Abstract: Aiming at the problem that the coupling characteristics of guidance and attitude loops of high-speed morphing wing aircraft are strong and difficult to separate and design, an Integrated Guidance and Control(IGC) method considering the morphing characteristics is designed based on Backstepping Method and Fixed-Time Sliding Mode Control meth-od. Firstly, a six-degree-of-freedom complete kinematic model of the aircraft under morphing conditions is established, and a strict feedback form of the integrated guidance and control (IGC) model with additional deformation terms is derived. Secondly, a novel integrated design method for guidance and control is proposed using Backstepping Method (BM) combined with Fixed-Time Sliding Mode Control (FTSMC), and the stability of the system is proved by Lyapunov theory. Finally, the comparison between the traditional method and the new integrated design method is carried out without morphing case, which verifies the rapidity and effectiveness of the new method; the comparison of the new method is carried out with and without morphing, which verifies the superiority of the integrated design of guidance and control in the morphing case.

Key words: high-speed morphing wing aircraft, integrated guidance and control, backstepping control, Fixed-time sliding mode control, standard trajectory tracking