Real-Time Multi-Constraint Guidance for Near Space Flight Vehicle Using Adaptive Gauss Pseudo-Spectral Optimization

For the interception of a high-speed target in the near space, the optimal midcourse guidance of air-to-air missile is designed. The relative motion model of the missile and target in three-dimensional space is established, and the optimal midcourse guidance problem is formulated as an optimal control problem with constraints where the energy consumption is chosen as the performance index. With the state and control of the system discretized using Gauss pseudo-spectral method, the optimal control problem is formulated into a nonlinear programming problem (NLP)which can be solved to obtain open-loop optimal guidance commands. Then, in the receding horizon architecture, the NLP problem corresponding to the certain time horizon is repeatedly solved on line to implement the closed-loop guidance. The stability is proved for the closed-loop guidance system with the existence of external disturbances, model parameter uncertainties, and computational errors. Finally, numerical simulation is carried out to verify the feasibility of the design.