Abstract: When GEO satellite is used in a navigation constellation, its prediction orbit must be determined during the orbit maneuver. Two strategies which include constructing dynamic thrust model and estimating the parameter in short-arc are mainly used to solve this problem. The piecewise linear acceleration model and instantaneous velocity changes (pulse) model are used for GEO orbit determination and orbit prediction at maneuver time, and their applicability are evaluated, also their advantage and disadvantage for orbit determination and prediction are compared with short-arc strategy. It showed that instantaneous velocity changes acceleration model is superiority to the piecewise linear acceleration model for determining the maneuver orbit. These two kinds of dynamic model method can fit the maneuver track of one day with an error no more than 5m, but orbit prediction accuracy of the piecewise linear model is inferiority to the short-arc strategy and the pulse acceleration model. The accuracy of maneuver orbit determination can be improved by combining the C band transfer observation with L band observation.