SINS/CNS/GNSS integrated navigation scheme for advanced upper stage

Abstract

A SINS/CNS/GNSS integrated navigation scheme is researched for advanced upper stage in this paper. First of all, the composition of the integrated navigation is introduced. Then, the error model of the integration system in launch inertial frame was established. especially the misalignments of star tracker are inputted as system states, and also the federated filter algorithm is used to estimate the state errors of the integrated navigation system. Finally, simulations results show that the SINS/CNS/GNSS integrated navigation can provide navigation parameters with high accuracy, which can meet the accuracy requirements of advanced upper stage.