An integrity monitoring framework for highly non-linear high dynamic space launch vehicle motion system is presented. The structure for outlier detection and exclusion from faulty measurement sets is designed for the integrity monitoring based on greedy search algorithm. The extended Kalman filter is adopted for state estimation of the space launch vehicle dynamic system. The simulation is performed using the global navigation satellite system (GNSS) pseudorange measurements obtained from the dynamic second order differential equation of space launch vehicle motion. The performance of the integrity monitoring is verified by demonstrating the probability of bias detection analysis.