Abstract: In order to establish an accurate model of the all electric propulsion satellite, design an attitude orbit control method and improve the satellite control accuracy, the dynamics modeling of the all electric propulsion satellite with deployable thruster point assembly mechanism (TPAM) is studied. The model of the four joint deployable TPAM is established, and the electric thrust and torque models based on the configuration of TPAM are derived. On this basis, the attitude orbit dynamics equation of the satellite is established. The model can be used to describe the attitude motion state and orbit change of the all electric propulsion satellite, which can accurately reflect the motion performance of the satellite. The model has been applied in the development of the APSTAR 6E satellite. The simulation results show that the dynamic simulation results of all electric propulsion satellite via the model accord with the test and analysis results, and the control effect of the APSTAR 6E in orbit is consistent with the expectation, which verifies the validity of the model.

Key words: all electric propulsion, thruster point assembly mechanism, dynamic model, APSTAR6E