TY - GEN
T1 - Robust Attitude Control of Multibody Aircraft with Preview-Based Control Compensation
AU - Qi, Pengyuan
AU - Li, Qingxian
AU - Mou, Quanrun
AU - Wang, Yinan
N1 - Publisher Copyright:
© 2024, Chinese Society of Aeronautics and Astronautics.
PY - 2024
Y1 - 2024
N2 - This paper investigates the robust attitude control for wingtip-connected multibody aircraft, using preview-based control compensation mechanism to address the issues of inherent wingtip couplings. A constrained multibody dynamics model is first derived to obtain the nonlinear and linearised formulations for multibody aircraft. The H∞ control is employed to synthesize the pitch angle and forward velocity controller in the longitudinal channel, while the H∞ preview control is employed to synthesize the roll angle and yaw rate controller in the lateral channel. The preview control scheme enables the usage of future reference commands as feedforward information to synthesize appropriate control compensation to reduce the impact of wingtip couplings between adjacent aircraft units. Simulation studies conducted based on the nonlinear model show that the preview-based H∞ control system is able to achieve better control effectiveness and disturbance rejection performance, compared to the baseline regular H∞ control system without preview. These demonstrate that the mechanism of control compensation can greatly benefit the flight control of multibody aircraft.
AB - This paper investigates the robust attitude control for wingtip-connected multibody aircraft, using preview-based control compensation mechanism to address the issues of inherent wingtip couplings. A constrained multibody dynamics model is first derived to obtain the nonlinear and linearised formulations for multibody aircraft. The H∞ control is employed to synthesize the pitch angle and forward velocity controller in the longitudinal channel, while the H∞ preview control is employed to synthesize the roll angle and yaw rate controller in the lateral channel. The preview control scheme enables the usage of future reference commands as feedforward information to synthesize appropriate control compensation to reduce the impact of wingtip couplings between adjacent aircraft units. Simulation studies conducted based on the nonlinear model show that the preview-based H∞ control system is able to achieve better control effectiveness and disturbance rejection performance, compared to the baseline regular H∞ control system without preview. These demonstrate that the mechanism of control compensation can greatly benefit the flight control of multibody aircraft.
UR - https://www.scopus.com/pages/publications/85180740357
U2 - 10.1007/978-981-99-8867-9_61
DO - 10.1007/978-981-99-8867-9_61
M3 - 会议稿件
AN - SCOPUS:85180740357
SN - 9789819988662
T3 - Lecture Notes in Mechanical Engineering
SP - 637
EP - 648
BT - Proceedings of the 6th China Aeronautical Science and Technology Conference - Volume 3
PB - Springer Science and Business Media Deutschland GmbH
T2 - 6th China Aeronautical Science and Technology Conference, CASTC 2023
Y2 - 26 September 2023 through 27 September 2023
ER -