In this article have been proposed the design objectives for an integrated guidance system of a
commercial launch vehicle with application of GPS technologies and has been set a technical problem of the
conceptual design of an integrated navigation system for the space launch vehicle qualified to inject small artificial
Earth satellites into low and medium circular orbits. The conceptual design of the integrated navigation system
based on GPS technology involves determination of its structure, models and algorithms, providing the
required accuracy and reliability in injecting payloads with due regard to restrictions on weight and
dimensions of the system.
Determination of the adequacy of space launch vehicle system development conditions using a statistical similarity criterion