Payload Optimization for EnVision Mission Using an Electric Propulsion Module for Interplanetary Transfers

Abstract

This paper presents a study on the feasibility of using electric propulsion (EP) for interplanetary transfer in the context of an Earth–Venus mission. Extensive research has been conducted on EP modules for Mars missions, demonstrating their potential for faster mission times and greater flexibility compared to all-chemical propulsion (CP) systems. However, there is a notable gap in our understanding regarding EP systems for Venus missions, despite the unique and challenging environment that Venus presents. This study aims to bridge that gap by evaluating the performance of an EP module compared to a conventional all-CP spacecraft, which serves as the backup mission for the EnVision mission by the European Space Agency. The objectives of the study include identifying key drivers for the EP module’s preliminary design, analyzing tradeoffs and challenges associated with EP systems, and evaluating the feasibility of achieving payload mass delivery. The results reveal that the all-EP spacecraft delivers a higher payload mass compared to the all-CP EnVision mission, highlighting the superiority of EP over CP for interplanetary missions. This research provides valuable insights into the potential advantages of EP systems for future interplanetary missions and emphasizes the necessary design considerations when utilizing EP technology.