Specific Mass Optimization Modeling of Space Nuclear Electric Propulsion System for Jupiter Exploration Mission

Abstract

The space nuclear electric propulsion (NEP) system is a revolutionary space propulsion technology that converts nuclear heat energy into electrical energy and drives high-power electric thrusters to generate thrust. Compared with traditional propulsion technology, NEP has the advantages of high specific impulse, high power and long life, which is very suitable for large-scale deep space exploration missions in the future. In this paper, the specific mass model of high power NEP system is established based on NEP system composition and the theory of small thrust orbit to obtain the maximum payload ratio. The complex coupling relation of orbit time, specific mass, power and payload ratio of NEP spacecraft can be decoupled by this model, which provides a computational basis for task optimization. The model was used to evaluate the technical specifications of the NEP system to complete the NASA Juno space mission. The calculation shows that when the specific mass of the NEP system reaches 4.8kg/kWe, it can the ground transfer time of the Juno space mission from 2266 days to 665 days, and the payload from 160kg to 1179kg, which greatly improves the spacecraft's detection capability and providing a useful reference for subsequent design.