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Two methods for construction and use of integrated inertial and satellite systems are considered, taking into account the specific features of aviation-related applications, namely, alignment correction, and autocalibration. Alignment correction is performed during aircraft maneuvering on the airfield. Autocalibration of strapdown inertial navigation systems (SINS) is based on using the estimations of instrumental errors of inertial sensors, which had been obtained by the complex information processing (CIP) algorithm in a number of previous flights of the aircraft. The results of numerous flight tests of laser SINS designed by PAO MIEA for civil and military applications are provided as an evidence of high efficiency of the information integration methods proposed herein. [ABSTRACT FROM AUTHOR]