novtexmechМехатроника, автоматизация, управлениеMekhatronika, Avtomatizatsiya, Upravlenie1684-64272619-1253Commercial Publisher «New Technologies»10.17587/mau.24.652-659novtexmech-1469Research ArticleДИНАМИКА, БАЛЛИСТИКА И УПРАВЛЕНИЕ ДВИЖЕНИЕМ ЛЕТАТЕЛЬНЫХ АППАРАТОВDYNAMICS, BALLISTICS AND CONTROL OF AIRCRAFTИсследование цилиндрических орбит ниже южного полюса Луны вблизи точки L2 на основе солнечного парусаStudy on Displaced Orbits Below the Moon’s South Pole Near L2 Point Based on Solar SailЮйВ.YuW.

аспирант

г. Самара

Postgraduate Student

Samara

yussau@foxmail.comСтариноваО. Л.StarinovaO. L.

д-р техн. наук, проф.

г. Самара

PhD. Tech. Sc, Professor

Samara

solleo@mail.ruСамарский национальный исследовательский университетРоссияSamara National Research UniversityRussian Federation2023061220232412652659Copyright © Commercial Publisher «New Technologies», 20232023Commercial Publisher «New Technologies»Commercial Publisher «New Technologies»https://mech.novtex.ru/jour/about/submissions#copyrightNoticehttps://mech.novtex.ru/jour/article/view/1469

Исследуются цилиндрические орбиты солнечных парусов ниже южного полюса Луны в окрестности точки либрации L2 системы Земля—Луна. Давление солнечного излучения обеспечивает ускорение для цилиндрических орбит. Такие орбиты позволяют поддерживать непрерывную связь и наблюдение за южной полярной областью Луны, где планируется создание лунной базы. Линеаризованные уравнения динамики дают аналитические решения цилиндрических орбит, которые могут быть квазипериодическими или периодическими. Квазипериодические орбиты имеют переменную высоту в диапазоне сотен километров и период около года, а периодические орбиты имеют постоянную высоту и тот же период. Управление в скользящем режиме поддерживает орбиты с использованием углов ориентации паруса и его отражательной способности в качестве управляющих параметров. При парусности солнечного паруса 18 м2/кг высоты цилиндрических квазипериодической и периодической орбит под точкой либрации L2 составляют 2010,38 км и 2210,06 км соответственно. Численное моделирование подтверждает эффективность управления в скользящем режиме для обоих типов орбит.

This work explores displaced orbits of solar sails below the Moon’s south pole, near the L2 libration point in the Earth-Moon system. Light pressure provides acceleration for displaced orbits. These orbits enable continuous communication and observation of the Moon’s south polar region, where a lunar base is planned. Linearized dynamic equations yield analytical solutions of displaced orbits, which are either quasi-periodic or periodic. Quasi-periodic orbits have varying altitudes of hundreds of kilometers and a period of about a year, while periodic orbits have fixed altitudes аnd the same period. A sliding mode controller maintains the orbits using sail attitude angles and reflectivity as control variables. With a reflective area to mass ratio of 18 m2/kg, the displaced heights of quasiperiodic and periodic orbits near L2 are 2010.38 km and 2210.06 km, respectively. Numerical simulations confirm the controller’s effectiveness for both orbit types

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The authors declare that there are no conflicts of interest present.