TY - JOUR
T1 - Design and implementation of a hardware-in-the-loop simulation platform for a tail-sitter UAV
AU - Zou, Xu
AU - Liu, Zhenbao
AU - Zhao, Wen
AU - Wang, Lina
N1 - Publisher Copyright:
© 2023, Emerald Publishing Limited.
PY - 2023/5/2
Y1 - 2023/5/2
N2 - Purpose: A high-fidelity simulation platform helps to verify the feasibility of the controller and reduce the cost of subsequent experiments. Therefore, this paper aims to design a high-fidelity hardware-in-the-loop (HIL) simulation platform for the tail-sitter vehicles. Design/methodology/approach: The component breakdown approach is used to develop a more reliable model. Thruster dynamics and ground contact force are also modeled. Accurate aerodynamic coefficients are obtained through wind tunnel tests. This simulation system adopts a mode transition method to achieve continuous simulation for all flight modes. Findings: Simulation results are in good agreement with the flight log and successfully predict the state of the vehicle. Originality/value: First, the effects of the propeller slipstream are considered. Second, most researchers ignore the parasitic drag caused by the landing gear and other appendages, which is discussed in this study. Third, a ground contact model is implemented to allow a realistic simulation of the takeoff and landing phases. Fourth, complete wind tunnel tests are conducted to obtain more accurate aerodynamic coefficients. Finally, a mode transition method is deployed in the HIL simulation system to achieve continuous simulation for all flight modes.
AB - Purpose: A high-fidelity simulation platform helps to verify the feasibility of the controller and reduce the cost of subsequent experiments. Therefore, this paper aims to design a high-fidelity hardware-in-the-loop (HIL) simulation platform for the tail-sitter vehicles. Design/methodology/approach: The component breakdown approach is used to develop a more reliable model. Thruster dynamics and ground contact force are also modeled. Accurate aerodynamic coefficients are obtained through wind tunnel tests. This simulation system adopts a mode transition method to achieve continuous simulation for all flight modes. Findings: Simulation results are in good agreement with the flight log and successfully predict the state of the vehicle. Originality/value: First, the effects of the propeller slipstream are considered. Second, most researchers ignore the parasitic drag caused by the landing gear and other appendages, which is discussed in this study. Third, a ground contact model is implemented to allow a realistic simulation of the takeoff and landing phases. Fourth, complete wind tunnel tests are conducted to obtain more accurate aerodynamic coefficients. Finally, a mode transition method is deployed in the HIL simulation system to achieve continuous simulation for all flight modes.
KW - Hardware-in-the-loop
KW - MATLAB
KW - Simulation
KW - UAV
KW - Unmanned aerial vehicle
KW - VTOL
UR - http://www.scopus.com/inward/record.url?scp=85148355623&partnerID=8YFLogxK
U2 - 10.1108/AEAT-10-2022-0293
DO - 10.1108/AEAT-10-2022-0293
M3 - 文章
AN - SCOPUS:85148355623
SN - 1748-8842
VL - 95
SP - 985
EP - 994
JO - Aircraft Engineering and Aerospace Technology
JF - Aircraft Engineering and Aerospace Technology
IS - 6
ER -