火箭上升段滚动时域制导控制一体化设计

A method of receding horizon integrated guidance and control (IGC) based on the convex optimization for rockets in the ascent phase is proposed for that the traditional separation design of the guidance and attitude control systems cannot achieve the optimal performance of the overall system. Firstly, the IGC model reflecting the coupling between the guidance and control loops is established and linearized by the feedback linearization. Then, the ascent IGC problem is modeled as an optimal control problem. A receding horizon controller based on the convex optimization theory is designed. The method can make up for the uncertainty caused by the model error and external interference timely based on the idea of feedback correction and receding horizon optimization of the receding horizon control (RHC) strategy. Meanwhile, the complex optimization problem with the control constraints can be solved effectively based on the advantages of low computational complexity and simple solution of convex optimization algorithm. The closed-loop stability of the IGC system is proved based on the Lyapunov stability theory. The numerical simulation verifies the effectiveness and robustness of the proposed method. And the simulation results show that the IGC design has higher guidance precision, smaller control requirements and smoother attitude angle change than the traditional separation design.