The paper considers the problem of launching satellites into the orbits for Earth radiation monitoring using the upper stage previously inserted into a reference circular orbit and equipped with a combined propulsion system, i.e. chemical rocket engines and electric rocket propulsion system (ERPS). The combined launch scheme implies formation of the intermediate orbit using the chemical rocket engines and further successive satellites insertion into the target orbits using the electric rocket propulsion system. Calculation of the satellite group launch trajectory parameters is provided, single accompanying and two more in cluster formation, to the given elliptical orbits. The spacecraft flight is approximated at the chemical rocket engines operation phase by a pulse action using the double-pulse apsidal maneuvers; and the spacecraft flight trajectory in the ERPS phase is calculated under the condition of minimizing the flight time with the Pontryagin maximum principle. The results obtained demonstrate technical feasibility of the task of launching satellites into specified orbits using the combined thrust, as well as advantages of a combined scheme for launching a payload in order to reduce flight duration compared to using the ERPS throughout the entire flight.