Comparative analysis of the launch of satellites for the radiation monitoring using low and high thrust engines

Abstract

This article considers the comparative analysis of the launch of satellites for the Earth radiation monitoring using low-thrust engines – electric propulsion system (EPS), and high thrust – chemical rocket engines (CRE). The launch scheme assumes successive delivery of satellites to the predetermined orbits with the help of a space tug, previously launched into a base circular orbit and equipped with CRE or EPS. The parameters of the trajectories are calculated – considering both the form of ridershare launch of a satellite and the clustered launch of two satellites into specified elliptical orbits. The flight of the spacecraft with the CRE is approximated by impulsive maneuvers, and the flight with the EPS is calculated under the condition of minimizing the flight time using the maximum principle of Pontryagin. The results obtained demonstrate the technical feasibility and advantages of satellite delivery into specified orbits using low and high thrust engines – chemical rocket engines and electric propulsion system.