The invention relates to a method for selecting time of deep space probe approach orbit correction maneuver, which belongs to the field of spaceflight and aviation and solves the problems of deep space probe approach orbit correction maneuvering time including low control precision, great calculation amount and poor independency in the prior method for selecting time of deep space probe approach section orbit correction maneuver. The method comprises: 1, determining miss distance rhof passing through the B plane of an object celestial body; 2, determining the acceptable maximum miss distance rhomax of a deep space probe; 3, judging whether the miss distance rhof is more than the acceptable maximum miss distance rhomax, if yes, executing step 4; otherwise, returning to step 1; and 4, executing deep space probe approach section orbit correction maneuver. The method not only can save fuel at a rate of 6m/s, but also can ensure that final passing-through precision is increased by more than 100m as compared with ground station designated maneuver time precision under the same condition and reaches within 250m.