Analysis of low-thrust satellite tour strategy in the Jupiter system

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Abstract

A new method for designing a Tisserand graph with low-thrust between gravity assists is proposed. The motion of a spacecraft is considered in the context of the circular restricted three-body problem and the zero-radius sphere of influence model, based on conjugate conic sections. Simple control algorithms for changing the semi-major axis and eccentricity are used for low-thrust maneuvers. The analysis of the proposed control algorithms is carried out. The effectiveness of the proposed technique is shown. Examples of effective low-thrust spacecraft maneuvering strategies in the Jupiter satellite system for transfer to the orbits of Europa, Ganymede, and Calisto have been obtained.

About the authors

A. V. Ivanyukhin

Research Institute of Applied Mechanics and Electrodynamics of Moscow Aviation institute; Peoples Friendship University of Russia (RUDN University)

Author for correspondence.
Email: ivanyukhin.a@yandex.ru
Moscow, Russia

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