Application of Constant Thrust Maneuvering Model in Orbit-determinant and Prediction of Low Earth Orbit Satellites
Orbital maneuvering control is very common in in-orbit operations of low Earth orbit(LEO)satellites.Particularly,with the increasing popularity of electric propulsion technology in recent years,orbital maneuvering control has been widely used in LEO satellites,owing to its high specific impulse and stable thrust.Orbital maneuvering control will cause changes in the orbital parameters,and thus it is necessary to determine the post-control orbit by means of orbit-determination.However,traditional orbit-determination method does not consider the maneuver model,and requires measurement data without orbit control in a period of time.Since it is not possible to obtain enough measurement data within a short period of time,especially for electric propulsion satellites,the time of single maneuver is long,the control frequency is high,and the measurement data without orbit control is very limited,resulting in a large error in estimating the atmospheric drag coefficient.Therefore,the atmospheric drag coefficient is usually not estimated,and thus the forecast accuracy is relatively limited.In order to obtain more measurement data for orbit-determination,the frequency of orbit control is usually reduced,leading to longer and more frequent maneuver durations.In this context,a maneuver model is incorporated into the orbit determination process,considering the thrust magnitude and thrust direction of the thruster.By leveraging the measurement data during the control phase,this approach can simultaneously estimate the atmospheric parameters,the thruster thrust magnitude,and the thruster thrust direction.The least squares method is used to construct and solve the thruster perturbation model under maneuvering states,and the reliable orbit elements and atmospheric parameters are obtained.The actual global navigation satellite system(GNSS)data and orbital maneuvering verification show that the orbit-determination accuracy of the maneuvering model is basically consistent with that of the no-orbit-control phase,and more reliable atmospheric drag coefficients can be obtained due to the use of measurement data in a longer period of time.This ultimately enhances the prediction accuracy of LEO satellites under frequent maneuvers.
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维普
