis of UAM multicopters are derived from momentum theory, and the power and energy requirements for hovering and cruise flight are evaluated, thereby enabling estimation of the maximum hovering time and flight range. Finally, a sizing method is introduced and validated against an actual UAM design.
Funder
AVIC General Aircraft Research Institute Laboratory of Aerodynamic Noise Control of the China Aerodynamics Research and Development Center Rotor Aerodynamics Key Laboratory of the China Aerodynamics Research and Development Center National Science Foundation of China Guangdong Basic and Applied Basic Research Foundation Guangdong Provincial Key Laboratory of Intelligent Morghing Mechanisms and Adaptive Robotics Shenzhen Science and Technology Program
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