通过两行根数获取轨道初值，以数值积分方法进行轨道预报，比较不同航天器的主要摄动力影响，并按航天器的轨道类型进行总结与分析。结果表明，地球非球形引力是产生位移偏量最大的摄动力，大气阻力和三体引力摄动与轨道高度有明显联系，太阳光压摄动力具有与航天器运行周期一致的周期特征。

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.