A propellant budge-based low orbit elliptic track satellite successful injection determining method is provided. Through acquisition of relationships between propellant waste and apogee, perigee, eccentricity ratio and inclination angle adjustment amount, an injection success determination formula containing the apogee, perigee, eccentricity ratio and inclination angle adjustment amount can be achieved via total propellant waste provided by satellite orbital transferring; primary orbital transferring propellant amount allowed by a satellite can be determined according to limitations of each party; the apogee, perigee, eccentricity ratio and inclination angle deviation value of the satellite can be determined after separation of the satellite and a rocket; and whether the satellite successfully enters an orbit is determined via the determination formula. An orbital maneuver theory and formula are employed to achieve an analytic calculation formula, so accuracy, rationality, simplicity and high efficiency can be achieved; easy operation is provided and the method is in particular suitable for quick determination of success carry launch; and basis and instruction are provided for implements of emergency measures of the satellite upon problems during the carrying launch.