Abstract：The variation of perturbation forces and the complexity of special flying environments of low earth orbit satellites make traditional dynamics orbit determination method can not be competent for cmlevel accuracy. It studies the application of acceleration data as a substitutive method for nonconservative perturbation force to dynamic orbit determination.Experimental results for gravity satellite CHAMP and GRACE show that cmlevel orbit accuracy can be reached by using acceleration observation. The accuracy is the same as compared with the experienced force compensation model method and better than the traditional method which deals with all force by modeling.
