A prediction correcting guidance method of a
deep space exploration returning process comprises the steps that (1) a heeling angle section used for
deep space exploration returning process track prediction is determined; (2) the amplitude value | sigma 0 | of the heeling angle of a
current point is computed in an iterative mode; (3) a salutatory reentry
flight track of a returning device is divided into an initial reentry stage, a primary reentry descending stage, a primary reentry ascending stage, a Kepler stage and a final reentry stage, a final guidance rule of the returning device is determined, and the final guidance rule is that when the returning device is in the initial reentry stage or the primary reentry descending stage or the primary reentry ascending stage or the final reentry stage, the amplitude value | sigma 0 | determined in the step (2) of the heeling angle sigma 0 of the
current point is used for guidance; and when the returning device is in the Kepler stage, | sigma 0 | = 180 degrees is used for guidance, and accordingly prediction correcting guidance of the
deep space exploration returning process is completed. The guidance rule is designed at the Kepler stage of the track for achieving overload restrain on the deep
space exploration returning process, and safe and accurate landing of the returning device is guaranteed.