RUDN Journal of Engineering ResearchRUDN Journal of Engineering ResearchВестник Российского университета дружбы народов. Серия: Инженерные исследования2312-81432312-8151Peoples’ Friendship University of Russia named after Patrice Lumumba (RUDN University)2725510.22363/2312-8143-2021-22-1-36-42ArticlesСтатьиResearch ArticleStress-strain state analysis of the design of full-turning vertical empennage for aero-spacecraftАнализ напряженно-деформированного состояния конструкции цельноповоротного вертикального оперения малогабаритного аэрокосмического летательного аппаратаChistyakovAndrey A.ЧистяковАндрей Андреевич

Master Student of the Department SM-13 Rocket and Space Composite Structures, BMSTU

магистрант кафедры СМ13 «Ракетно-космические композитные конструкции» МГТУ им. Н.Э. Баумана

chistyakov_andrew@outlook.comTimoshenkoValery P.ТимошенкоВалерий Павлович

Professor of the Department SM-13 Rocket and Space Composite Structures, BMSTU; Dr. Sc.

профессор кафедры СМ13 «Ракетно-космические композитные конструкции» МГТУ им. Н.Э. Баумана; д-р техн. наук

moltim@yandex.ruBauman Moscow State Technical University (National Research University of Technology)Московский государственный технический университет имени Н.Э. Баумана (национальный исследовательский университет)27082021221VOL 22, NO1 (2021)ТОМ 22, №1 (2021)364227082021Copyright ©; 2021, Chistyakov A.A., Timoshenko V.P.Copyright ©; 2021, Чистяков А.А., Тимошенко В.П.2021Chistyakov A.A., Timoshenko V.P.Чистяков А.А., Тимошенко В.П.http://creativecommons.org/licenses/by/4.0https://journals.rudn.ru/engineering-researches/article/view/27255

In this work, the most rational schemes to designing the skin of a full-turning vertical empennage element (stabilator) have been studied. Skin designing schemes were chosen according to aero-spacecraft operating conditions in the re-entry trajectory. During designing process, the requirements for reusable structures of tourist-class aero-spacecrafts were taken into account, such as: maximum simplicity and endurance of the product. To determine the mechanical loads acting on the keel during its movement in the air, a numerical simulation of the aerodynamic flow-around the stabilator profile at 5 arbitrary points on the flight path was carried out. The parameters used for the analysis are: flight velocity, density and viscosity of the air. Of the 5 obtained fields of dynamic pressure acting on the stabilator, the field that creates the largest distributed load was used as the boundary condition for the analysis of the stress-strain state of the structure. The problem of mechanical loading of the stabilator was solved separately for each of the previously studied structural schemes of the skin. Based on the obtained calculation results the optimal skin structural scheme was chosen by comparing the displacements on the line connecting ribs.

В представленной работе были рассмотрены наиболее рациональные схемы конструирования обшивки цельноповоротного вертикального оперения (киля). Критерии, в соответствии с которыми выбирались схемы конструирования обшивок, соответствуют условиям функционирования аэрокосмического летательного аппарата на траектории спуска в атмосфере. В процессе конструирования силовой схемы киля (каркаса) учитывались требования, предъявляемые к многоразовым конструкциям аппаратов туристического класса, такие как максимальная простота и выносливость изделия. Для определения механических нагрузок, действующих на киль в процессе его движения в воздушной среде, проводилось численное моделирование аэродинамического обтекания профиля киля в 5 произвольных точках траектории полета. Параметрами, по которым проводился анализ, являются скорость полета, плотность и вязкость среды. Из 5 полученных полей динамического давления, действующего на киль, в качестве граничных условий для анализа напряженно-деформированного состояния конструкции использовалось поле, создающее наибольшую распределенную нагрузку. Решалась задача механического нагружения конструкции киля отдельно для каждой из рассмотренных ранее конструктивных схем обшивок. На основании полученных результатов расчетов, путем сравнения прогибов на линии, соединяющей поперечные силовые элементы каркаса, была выбрана оптимальная схема конструирования обшивки.

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