Integrated Guidance and Control Method for the Interception of Hypersonic Vehicle Based on High-Order Sliding Mode Approach

This paper focuses on the integrated guidance and control (IGC) method applied in the interception of maneuvering near space hypersonic vehicles using the homogeneous high order sliding mode (HOSM) approach. The IGC model is derived by combining the target-missile relative motion and dynamic equations. Then, a fourth order sliding mode controller is implemented in the augmented IGC model, To estimate the high order differentiate of the sliding manifold which is required in the HOSM method, an arbitrary order robust exact differentiator is present. At last, the idea of virtual control is introduced to alleviate the chattering of the control input without using any saturation functions which may lead to a loss of the robustness. And the stability of the fourth order homogeneous HOSM controller is also proved theoretically. Finally, simulation results are provided and analyzed to demonstrate the effectiveness of the proposed method in three typical engagement scenarios.