The invention relates to a method for analyzing influences of initial localization and orientation errors of a long-range rocket and aims to solve the problem that existing estimation precision is not high. According to the technical scheme, the method comprises steps as follows: step 1, establishing a navigation perturbation equation when coupling of apparent acceleration is considered; step 2, a gravitational acceleration-position partial derivative matrix, apparent acceleration projection deviation, apparent acceleration coupling deviation, initial speed errors and initial position errors are solved according to the navigation perturbation equipment obtained in the step 1 when coupling of apparent acceleration is considered; step 3, approximate analytical solutions of burnout time position deviation and speed deviation and approximate analytical solutions of impact point longitudinal deviation and transverse deviation caused by initial localization and orientation errors of the long-range rocket when coupling of the apparent acceleration is considered are obtained. The method is used for the field of space technology.