Choosing an efficient option of the combined propulsion system and flight profile of the INTERHELIO-PROBE spacecraft

Abstract

The paper is devoted to the design features of the prospective Russian INTERHELIO-PROBE spacecraft using, depending on the configuration version, an electric or chemical propulsion system as a sustainer. The scientific goal of the mission is the study of near-solar space from close distances (60–70 solar radii). The paper presents the description of several versions of the spacecraft options depending on the installed propulsion system, as well as the main characteristics of the flight profile depending on the engine type.