A new reusable launch vehicle (RLV) entry guidance algorithm with ranging technique which only needs to update flight profile parameters was developed and a predictor-corrector entry guidance methodology using Runge-Kutta-Fehlberg method for RLVs combined with trajectory online generation technology was studied. Comparisons between the two guidance schemes were performed, and simulation results show that the two guidance methods are feasible, which indicates that the integration of reference-trajectory entry guidance and predictor-corrector entry guidance is a promising entry guidance scheme for future RLVs.