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    • Design of a Fuel-Electric Hybrid Composite Wing Unmanned Aerial Vehicle （UAV） with Enhanced Vertical Flight Performance
    DOI：10.13949/j.cnki.nrjgc.2025.03.011
    Key Words:fuel-electric hybrid power  unmanned aerial vehicle（UAV）  composite wing UAV  piston engine  variable pitch propeller  ground testbench
    Author NameAffiliationE-mail
    GAN Yuantao* College of Aviation Engineering， Civil Aviation Flight University of China， Guanghan 618307， China gytao123@qq.com 
    FU Yaoming College of Aviation Engineering， Civil Aviation Flight University of China， Guanghan 618307， China ymfo@163.com 
    PENG Xu Institute of Electronic and Electrical Engineering， Civil Aviation Flight University of China， Guanghan 618307， China  
    YE Yuxiang College of Aviation Engineering， Civil Aviation Flight University of China， Guanghan 618307， China 1422397135@qq.com 
    AN Siqi* Institute of Electronic and Electrical Engineering， Civil Aviation Flight University of China， Guanghan 618307， China ansiqi@cafuc.edu.cn 
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    Abstract:In order to improve the logistics transportation capabilities of composite wing unmanned aerial vehicle（UAV）， a design methodology for the overall layout and power propulsion system of a hybrid wing UAV was proposed to enhance its vertical flight performance and extend hover duration. Furthermore， successful development of an engineering prototype and an adaptive ground platform was achieved. In accordance with the specific task requirements， the structure of a series direct drive hybrid power system was designed and the power output mode was formulated. Considering structural constraints such as wing load and thrust-to-weight ratio， an estimation method for take-off weight and wing size in fixed-wing mode was provided. The USA-35B airfoil suitable for low-speed flight was selected using the Profili software. Simultaneously， selection methods for rotors and variable pitch propellers were discussed， and the optimal cruise blade angle was determined through ground testing. The feasibility of the power system， electric transmission system， and mechanical structure was validated through simulation experiments and ground tests. Following prototype test flight verification， the designed composite wing UAV demonstrates a hover time of 24 min， exhibiting significantly improved vertical flight performance compared to industry standards.
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