ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Integrated guidance and control design based on fully actuated system method
Received date: 2023-04-20
Revised date: 2023-05-17
Accepted date: 2023-06-15
Online published: 2023-06-27
Supported by
National Natural Science Foundation of China(52272358)
Aiming at the problem of high frequency oscillation of instantaneous overload of high maneuvering target and uncertain time-varying of line-of-sight angle at the end of guidance， an integrated design scheme of guidance and control based on fully actuated system and backstepping method is proposed in this paper. Firstly， considering the maneuvering characteristics of the target， a second-order strict feedback guidance and control integrated nonlinear model is established， which eliminates the intermediate process quantity， simplifies the modeling and calculation process， and designs a reduced-order state observer to estimate and compensate the system disturbance. Secondly， under the framework of backstepping method， combined with the high-order fully actuated system method， the guidance control law with interception angle constraint is designed. Finally， the pole assignment method is used to obtain the control coefficient matrix of the closed-loop system， and the Lyapunov function is introduced to prove the stability of the system. The effectiveness， superiority and robustness of the designed guidance and control integration scheme are proved by different scenarios and comparative simulation experiments.
Hongyan ZHANG , Wei WANG , Shiwei CHEN , Yi JI , Jiaqi LIU . Integrated guidance and control design based on fully actuated system method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2024 , 45(1) : 628891 -628891 . DOI: 10.7527/S1000-6893.2023.28891
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