A new entry guidance method combined predictor-corrector guidance and reference trajectory guidance was proposed for reducing calculated amount in predictor corrector entry guidance. Predictor-corrector guidance was applied in initial entry phase to improve robustness, and reference trajectory guidance was applied in second entry phase to reduce calculated amount. Through the information of reference trajectory, it was less time consumed in predicting. The method with a new command fast iterative algorithm was designed to reduce the iterative times. The reference command profile was revised according to actual condition of lunar capsule in transfer position so as to compensate error and to improve the quality of the second entry guidance performance. Numerical simulation results demonstrate that the combined entry guidance method is able to lessen time in predicting and fasten correction, and it has the characteristics of high precision and robustness.