TY - GEN
T1 - Design of Flight Control Law of Tilt-Rotor Aircraft Based on Incremental Nonlinear Dynamic Inversion
AU - Tang, Peng
AU - Liu, Shuna
AU - Zheng, Chen
N1 - Publisher Copyright:
© 2022, The Editor(s) (if applicable) and The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.
PY - 2022
Y1 - 2022
N2 - This paper presents a Hover Mode transition to Fast-Forward Mode flight control law of tilt-rotor UAV. A control law based on incremental nonlinear dynamic inversion is designed for tilt-rotor UAV, which has better robustness and lower model precision requirement compares to the nonlinear dynamic inversion control model. Firstly, the tilt-rotor UAV is introduced as experimental platform. In view of the redundancy of tilt-rotor aircraft, the control allocation algorithm of the control surface is designed, and the control of different kinds of control surfaces during the transition process is realized. Then, an incremental nonlinear dynamic inversion control law is derived based on the dynamic model of the tilt-rotor aircraft, which can be applied to different flight modes. Finally, simulation tests in hover mode to fast-forward mode show that the control law has good robustness and command tracking ability. In addition, sensitivity analysis of aerodynamic parameters provides us with some suggestions for adjusting the parameters in the actual flight test.
AB - This paper presents a Hover Mode transition to Fast-Forward Mode flight control law of tilt-rotor UAV. A control law based on incremental nonlinear dynamic inversion is designed for tilt-rotor UAV, which has better robustness and lower model precision requirement compares to the nonlinear dynamic inversion control model. Firstly, the tilt-rotor UAV is introduced as experimental platform. In view of the redundancy of tilt-rotor aircraft, the control allocation algorithm of the control surface is designed, and the control of different kinds of control surfaces during the transition process is realized. Then, an incremental nonlinear dynamic inversion control law is derived based on the dynamic model of the tilt-rotor aircraft, which can be applied to different flight modes. Finally, simulation tests in hover mode to fast-forward mode show that the control law has good robustness and command tracking ability. In addition, sensitivity analysis of aerodynamic parameters provides us with some suggestions for adjusting the parameters in the actual flight test.
KW - Flight control
KW - Incremental nonlinear dynamic inversion
KW - Simulation
UR - https://www.scopus.com/pages/publications/85120655808
U2 - 10.1007/978-981-15-8155-7_391
DO - 10.1007/978-981-15-8155-7_391
M3 - 会议稿件
AN - SCOPUS:85120655808
SN - 9789811581540
T3 - Lecture Notes in Electrical Engineering
SP - 4733
EP - 4746
BT - Advances in Guidance, Navigation and Control - Proceedings of 2020 International Conference on Guidance, Navigation and Control, ICGNC 2020
A2 - Yan, Liang
A2 - Duan, Haibin
A2 - Yu, Xiang
PB - Springer Science and Business Media Deutschland GmbH
T2 - International Conference on Guidance, Navigation and Control, ICGNC 2020
Y2 - 23 October 2020 through 25 October 2020
ER -