МОДЕЛЮВАННЯ ПРОЦЕСІВ АЕРОДИНАМІЧНОГО НАГРІВУ І ПЛАВЛЕННЯ КОСМІЧНИХ ОБ’ЄКТІВ В АТМОСФЕРІ ЗЕМЛІ
DOI:
https://doi.org/10.15421/472203Keywords:
large-sized space debris object, a combined method of de-orbit, aerodynamic heating, thermal destruction, the constructional materials, the first stages of launch vehicles, fuel tanksAbstract
The results of modeling the processes of thermal destruction of large-sized space debris objects due to aerodynamic heating and melting in the upper atmosphere are presented in order to determine the feasibility of using a combined method for their de-orbiting. The cylindrical and spherical models of space debris elements were considered to estimation of the parameters of thermal destruction. The guess, that melt layer which is formed on an object surface, is carried away by a running atmospheric flow, was assumed. The value of heat flux depends on the location on the body surface, thus, two cases were considered: stagnation point, where the heat flux is maximum, and the point on a flat surface. It is shown that the efficiency of destruction of cylindrical bodies (first stages of launch vehicles) depends on the
angle of attack during object movement in the atmosphere. The most advantageous, to provide the maximum thermal load, are the angles of attack not less than 40°. At small angles of attack, the thermal load on the side surface is insignificant, which can lead to incomplete destruction of the object. Calculations also showed effective combustion of objects spherical shape (fuel tanks of upper stages in the atmosphere. The presented trajectories of deorbiting of space debris objects confirm the effectiveness of thermal destruction for reentry angles: 0°; 0,5°; 1,0°; 1,5°. At the same time, the melting rate increases when reentry angle is increasing. Complete thermal destruction (melting) of the discharge objects is possible for the structural material from aluminum alloys, in particular АМг6. This case takes place in aerospace design practice. Thus, the use of a combined method of deorbiting the large-sized space debris into the dense layers of the Earth's atmosphere is quite appropriate, because it provides the productive aerodynamic heating and thermal destruction in the atmosphere some objects like as used first stages of launch vehicles or fuel tanks, which are the most typical components of space debris
References
Takahashi, Yusuke. Aerodynamic heating of inflatable aeroshell in orbital reentry [Text]/Yusuke Takahashi, Kazuhiko Yamada//Acta Astronautica. – 2018. –V. 152. – P. 437 – 448. https://doi.org/10.1016/j.actaastro.2018.08.003
Trushlyakov, V. Combustion possibility assessment for separating launch-vehicle components during atmospheric phase of descent trajectory [Text]/V. Trushlyakov, K. Zharikov, D. Davydovich// Acta Astronautica. – 2019. – V. 159. – P. 540-546.
Dreus, A.Yu. The destruction rate estimation of space debris by aerodynamic heating during re-entry to atmosphere [Text]/A.Yu. Dreus, M.M. Dron, K.V. Heti//Вісник Дніпровського університету. Серія: Механіка. – 2022. – Т. 28, № 5. – С. 61 – 68.
Balakrishnan, D. Material Thermal Degradation under Reentry Aerodynamic Heating [Text]/D. Balakrishnan, J. Kurian//Journal of Spacecraft and Rockets. – 2014. – V. 51(4). – P. 1319–1328. doi:10.2514/1.a32712
Pagan, A. S. Experimental Investigation of Material Demisability in Uncontrolled Earth Re-entries [Text]/A.S. Pagan, B. Massuti-Ballester, G. Herdrich et al//31st International Symposium on Space Technology and Science. – Matsuyama, Japan, 2017.
Merrifield, J. Aerothermal heating methodology in the spacecraft aerothermal model (SAM) [Text]/J. Merrifield, J. Beck, G., Markelov, P. Leyland, R. Molina //In Space Safety is No Accident Springer, Cham. – 2015. – P. 463 – 468.
Ostrom, C. Operational and Technical Updates to the Object Reentry Survival Analysis Tool.[Text]/C. Ostrom, B. Greene, A. Smith, R. Toledo-Burdett, et. al//LPI Contributions. – 2109, 6018.
Андреевский, А.А. Динамика спуска космических аппаратов на Землю [Текст]/А.А. Андреевский. – М.: Машиностроение, 1970.
Ярошевский, В.А. Аппроксимация модели стандартной атмосферы [Текст]/В.А. Ярошвский//Ученые записки ЦАГИ. – 2009. – XL(3). – С. 53-59.
Коняев, В.Г. Энергетическая оценка потерь массы теплозащиты летательного аппарата при торможении в атмосфере со сверхкруговой скоростью [Текст]/В.Г. Коняев//Ученые записки ЦАГИ. – 4(6), 124-130.
Веселовский, В.Б. Прогрев и оплавление тел, движущихся в атмосфере [Текст]/В.Б. Веселовский//Техническая механика. – 1998. – №7. – С. 117-122.
Fritsche, B. Spacecraft disintegration during uncontrolled atmospheric re-entry [Text]/B. Fritsche, H. Klinkrad, A. Kashkovsky, E. Grinberg//Acta Astronautica. – 2000. – 47(2-9). – P. 513-522.
Dron, M. Investigation of aerodynamic heating of space debris object at reentry to earth atmosphere[Text]/M. Dron, A. Dreus, A. Golubek, Y. Abramovsky// Proc. 69th International Conference IAC-18, Bremen, Germany, 1-5 October. – Bremen, 2018. – A6.2.
Полежаев, Ю.В. Тепловая защита [Текст]/Ю.В. Полежаев, Ф.Б. Юревич, под ред. А. В. Лыкова. – М.: Энергия, 1976. – 392 с.
