Моделювання конструктивно-технологічних параметрів шасі літака

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dc.contributor.authorЯцковий, А. О.
dc.contributor.authorВірченко, Г. А.
dc.date.accessioned2023-04-25T11:43:32Z
dc.date.available2023-04-25T11:43:32Z
dc.date.issued2017
dc.description.abstractotherRecently, the relation of some countries in the world has become aggravated. The situation in eastern Ukraine can be considered as an example. Therefore, there is a task to design and manufacture the cargo aircraft that will be adapted to the specified circumstances (AN-178), but it is not feasible in very short term. One of the ways to solve this problem is to improve the existing cargo aircraft (its chassis and chassis options) and to improve its use in the particular conditions. As it is known, it is expedient to use the fixed chassis on planes for small speeds and load-carrying capacity increase (due to the absense of a niche under the chassis). The performed calculations show that the aircraft does not bear the large losses of Cx () and Cy () in the case of the fixed chassis installing. There are no recommendations regarding the design and construction of the aircraft chassis. Existing techniques and programs for the design and technological parameters modelling of the chassis and its fairing do not give a picture for the exact achievement of the set model conditions and generally, they are are not solved. Having analyzed the dependencies of / K Cy for each profile, it was concluded that the NACA profile 643612 behaves best at 0... 0,8 Сy , which corresponds to the value of the lifting force in most flight modes of the AN-140 and it can be used for chassis fairing . As a result of the performed research, it was determined that the modelling of the chassis flange is appropriate for this airplane and has minimally negative affects for aerodynamic qualities. Four aerodynamic profiles have been analyzed, their geometric parameters have been selected. For the formation of the fairing longitudinal projection the best aerodynamic profile is selected. The construction of a folding chassis unit justifies the feasibility of using CAD COMPASS-3D specifically for this type of modelling.uk
dc.format.pagerangeС. 108-115uk
dc.identifier.citationЯцковий, А. О. Моделювання конструктивно-технологічних параметрів шасі літака / А. О. Яцковий, Г. А. Вірченко // Механіка гіроскопічних систем : науково-технічний збірник. – 2017. – Вип. 34. – С. 108-115. – Бібліогр.: 6 назв.uk
dc.identifier.doihttps://doi.org/10.20535/0203-3771342017122918
dc.identifier.urihttps://ela.kpi.ua/handle/123456789/54892
dc.language.isoukuk
dc.publisherКПІ ім. Ігоря Сікорськогоuk
dc.publisher.placeКиївuk
dc.relation.ispartofМеханіка гіроскопічних систем: науково-технічний збірник, Вип. 34uk
dc.subject.udc001.891.574uk
dc.titleМоделювання конструктивно-технологічних параметрів шасі літакаuk
dc.typeArticleuk

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Механіка гіроскопічних систем: науково-технічний збірник, Вип. 34