BDS System GEO Satellite Orbit Maneuver Detection And Maneuver Orbit Fast Recovery Performance Analysis

High-precision statistical orbit determination not only requires high-precision ranging data,but also relies on accurate dynamics models.However,during the orbital maneuver,the magnitude and direction of the maneuvering force received by the satellite is unknown,and it is difficult for the ground monitoring center to model the maneuvering force.Therefore,the dynamics method cannot effectively complete the orbit determination task during the orbital maneuver.As an important part of the Beidou satellite navigation system,GEO satellites have the most frequent maneuvers due to their static characteristics,which affects the continuity of satellite navigation services.Therefore,in order to enable GEO satellites to provide better navigation services to users,we must accurately identify the start time of orbital maneuvers,and quickly restore the orbit to a usable state after the end of the maneuver.This paper mainly studies the performance of BDS GEO satellite orbit maneuvering start time detection and orbit recovery after maneuvering,mainly including the following aspects:1.Analyze the influence of natural perturbation power and maneuverability on satellite orbit.The experimental analysis results of the simulation data show that when the 7×7-order gravity field model is adopted,the single-day orbit integral reaches the millimeter level,which can meet the needs of precise orbit determination;the influence of the earth tide and ocean tide on the orbit is maintained at the centimeter and millimeter level.In terms of the accuracy of broadcast ephemeris,the impact of ocean tides can be ignored;the gravity of the sun and the moon and the pressure of sunlight on the orbit reach the order of 100 meters and ten meters respectively;under the action of mechanical power,the orbit of the satellite will quickly deviate from the original position.The directional forecast accuracy error exceeds 10 KM,and its influence exceeds the sum of the natural perturbation force.2.Using the orbital maneuvering time detection factor and the robust weight matrix,based on the broadcast ephemeris pseudorange observations,the detection of the start time of the orbital maneuvering of the BDS GEO satellite is realized.Before maneuver detection,this article first analyzes the rationality of the threshold selection and the effectiveness of the robust weight matrix.The experimental analysis shows that when the three times the error of the pseudorange residual is used as the threshold to detect maneuver,the confidence level is as high as 99.74%,and the resistance is as high as 99.74%.The difference weight matrix can effectively resist the influence of mobile satellites and accurately calculate the receiver clock error.Based on the above analysis of the reliability of the detection method,this paper adopts the ground measurement data to carry out the orbital maneuver.The detection results show that the start time of the detection maneuver is consistent with the time when the single point positioning of the station deviates from a reasonable value,which shows the accuracy of this method.Finally,this paper uses simulation data for experimental analysis,and demonstrates the applicability of this method under the action of different forms of mechanical power.3.Using the short-arc kinematics orbit determination method based on polynomial fitting,the orbit determination accuracy of different orbit determination arc lengths under the condition of obtaining the satellite clock error information is studied,which solves the problem of the BDS GEO satellite during the recovery of the maneuvering orbit to a certain extent.The problem of orbit determination.In order to analyze the method of obtaining satellite clock error during orbit restoration,this paper analyzes the frequency stability of satellite atomic clock and the prediction accuracy of satellite clock error.The results show that the linear model for clock error prediction during orbit restoration can achieve better accuracy.The prediction accuracy is-0.601 ns,which can meet the orbit determination accuracy requirements during orbit recovery.After determining the prediction method of the satellite clock error during the orbit recovery period,this article performs orbit recovery based on the measured data.The results show that when the satellite clock error is calculated as an unknown parameter,the satellite orbits determined by different arc lengths cannot meet the needs of the RDSS service;When the satellite clock error uses the predicted value and the orbit determination arc length is 10 minutes,the difference between the orbit provided by the broadcast ephemeris is within10 m,and its accuracy can meet the positioning needs of ground users.Finally,this paper uses simulation data for orbit determination analysis,and the results show that the short-arc kinematics orbit determination based on polynomial fitting can be applied to orbit recovery under different motor forces,and the orbit recovery results are mainly affected by the observation quality of the ground tracking station.It has nothing to do with the form of power.