TY - GEN
T1 - Transition Flight Control of A Small Unmanned Tilt Rotor Aircraft with Distributed Electric Propulsion
AU - Zhao, Qingfeng
AU - Zhou, Zhou
AU - Dong, Qiyuan
N1 - Publisher Copyright:
© 2023, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.
PY - 2023
Y1 - 2023
N2 - Tilt rotor aircraft is a type that has gained wide attention and developed quickly in recent years, combining the advantages of rotorcraft and fixed-wing aircraft, such as vertical takeoff/landing ability and high-speed cruise. An extended dynamics equation, based on six degree-of-freedom (6-DOF), is proposed in this paper, to solve the problem of inertial properties dynamic behavior during transition. Then, the transition corridor is calculated considering force and torque balance based on nonlinear programming. Last, the study focuses on the transition flight of the tilt rotor aircraft with distributed propulsion, which is nonlinear, strongly coupled and uncertain. And due to the significant change in dynamic characteristics, the error in the aerodynamic calculations and the strong external interference. An attitude controller is designed, by Active Disturbance Rejection Control (ADRC) method, as an inner loop control demonstrating excellent dynamic suppression performance. Overall, distributed electric propulsion not only presents unique control challenges, but also provides new solutions for transition flight control. This paper focuses on new properties brought by distributed propulsion to the transition envelope. Furthermore, a robust control method is designed, which may be a new research approach to the tilt rotor aircraft with distributed electric propulsion.
AB - Tilt rotor aircraft is a type that has gained wide attention and developed quickly in recent years, combining the advantages of rotorcraft and fixed-wing aircraft, such as vertical takeoff/landing ability and high-speed cruise. An extended dynamics equation, based on six degree-of-freedom (6-DOF), is proposed in this paper, to solve the problem of inertial properties dynamic behavior during transition. Then, the transition corridor is calculated considering force and torque balance based on nonlinear programming. Last, the study focuses on the transition flight of the tilt rotor aircraft with distributed propulsion, which is nonlinear, strongly coupled and uncertain. And due to the significant change in dynamic characteristics, the error in the aerodynamic calculations and the strong external interference. An attitude controller is designed, by Active Disturbance Rejection Control (ADRC) method, as an inner loop control demonstrating excellent dynamic suppression performance. Overall, distributed electric propulsion not only presents unique control challenges, but also provides new solutions for transition flight control. This paper focuses on new properties brought by distributed propulsion to the transition envelope. Furthermore, a robust control method is designed, which may be a new research approach to the tilt rotor aircraft with distributed electric propulsion.
KW - Active disturbance rejection controller (ADRC)
KW - Distributed electric propulsion
KW - Transition corridor
KW - Transition flight control
KW - Unmanned tilt rotor aircraft
UR - http://www.scopus.com/inward/record.url?scp=85140449190&partnerID=8YFLogxK
U2 - 10.1007/978-981-19-2635-8_29
DO - 10.1007/978-981-19-2635-8_29
M3 - 会议稿件
AN - SCOPUS:85140449190
SN - 9789811926341
T3 - Lecture Notes in Electrical Engineering
SP - 395
EP - 409
BT - The Proceedings of the 2021 Asia-Pacific International Symposium on Aerospace Technology APISAT 2021, Volume 2
A2 - Lee, Sangchul
A2 - Han, Cheolheui
A2 - Choi, Jeong-Yeol
A2 - Kim, Seungkeun
A2 - Kim, Jeong Ho
PB - Springer Science and Business Media Deutschland GmbH
T2 - Asia-Pacific International Symposium on Aerospace Technology, APISAT 2021
Y2 - 15 November 2021 through 17 November 2021
ER -