Cosmic ResearchCosmic ResearchКосмические исследования0023-42063034-5502The Russian Academy of Sciences69671710.31857/S0023420625050031ArticlesСтатьиResearch ArticleAnalysis of low-thrust satellite tour strategy in the Jupiter systemАнализ рациональных схем спутниковых туров с малой тягой в системе ЮпитераIvanyukhinA. V.ИванюхинА. В.ivanyukhin.a@yandex.ruResearch Institute of Applied Mechanics and Electrodynamics of Moscow Aviation instituteНаучно-исследовательский институт прикладной механики и электродинамики Московского авиационного институтаPeoples Friendship University of Russia (RUDN University)Российский университет дружбы народов15092025635VOL 63, NO5 (2025)ТОМ 63, №5 (2025)48250021112025Copyright ©; 2025, Russian Academy of SciencesCopyright ©; 2025, Российская академия наук2025Russian Academy of SciencesРоссийская академия наукhttps://journals.eco-vector.com/0023-4206/article/view/696717

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.

Предлагается новый метод построения карты Тиссерана с маневрами малой тяги между гравитационными маневрами. Движение космического аппарата рассматривается в рамках ограниченной круговой задачи трех тел и метода грависфер нулевой протяженности на основе сопряженных конических сечений. Для совершения маневров с малой тягой предлагается использовать простые законы управления для коррекции большой полуоси и эксцентриситета. Проведен анализ предложенных законов управления. Продемонстрирована эффективность предложенной методики. Получены варианты рациональных схем маневрирования космического аппарата с двигателем малой тяги в спутниковой системе Юпитера для выхода на орбиты Европы, Ганимеда и Калисто.

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