ESTIMATION OF THE POSSIBILITY OF USING A SOLAR SAIL IN THE PROBLEMS OF COMBINED DEORBITING FROM LOW-EARTH ORBITS

  • V. Korobka Oles Honchar Dnipro National University
  • M. Dron Oles Honchar Dnipro National University
  • A. Golubek Oles Honchar Dnipro National University
Keywords: COMBINED DEORBITING, JET PROPULSION SYSTEM, SOLAR SAIL, LOW-EARTH ORBITS.

Abstract

To clean the upper segment of low-Earth orbits with an altitude of 1400-2000 km, the possibility of using a combined method of deorbiting to the Earth's atmosphere has been evaluated. It is based on the combined use of a jet propulsion system and a solar sail. A scheme has been developed for the combined deorbiting of a satellite with a lifetime of up to 25 years. Its features: the solar sail provides a gradual decrease in flight altitude, and the ignition of a jet propulsion system at the end of the deorbiting period - the formation of an orbit with perigee in the dense layers of the Earth's atmosphere (120 km and below). Simulation of the deorbiting processes of a large-sized satellite using a jet propulsion system, a solar sail and their combination has been carried out. A comparative analysis of the mass of the deorbiting system for various methods is carried out. At the same time, it is believed that the satellite is equipped with a jet propulsion system for additional orbital expansion and maintenance. For the deorbiting of a spacecraft with a mass of 1 ton from an orbit of 2000 km, the following results were obtained. The minimum solar sail area is about 1200 m2. For comparison, the most expensive is the deorbiting by the active method using a jet propulsion system. It requires about 140 kg of propellant on board. The least costly steer is the passive method using a solar sail. It requires a system with a mass of about 34 kg on board. In turn, the area of the combined method lies between these two methods. It is inferior in mass to the passive deorbit system, but outperforms the active one. Its effectiveness in comparison with the active method ranges up to 76%. It can be used in cases where there are restrictions on passive deorbiting, for example, in terms of the overall and mass characteristics of the deorbit system or in terms of the control system lifetime.

Author Biographies

V. Korobka, Oles Honchar Dnipro National University

Украина. Днипровский национальный университет имени Олеся Гончара.

Студент.

Сфера интересов – проектирование ракетно-космических летательных аппаратов.

M. Dron, Oles Honchar Dnipro National University

Украина. Днипровский национальный университет имени Олеся Гончара.

Профессор кафедры проектирования и конструкций. Доктор технических наук, профессор.

Сфера интересов – проектирование авиационно-космической техники.

A. Golubek, Oles Honchar Dnipro National University

Украина. Днипровский национальный университет имени Олеся Гончара.

Доцент кафедры систем автоматизированного управления, кандидат технических наук, доцент.

Сфера интересов – динамика, баллистика и управление движением ракетно-космических летательных аппаратов.

References

Голубек О.В., Дреус А.Ю., Ємець В.В., Пашков А.В. Системи відводу космічних об’єктів з низьких навколоземних орбіт: монографія. Дніпро: Ліра, 2019. 218 с.

Палий А.С. Методы и средства увода космических аппаратов с рабочих орбит (состояние проблемы) Техническая механика. 2012. № 1. С. 94-102.

Ionel A. Deorbiting upper-stages in LEO at EOM using solar sails. Incas

bulletin. 2017. No 9 (2). P. 117-132.

DOI: 10.13111/2066-8201.2017.9.2.9.

Zimin V.N., Nerovny N. On the analysis of a rotating solar sail. Mechanics of Solids. 2017. Vol. 52 (2). P. 195-199.

DOI: 10.3103/S0025654417020091.

Mori O., Okuizumi N., Chujo T., Takao Y. Improvement of sail storage and deployment mechanism for spin-type solar power sail. Astrodynamics. 2020. Vol. 4. P. 223-231. DOI: 10.1016/j.asr.2020.03.028.

Nesterin I. M., Pichhadze K. M., Sysoev V. K., Finchenko V. S., Firsyuk S. O., Yudin A. D. Proposal for Creating a Device for Deorbiting Low-Earth-Orbit CubeSats. Solar System Research. 2018. Vol. 52. P. 606-612. DOI: 10.1134/S003809461807016X.

Firuzi S., Gong S. Attitude Control of a Flexible Solar Sail in Low Earth Orbit. Journal of Guidance, Control, and Dynamics. 2018. Vol. 41. No. 8. P. 1715-1730.

DOI: 10.1007/s42064-019-0063-z.

Kelly P.W., Bevilacqua R., Mazal L., Erwin R.S. TugSat: Removing Space Debris from Geostationary Orbits Using Solar Sails. Journal of Spacecraft and Rockets.

Vol. 55. No. 2. P. 437-450.

DOI: 10.2514/1.A33872.

Yoo Y., Kim S., Suk J., Kim J. Attitude Control System Design & Verification for CNUSAIL-1 with Solar/Drag Sail. International Journal of Aeronautical and Space Sciences. 2016. Vol. 17. No. 4. P. 579-592. DOI: 10.5139/IJASS.2016.17.4.579.

Barnes N.C., Derbes W.C., Player C.J., Diedrich B.L. Sunjammer: A Solar Sail Demonstration. Advances in Solar Sailing. 2014. P. 115-126.

Mei H., Damaren C.J., Zhan X. Hybrid removal of end-of-life geosynchronous satellites using solar radiation pressure and impulsive thrusts. Advances in Space Research. 2020. Vol. 66. No 4. P. 974-991.

DOI: 10.1016/j.asr.2020.04.052.

Макаренкова Н.А. Управление пространственным положением солнечного паруса. Труды МАИ. 2017. Выпуск № 94. URL: https://mai.ru/publications/index.php? ID=81044 (дата доступа 30.06.2021).

Чернякина И.В., Старинова О.Л. Комплексное моделирование поведения конструкции космического аппарата с солнечным парусом роторного типа. Известия Самарского научного центра Российской академии наук. 2019. Т. 21. № 1 (87). С. 45-51.

Трофимов С.П. Увод малых космических аппаратов с низких околоземных орбит: дис. канд. физ.-мат. наук: 01.02.01. М., 2015. 125 с. – URL: http://library.keldysh.ru/diss.asp?id=2015-trofimov (дата доступа 30.06.2021).

Сихарулидзе Ю.Г. Баллистика и наведение летательных аппаратов. 2-е изд. эл. – М.: БИНОМ. Лаборатория знаний, 2013. – 407 с.

Эльясберг П.Е. Введение в теорию полёта искусственных спутников Земли. – М.: URSS, 2015. – 544 с.

Жданюк В.Ф. Основы статистической обработки траекторных измерений. – М.: Сов. радио, 1978. – 384 с.

Published
2021-11-17
How to Cite
Korobka, V., Dron, M., & GolubekА. (2021). ESTIMATION OF THE POSSIBILITY OF USING A SOLAR SAIL IN THE PROBLEMS OF COMBINED DEORBITING FROM LOW-EARTH ORBITS. Journal of Rocket-Space Technology, 29(4), 179-189. https://doi.org/10.15421/452120
Section
Spacecraft, satellite systems and methods for processing satellite data