The actual orbit will deviate from the nominal orbit when spacecraft maneuvers because of all kinds of error factors. The covariance propagation equations need to be developed for the main error factors when spacecraft maneuvers. Desired effect has been obtained for orbital error propagation by covariance technique. But the dynamic model is over simplified. Therefore the inherent characteristics of the nonlinear system are neglected. In this paper, the orbital error propagation equations are proposed by real linearized method and quasi linearized method, and the perturbation effect of the equations is taken into consideration. Through numerical simulations. The error of orbit prediction is obtained by reference to Monte Carlo method. The results of the proposed orbital error propagation equations are compared with that of real linearized method and quasi linearized method. Results show: the quasi linear model has higher accuracy than the linear model. Orbital control error propagation equations are also proposed by quasi linearized method. The simulation analysis show: the size deviation of the control force has the greatest influence on the error propagation accuracy of orbital control.