Modeling and control of a quadrotor tail-sitter unmanned aerial vehicles. (March 2022)

• Record Type: Journal Article
• Authors: Xin, Hongbo; Wang, Yujie; Gao, Xianzhong; Chen, Qingyang; Zhu, Bingjie; Wang, Jianfeng; Hou, Zhongxi
• Is Part Of: Proceedings of the Institution of Mechanical Engineers. Volume 236:Number 3(2022)
• Page Start: 443
• Page End: 457
• Publication Date: 2022-03
• Subjects: Unmanned aerial vehicles -- vertical take-off and landing -- quadrotor tail-sitter -- flight mode transition -- simulation in MATLAB/Simulink -- flight test; Mechanical engineering -- Periodicals; Automatic control -- Periodicals; Systems engineering -- Periodicals; 621.3
• DOI: 10.1177/09596518211050466
• Languages: English
• ISSNs: 0959-6518

Abstract

The tail-sitter unmanned aerial vehicles have the advantages of multi-rotors and fixed-wing aircrafts, such as vertical takeoff and landing, long endurance and high-speed cruise. These make the tail-sitter unmanned aerial vehicle capable for special tasks in complex environments. In this article, we present the modeling and the control system design for a quadrotor tail-sitter unmanned aerial vehicle whose main structure consists of a traditional quadrotor with four wings fixed on the four rotor arms. The key point of the control system is the transition process between hover flight mode and level flight mode. However, the normal Euler angle representation cannot tackle both of the hover and level flight modes because of the singularity when pitch angle tends to± 90 ° . The dual-Euler method using two Euler-angle representations in two body-fixed coordinate frames is presented to couple with this problem, which gives continuous attitude representation throughout the whole flight envelope. The control system is divided into hover and level controllers to adapt to the two different flight modes. The nonlinear dynamic inverse method is employed to realize fuselage rotation and attitude stabilization. In guidance control, the vector field method is used in level flight guidance logic, and the quadrotor guidance method is used in hover flight mode. The framework of the whole system is established by MATLAB and Simulink, and the effectiveness of the guidance and control algorithms are verified by simulation. Finally, the flight test of the prototype shows the feasibility of the whole system.