Abstract: Numerical method of orbit determination usually can not directly obtain mean orbit period rate used to calculate orbit maneuver strategy for recoverable spacecraft,but can solve atmospheric drag coefficient.Through the creation of sophisticated spacecraft dynamics models,numerical integrator,conversion algorithm from osculating elements to mean elements and polynomial fitting algorithm for mean period series,a calculation method of mean orbit period rate was proposed based on numerical method for precision orbit determination and prediction.Applications for the two spacecrafts have revealed to the validity of the methodology.