1) Key Laboratory of Dynamic Geodesy, Institute of Geodesy and Geophysics, CAS, Wuhan 430077 2) Disaster Prevention Research Institute, Kyoto University, Uji, Kyoto 611-0011, Japan 3) Department of Applied Physics, Wuhan University of Science and Technology, Wuhan 430081 4) Shanghai Astronomical Observatory, CAS, Shanghai 200030
Abstract The optimal selection of orbital parameters in the future ImprovedGRACE satellite gravity measurement mission in China is carried out by using the combined model of cumulative geoid height errors influenced by the intersatellite rangerate error of interferometric laser ranging system, orbital position and velocity errors of GPS receiver and nonconservative force error of accelerometer based on the improved semianalytic method. The simulated results show as follows.Firstly, at degree 300, cumulative geoid height error is 3.993×10 -1 m at 350 km orbital altitude, the accuracies are improved respectively 8.770 times and 77.145 times at 300 km and 250 km compared with that at 350 km orbital altitudes, and the accuracies are decreased respectively 8.718 times and 75.307 times at 400 km and 450 km compared with that at 350 km orbital altitudes.Secondly, cumulative geoid height error is 3.993
×10-1 cm as using 50 km intersatellite range, and the accuracies are reduced respectively 1.259 times and 1.395 times using 110 km and 220 km compared with that using 50 km intersatellite ranges.Finally, the optimal designs of average orbital altitude 350 km and mean intersatellite range 50 km are suggested in the future first ImprovedGRACE gravity satellite in China.
Zheng Wei,Xu Houze ,Zhong Min et al. RESEARCH ON OPTIMAL SELECTION OF ORBITAL PARAMETERS INIMPROVED-GRACE SATELLITE GRAVITY MEASUREMENT MISSION[J]. , 2010, 30(2): 43-48.
Zheng Wei,Xu Houze ,Zhong Min et al. RESEARCH ON OPTIMAL SELECTION OF ORBITAL PARAMETERS INIMPROVED-GRACE SATELLITE GRAVITY MEASUREMENT MISSION[J]. jgg, 2010, 30(2): 43-48.
