Abstract：In this study, totally eight typical spacecraft are selected, including three types depending on their orbit altitudes, namely low earth orbit, medium earth orbit and high earth orbit, respectively. A numerical integration method is applied for orbit propagation with orbit initial conditions obtained by Two Line Elements. Furthermore, the individual effect of each discussed perturbation force is compared with reference orbit. Consequently, analysis and summaries indicate that remarkable displacement bias is caused by the Earth geopotential gravity. Besides, atmospheric drag is connected with orbit altitude, which is at a very small level for a medium or high orbit. Meanwhile, results show apparent periodic variance of solar radiation pressure corresponding to spacecraft operating period.
