This study presents a novel integrated guidance and control method for near space interceptor, considering the coupling among\ndifferent channels of the missile dynamics, which makes the most of the overall performance of guidance and control system.\nInitially, three-dimensional integrated guidance and control model is employed by combining the interceptor-target relative motion\nmodel with the nonlinear dynamics of the interceptor, which establishes a direct relationship between the interceptor-target relative\nmotion and the deflections of aerodynamic fins. Subsequently, regarding the acceleration of the target as bounded uncertainty of the\nsystem, an integrated guidance and control algorithm is designed based on robust adaptive backstepping method, with the upper\nbound of the uncertainties unknown.Moreover, a nonlinear tracking differentiator is introduced to reduce the ââ?¬Å?compute explosionââ?¬Â\ncaused by backstepping method. It is proved that tracking errors of the state and the upper bound of the uncertainties converge to\nthe neighborhoods of the origin exponentially. Finally, simulations results show that, compared to the conventional guidance and\ncontrol design, the algorithm proposed in this paper has greater advantages in miss distance, required normal overload, and flight\nstability, especially when attacking high-maneuvering targets.
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