Abstract: In this article, it is analyzed that how the GEO orbit propagation with a singe step numerical integrator, the representative Runge-Kutta(RKF7(8))method, or a multi-steps one, the representative 12 degrees PECE method, affected by the boundaries of cylinder shadow model or conical shadow model. And more, some correcting methods are introduced according to the idiographic problems. All the introduced methods are convenient for users to program with simple principles, and lead to high accuracy corrected orbit. The maximal bias in 3 day length arcs is in centimeter magnitude, even less.