Abstract:

To implement the interception of a maneuvering target for a skid-to-turn (STT) missile, a three-dimensional partial integrated guidance and control (PIGC) with impact angle constraints is developed based on the adaptive terminal sliding mode dynamic surface control. Firstly, the PIGC model with strict-feedback form of an STT missile is established without the information of the missile velocity derivatives vector along the body frame. Then, the PIGC design is proposed based on the dynamic surface control procedure for the design model. Based on terminal sliding mode theory, the error vector of the method is constructed as the terminal sliding surface and used in the design of the virtual control law to guarantee the precise interception with the impact angle constraints. The nonlinear extended state observers (ESO) with finite time convergence are introduced to estimate the uncertainties in system. Additionally, the adaptive operators are designed to compensate the estimate errors of ESO to increase the robustness against uncertainties. Fiually, simulation results demonstrate the effectiveness of the proposed method.

Key words:  Partial integrated guidance and control (PIGC), Impact angle constraint, Dynamic surface control (DSC), Sliding mode control (SMC), Extended state observer (ESO), Adaptive control