Predictor-Corrector Reentry Guidance of Hypersonic Gliding Vehicle Satisfying No-Fly Zone Constraints with High Terminal State Accuracy

For the reentry guidance of hypersonic gliding vehicles, a new predictor-corrector guidance method is proposed based on the quasi-equilibrium gliding condition, which can avoid no-fly zones and possess high terminal state accuracy. In the longitudinal guidance, according to the reentry downrange error, the magnitude of the bank angle is obtained by a predictor-corrector approach. In order to eliminate large phugoid oscillations, a new reference altitude change rate is applied to the guidance scheme. The path constraints are transformed into the constraints on the bank angle. A proportional differential regulator for the normal overload is proposed, which can be used to modify the angle of attack to achieve accurate terminal attitude. In the lateral guidance, considering the target, a lateral guidance law is designed to avoid no-fly zones and eliminate the lateral error. Finally, simulation results demonstrate that the guidance method not only possesses high accuracy but also is robust enough under disturbance conditions, with all the path constraints are enforced.