ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Integrated guidance and control method for high-speed morphing wing aircraft
Received date: 2024-05-16
Revised date: 2024-06-06
Accepted date: 2024-07-03
Online published: 2024-07-08
Supported by
National Natural Science Foundation of China(92371203)
The guidance and attitude loops of high-speed morphing wing aircraft has strong coupling characteristics， and are difficult to separate and design. In this paper， an Integrated Guidance and Control （IGC） method considering morphing characteristics is designed based on the Backstepping Method and the Fixed-Time Sliding Mode Control （FTSMC） method. Firstly， a six-degree-of-freedom complete kinematic model of the aircraft under morphing conditions is established， and a strict feedback form of the IGC model with additional deformation terms is derived. Secondly， a novel integrated design method for guidance and control is proposed using the Backstepping Method （BM） combined with FTSMC， and the stability of the system is proved by the Lyapunov theory. Finally， comparison between the traditional method and the new integrated design method is carried out in the case without morphing， which verifies the rapidity and effectiveness of the new method. Comparison of the new method with and without morphing is carried out， which verifies the superiority of the new method in the case with morphing.
Hao HE , Peng WANG . Integrated guidance and control method for high-speed morphing wing aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2024 , 45(S1) : 730692 -730692 . DOI: 10.7527/S1000-6893.2024.30692
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