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Mathematical modeling of plumes impingement on landing site of "ExoMars" landing platform A. Kagenov, A. Glazunov, K. Kostyushin, I. Eremin

Contributor(s): Kagenov, Anuar M | Kostyushin, Kirill V | Eremin, Ivan V | Glazunov, Anatoly AMaterial type: ArticleArticleSubject(s): Экзомарс, поверхностная платформа | Марс, планета | математическое моделирование | посадочные платформы | контролируемая посадкаGenre/Form: статьи в журналах Online resources: Click here to access online In: AIP Conference Proceedings Vol. 1899. P. 060010-1-060010-7Abstract: This paper presents the results of numerical studies of the interaction of underexpanded four supersonic plumes with surfaces. The final stage of controlled landing of “ExoMars” landing platform on the surface of Mars is considered. The altitude of landing platform from 1 to 0.3 meter above the surface of Mars and the thrust level of the propulsion system is varied. The distributions of the parameters of gas near landing platform are obtained during operation of propulsion system at the minimum and maximum thrust. The ground effect lift loss under Mars conditions for given configuration landing platform is investigated. The insignificant of ground effect lift loss at altitude 1 meter was found and value of lift loss varied from 1 % to 3% depending on level of propulsion system thrust. For another altitudes, received significant effect of external pressure on the bottom surface of landing platform. The magnitude of this external pressure reached 26% of the maximum thrust of propulsion system.
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This paper presents the results of numerical studies of the interaction of underexpanded four supersonic plumes with surfaces. The final stage of controlled landing of “ExoMars” landing platform on the surface of Mars is considered. The altitude of landing platform from 1 to 0.3 meter above the surface of Mars and the thrust level of the propulsion system is varied. The distributions of the parameters of gas near landing platform are obtained during operation of propulsion system at the minimum and maximum thrust. The ground effect lift loss under Mars conditions for given configuration landing platform is investigated. The insignificant of ground effect lift loss at altitude 1 meter was found and value of lift loss varied from 1 % to 3% depending on level of propulsion system thrust. For another altitudes, received significant effect of external pressure on the bottom surface of landing platform. The magnitude of this external pressure reached 26% of the maximum thrust of propulsion system.

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