KINEMATIC PRECISE ORBIT DETERMINATION OF LOW EARTH ORBITER BASED ON EPOCHDIFFERENCE STRATEGY
Chen Junping 1,2) ; and Wang Jiexian 1,3)
1)Department of Surveying and Geomatics, Tongji University, Shanghai 2000922)GeoForschungsZentrum Potsdam, 14473, Potsdam, Germany3)Key Laboratory of Modern Engineering Surveying, State Bureau of Surveying and Mapping, Shanghai 20002
Abstract On the basis of the theory of Precise Point Positioning (PPP), a kinematic algorithm ——POD(Precise Orbiter Determination) based on an epochwise processing of the code observations combined with an epoch-differece processing of the phase observations is introduced. The method allows recovering the trajectory of the LEO without making use of any a priori dynamic perturbation, e.g., gravity field information and air drag, it may be very useful for gravity field recovery. Experiments with CHAMP and GRACE observations over a period of 2 weeks show that kinematic orbits of CHAMP have an average 3D RMS about 0.41m comparing to reference orbits, while the average 3D RMS of GRACE is 0.45 m,the average RMS of the 3 axes component (0.22,0.22,0.25) m are of CHAMP and (0.27,0.23,0.29) m of GRACE.
Chen Junping,and Wang Jiexian. KINEMATIC PRECISE ORBIT DETERMINATION OF LOW EARTH ORBITER BASED ON EPOCHDIFFERENCE STRATEGY[J]. , 2007, 27(4): 57-61.
Chen Junping,and Wang Jiexian. KINEMATIC PRECISE ORBIT DETERMINATION OF LOW EARTH ORBITER BASED ON EPOCHDIFFERENCE STRATEGY[J]. jgg, 2007, 27(4): 57-61.
