On Predictor-Corrector Guidance of Hypersonic Vehicle in Glide Segment

We use predictor-corrector guidance to solve the problem of excess energy in the glide phase of hypersonic vehicles. We only consider the 3-D model, the process constraints and terminal window conditions are given. We use the fast integration method to continuously predict the terminal error during the flight, and correct the guidance command in a certain period. On the basis of the quasi-equilibrium condition, an on-line trajectory updating method is given, which converts the predicted parameters into a parameter of nominal bank angle. The nominal angle of attack profile, transverse corridor and trajectory tracking control system are also designed. And We built a simulation platform with MATLAB and verified it. The results show that the method is reliable and effective. It can guide the aircraft to the terminal window smoothly under the condition of meeting the process constraints, and the terminal accuracy is high. It can meet the terminal state constraints within the tolerable range.