Coupling effect-triggered control strategy for hypersonic flight vehicles with finite-time convergence
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This paper investigates a novel control strategy of addressing coupling issue for attitude tracking control of hypersonic flight vehicle. By using a defined coupling effect indicator which demonstrates whether a coupling harms or benefits the system, one finite-time coupling effect-triggered control scheme is proposed via applying the second-order sliding mode control technique. A specific nonlinear function is designed to implement the addition of beneficial couplings or removal of detrimental couplings. As a consequence, the proposed method establishes a unified couplings recognition and coupling effect-triggered control framework, which leads to a potential of improving the dynamic performance. The chattering attenuation is also involved for practical implementation. Finally, simulation results illustrate the validity of the proposed control scheme.
KeywordsCoupling effect Sliding mode Attitude control Hypersonic flight vehicles
The authors would like to greatly appreciate the editor and all the anonymous reviewers for their comments, which helped to improve the quality of this paper. This work was supported by National Natural Science Foundation of China under Grants 61803308 and 61703339.
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Conflict of interest
No potential conflict of interest was reported by the authors.
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