Atmospheric drag is the main perturbation force on a low earth orbit satellite and is closely related to the variation of high atmospheric density.
大气阻力是低轨卫星主要的摄动力，与高层大气密度的变化密切相关。
The variation equation of the satellite orbit elements under both J2 and drag perturbations was derived based on the Gauss perturbation equation.
基于高斯摄动方程，推导了卫星在同时考虑J2和大气摄动情况下的轨道根数变化方程。
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