The tightly integration methods of inertial-satellite navigation systems (IS NS) based on estimation of dynamic error models of inertial navigation systems initially have a methodical errors caused by using the procedure of linearization of dynamic error models. This methodical errors are significantly increasing when the rough strapdown inertial navigation system (SINS) implemented based on technology of microelectromechanical systems using as the part of the IS NS. The method of integration of SINS measurements and satellite navigation systems measurements based on the nonlinear digital filtering has been given. This method would eliminate the loss of non-linear relationships in the construction of optimal estimation procedures of navigation parameters in IS NS.