TY - JOUR
T1 - 大跨域条件下的自适应滚转稳定容错控制方法
AU - Wang, Yuchen
AU - Lin, Defu
AU - Wang, Wei
AU - Ji, Yi
N1 - Publisher Copyright:
© 2021, Beihang University Aerospace Knowledge Press. All right reserved.
PY - 2021/3/25
Y1 - 2021/3/25
N2 - During the phase of large span flight, aerodynamic parameters of guided-munitions have a large-amplitude high-frequency nonlinear chattering accompanied by varying velocity, altitude and angle of attack, adversely affecting the roll stability. Moreover, the failure and time-lag features of the actuator increase the difficulty in roll stability control. To address these problems, this paper proposes a robust adaptive fault-tolerant roll stability control method. A mathematical model of the roll channel considering the actuator fault is first established. Taking the nonlinear term and model uncertainties as external disturbances, a robust roll stability control method based on the adaptive sliding mode control theory is then presented to compensate the severe influence resulted from the nonlinear term and actuator fault. Additionally, the actuator time-lag is considered and the backstepping method implemented to suppress the actuator lag and increase the roll response speed. Simulation results show strong robustness of the proposed control method in aerodynamic disturbances and fault handling.
AB - During the phase of large span flight, aerodynamic parameters of guided-munitions have a large-amplitude high-frequency nonlinear chattering accompanied by varying velocity, altitude and angle of attack, adversely affecting the roll stability. Moreover, the failure and time-lag features of the actuator increase the difficulty in roll stability control. To address these problems, this paper proposes a robust adaptive fault-tolerant roll stability control method. A mathematical model of the roll channel considering the actuator fault is first established. Taking the nonlinear term and model uncertainties as external disturbances, a robust roll stability control method based on the adaptive sliding mode control theory is then presented to compensate the severe influence resulted from the nonlinear term and actuator fault. Additionally, the actuator time-lag is considered and the backstepping method implemented to suppress the actuator lag and increase the roll response speed. Simulation results show strong robustness of the proposed control method in aerodynamic disturbances and fault handling.
KW - Actuator dynamic lag
KW - Actuator faults
KW - Adaptive sliding mode control
KW - Backstepping technique
KW - Guided-munition
KW - Roll stability
UR - http://www.scopus.com/inward/record.url?scp=85103936489&partnerID=8YFLogxK
U2 - 10.7527/S1000-6893.2020.24368
DO - 10.7527/S1000-6893.2020.24368
M3 - 文章
AN - SCOPUS:85103936489
SN - 1000-6893
VL - 42
JO - Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica
JF - Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica
IS - 3
M1 - 324368
ER -