Torque model verification for the GOCE satellite

摘要: Abstract The modeling of torques acting on satellites is essential for the design satellite attitude control systems. GOCE satellite, equipped with accurate accelerometers, star trackers and GPS receivers, presents an opportunity to validate these models. Although forces other accelerometer-carrying missions have been extensively analyzed in past, a similar analysis has so far not yet made torques. In this paper, we present set torque models satellite. It consists six main parts: (1) magnetic torquer actuators, (2) aerodynamic torque, (3) gravity gradient (4) solar radiation pressure (5) thruster (6) passive torque. properties payload are approximated using parametrization, which parameters estimated from observation data. Based data recorded during selected spacecraft events, model can be validated error sources identified perform best roll pitch, where standard deviation reduced 15.2% 2.1% around those axes respectively. yaw significantly larger at 30.5%. remaining differences between observations show signatures due electric currents errors. latter correspond well increase thermosphere density wind speed increased geomagnetic activity. pitch found potential source vertical