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Journal articles on the topic 'Фюзеляж'

Author: Grafiati

Published: 30 May 2022

Last updated: 31 May 2022

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1

Ефимцов, Б. М., and Л. А. Лазарев. "Расчет колебаний шпангоутов в подкрепленной оболочке, моделирующей фюзеляж самолета." Акустический журнал 60, no. 5 (2014): 518–25. http://dx.doi.org/10.7868/s0320791914040042.

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2

PEYGIN, Sergey V., and Sergey A. ORLOV. "OPTIMAL AERODYNAMIC DESIGN OF A WING-BODY CONFIGURATION FOR A WIDE-BODY LONG-RANGE AIRCRAFT." Vestnik Tomskogo gosudarstvennogo universiteta. Matematika i mekhanika, no. 63 (February 2019): 115–24. http://dx.doi.org/10.17223/19988621/63/10.

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3

Timchenko, S. V. "NUMERICAL STUDY OF THE AERODYNAMIC CHARACTERISTICS OF A “WING – FUSELAGE – ENGINE NACELLE – PYLON” THREEDIMENSIONAL LAYOUT OF THE ENGINE FOR A WIDE-BODY LONG-RANGE AIRCRAFT." Vestnik Tomskogo gosudarstvennogo universiteta. Matematika i mekhanika, no. 62 (2019): 135–41. http://dx.doi.org/10.17223/19988621/62/11.

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4

Bragin, N. N., S. A. Orlov, and S. V. Peygin. "INVESTIGATION OF THE STABILITY OF OPTIMAL AERODYNAMIC DESIGNING OF THE THREE-DIMENSIONAL WINGFUSELAGE LAYOUT FOR A WIDE-BODY LONG-RANGE AIRCRAFT WITH REGARD TO ITS INITIAL SHAPE." Vestnik Tomskogo gosudarstvennogo universiteta. Matematika i mekhanika, no. 62 (2019): 79–90. http://dx.doi.org/10.17223/19988621/62/7.

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5

Царенко, М. "Ордена на фюзеляже." Нумізматика і фалеристика, no. 4 (60) (2011): 26–29.

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6

Дибир, А. Г., А. А. Кирпикин, and Н. И. Пекельный. "ДО ВИЗНАЧЕННЯ УРІВНОВАЖУВАЛЬНОЇ НАВАНТАГИ НА ШПАНГОУТ ОДНОПАЛУБНОГО ФЮЗЕЛЯЖУ." Open Information and Computer Integrated Technologies, no. 91 (June 18, 2021): 113–21. http://dx.doi.org/10.32620/oikit.2021.91.08.

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With the optimal design of the fuselage, a very important issue is the choice of the optimal position of the load-bearing floor in the cross-section of the fuselage.Depending on the relative position of the load-bearing floor, the reduced thickness of the floor, the scheme of fastening the floor to the frames and the ratio of the reduced thicknesses of the fuselage skin and the floor, the position of the center of stiffness of the fuselage cross-section changes, the torsional stiffness of the fuselage. This leads to a change in torque, a redistribution of shear flows, a redistribution of flattening loads on the frame from the bending of the fuselage.In this work, two schemes of fastening the floor to the frame are considered - a rigid, torque connection and a hinged one. In this case, the frame takes up additional load from the floor. The fuselage is considered as a thin-walled rod, loaded with horizontal and vertical shear forces, torque and flattening forces from the fuselage bending.For reliability, the calculation of the position of the center of stiffness in a double-closed cross-section was carried out by two methods: a fictitious force and a fictitious moment. The influence of various parameters on the location of the center of rigidity was investigated. The influence of the vertical position of the floor, the ratio of the reduced thicknesses of the floor and the fuselage skin and the cross-sectional area of the beams of the floor attachment to the fuselage on the position of the center of stiffness was evaluated. Diagrams of these dependencies were constructed based on the results of calculations. The dependence of the torsional stiffness on the position of the floor and the ratio of the reduced thicknesses of the floor and the fuselage skin was investigated. Based on the calculation results, a diagram of these dependencies was built. Various constructive solutions were considered for fastening the floor to the fuselage skin: with their direct connection and with the floor support only on the beam. The floor loading from flattening loads caused by the bending of the fuselage was studied. The diagram of the loading of the frame and the floor from flattening loads is shown.According to the diagrams, you can choose the optimal vertical position of the floor, the reduced floor thickness and the cross-sectional area of the beam

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7

Долгих, Вячеслав Сергеевич. "ОПТИМІЗАЦІЯ НОСОВОЇ ЧАСТИНИ ФЮЗЕЛЯЖУ З ТОЧКИ ЗОРУ АЕРОДИНАМІКИ ЛІТАКА." Open Information and Computer Integrated Technologies, no. 86 (February 14, 2020): 127–38. http://dx.doi.org/10.32620/oikit.2019.86.09.

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The paper represents the analysis intended to optimize the fuselage nose section with regard to aircraft aerodynamics in the process of development of an unmanned transport aircraft (UTA). The article deals with provisions of high aerodynamic efficiency that cannot be achieved without proper selection of the shape and optimal fuselage parameters that determine mutual interference of aircraft components and units. When analyzing the flow improvement around the fuselage nose in flight, three fuselage versions were considered listed further: 1) a prototype for testing automatic flight control systems with participation of pilots; 2) a nose symmetrical relative to the fuselage rocket type cylinder axis; 3) a supposedly optimal variant based on the results of previous calculations. The aerodynamic characteristics of 3D fuselage models for positive integer Reynolds numbers (full-scale model) were calculated using the ANSYS software package. Three computational grids were built for these models in ANSYS ICEM CFD. The given version of the fuselage nose section intended for testing automatic flight control systems with participation of pilots initially has the greatest resistance among the considered variants. That is, first variant of the fuselage nose gives substantial braking zone as well as significant flow acceleration zone exists in place where fuselage is transformed into cylindrical part. The variant with the nose section symmetrical relative to the rocket type cylinder axis has smaller braking zone and less dispersed flow in place where fuselage is transformed into cylindrical part and, therefore, it has lower resistance in comparison with the first version. The fuselage execution developed on the basis of the results of previous calculations, despite the extensive acceleration zone at the junction of the nose to the cylindrical part, has shown the least resistance, respectively, and is the best of the considered variants. This is also confirmed by a comparison of streamlines over the nose surface. The streamlines are given for calculations at angle of attack of 8°; at this angle of attack, the difference in the coefficient Cx is clearly visible.

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8

Двейрін, О. З., О. Г. Гребеніков, А. М. Гуменний, and А. С. Чумак. "МЕТОД ІНТЕГРОВАНОГО ПРОЕКТУВАННЯ НОСОВОЇ ЧАСТИНИ ФЮЗЕЛЯЖУ ЛІТАКА ТРАНСПОРТНОЇ КАТЕГОРІЇ." Open Information and Computer Integrated Technologies, no. 91 (June 18, 2021): 4–36. http://dx.doi.org/10.32620/oikit.2021.91.01.

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Regulatory and technical documentation, design features and methods of fuselage transport category aircraft design was performed and identified the need to update design methods and calculate the characteristics of the fuselage using parametric models and integrated design systems CAD / CAM / CAE / PLM. The method of integrated fuselage design of transport category aircraft is developed and theoretically substantiated. Within the framework of the proposed method, parametric models of master geometry, aerodynamic flow and mass-inertial characteristics of the fuselage were created, taking into account the design features of transport aircraft.The proposed method was used to study the influence of geometric parameters of fuselage nose section on aerodynamic and mass characteristics of the fuselage, showing the efficiency of work with parametric models.The choice of parameters of the fuselage nose section in preliminary and sketch design of a promising aircraft for local airlines is justified, which allowed to implement and test the suitability of the proposed method for in new competitive aircraft designing process.The use of the method for integrated fuselage design for local aircraft allowed to determine the rational configuration of the nose section of the fuselage and increase the fuel efficiency of the aircraft by 6.4%, reduce the aerodynamic drag of the fuselage by 10%, increase the viewing angle from the cockpit by 10%. and ensure compliance with current regulatory and technical documentation, as well as determine the mass-inertial characteristics of the fuselage and its parts and form a list of cockpit equipment that will meet flight safety requirements, taking into account the operating conditions and modifications of the aircraft.The configuration of the nose section of the aircraft fuselage for local airlines has been developed, which allows to fit modern requirements for cockpit equipment and layout, low fuselage impedance and high aerodynamic quality and fuel efficiency in cruising mode at speeds up to 850 km / h (M = 0, 8). As a result of verification using other methods and parameters of existing aircraft, the accuracy of the results obtained using the proposed method at the level of 5% was confirmed.

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9

Бостанов, Баянды Оспанұлы, Еркин Аринов, Ербол Садуахасович Темирбеков, and Байрон Асқарұлы Карасаев. "СОСТАВНАЯ ТРАЕКТОРИЯ НЕПРЕРЫВНОЙ КРИВИЗНЫ." Bulletin of Toraighyrov University. Physics & Mathematics series, no. 3.2020 (October 9, 2020): 24–31. http://dx.doi.org/10.48081/zqvv6566.

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Рассматривается задача о создании безударной сложной траектории (формы, профиля, беговой дорожки) объекта и об определении положения точек соединения, обеспечивающие кинематическую и динамическую гладкости. Исследование направлено, в частности, на улучшение аэродинамических характеристик летательного аппарата, зависящиеся от геометрических характеристик и формы крыла (лопасти, фюзеляжа); на улучшение мореходных качеств судна при плавании в условиях штормового ветра и волнения с использованием комбинированной формы корпуса, удовлетворяющим требованиям к мореходности. Определены математические зависимости, выражающие условия соединения дуг траектории без скачка радиусов кривизны в местах сопряжения. Предлагаемый метод позволяет сформировать сложные технические формы и создать на их основе новые модели комбинированной траектории объекта непрерывной кривизны.

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10

Кузякин, Юрий Петрович. "Повітряний старт ракет-носіїв з вантажного відсіку фюзеляжу транспортного літака." Адаптивні системи автоматичного управління 2, no. 13 (December 16, 2008): 45–54. http://dx.doi.org/10.20535/1560-8956.13.2008.34074.

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11

Калкаманов, С. А. "Особливості обтікання передньої частини фюзеляжу маневреного літака на великих кутах атаки." Наука і техніка Повітряних Сил Збройних Сил України, no. 3(28) (September 26, 2017): 32–36. http://dx.doi.org/10.30748/nitps.2017.28.03.

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12

Конышев, Д. С. "МЕТОД ВИЗНАЧЕННЯ ОСНОВНИХ ПАРАМЕТРІВ ВАНТАЖНОГО ЛЮКА В ХВОСТОВІЙ ЧАСТИНІ ФЮЗЕЛЯЖУ ЛІТАКІВ ТРАНСПОРТНОЇ КАТЕГОРІЇ." Open Information and Computer Integrated Technologies, no. 87 (June 30, 2020): 52–71. http://dx.doi.org/10.32620/oikit.2020.87.02.

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A method has been developed for determining principal parameters for aft cargo door of transport aircraft. A list of input data is given and a technique for finding them is described. An example based on an existing transport aircraft is considered. The following has been used as source data: basic cargo nomenclature to be transported by the designed aircraft, cargo overall dimensions and weight, methods of loading and mooring, loading facilities. More over the design, operational and regulatory parameters are needed, such as landing gear configuration, its bottoming system, extension of rails of the upper equipment for loading/unloading, cargo trajectories during loading and airdropping, codes of the international regulatory bodies such as FAR, CS, AP. Based on the source data, the principle of determining the dimensions of the cargo compartment, cargo floor and the loading sites in the form of a ramp with a pressure bridge, and air stairs is given. The relation between the ramp length and the cargo floor length is described taking into account the loading, unloading and air dropping operations. Correct calculation of these parameters is the most important task, because performance of the future transport aircraft directly depends on the solution. The technique of determining the cargo door opening, development of the load-bearing structure of the transport aircraft fuselage aft section, its main strong elements – the cargo door beam, the ramp, the attachment units, the ramp locks – is given. The interconnection of the ramp load-bearing structure with the load-bearing structure of the fuselage aft part, the options for transferring loads perceived by the ramp to the frame are described. Examples of two types – flat and volumetric – of the cargo door beams, as well as the method of their assignment are considered. Trajectories of the extreme points of the in-gauge load are determined using graphical method for loading, unloading, and airdropping operations. Taking into account the positions of these trajectories makes it possible to select the desired cutout in the fuselage aft section. While designing the aft cargo doors the main features are highlighted. These features when considered make it possible to determine the most optimal parameters of the cutout, the cargo door type and its components.

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13

Быкова, И. С., I. S. Bykova, А. Д. Припадчев, and A. D. Pripadchev. "Программная реализация метода автоматизированного проектирования фюзеляжа воздушного судна с помощью объектно-ориентированных технологий." Международный журнал "Программные продукты и системы" 30 (June 1, 2016): 135–38. http://dx.doi.org/10.15827/0236-235x.114.135-138.

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14

Sergei, Gusev, and Nikolaev Vladimir. "Simulation of compartment thermal condition of passenger aircraft with honeycomb structures of the fuselage." Science Bulletin of the Novosibirsk State Technical University, no. 1 (March 10, 2016): 146–67. http://dx.doi.org/10.17212/1814-1196-2016-1-146-167.

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15

Zheleznov, L. P., and A. N. Seriosnov. "Research on Nonlinear Deformation and Stability of an Aircraft Fuselage Composite Section under Transverse Bending." Proceedings of Higher Educational Institutions. Маchine Building, no. 10 (739) (October 2021): 106–16. http://dx.doi.org/10.18698/0536-1044-2021-10-106-116.

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Currently, there is a lack of studies on the strength and stability of reinforced composite shells, taking into account the momentness and nonlinearity of the initial stress-strain state. Most of the known solutions to the shells stability problems are obtained by analytical and numerical methods, as a rule, in the linear approximation, i.e. in the classical formulation. A developed technique is proposed implementing the finite element method for solving the problems of strength and stability of discrete-reinforced cylindrical shells made of the composite material, taking into account the momentness and nonlinearity of their subcritical stress-strain state. The transverse bending stability of the reinforced aircraft fuselage compartment made of composite material has been investigated. The effect of deformation nonlinearity, stiffness of stringer set, shell thickness on critical loads of the shell instability has been determined.

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16

Pechenyuk, Valery, and Yuri Popov. "CONCEPTUAL DESIGN OF THE WING OR FUSELAGE STRUCTURE OF A MAINLINE AIRCRAFT MADE OF METAL-POLYMER COMPOSITE MATERIALS." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 64 (2021): 74–82. http://dx.doi.org/10.15593/2224-9982/2021.64.08.

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The analysis of existing aircraft structures made of metal-polymer composite materials is carried out, and a list of them with passport characteristics is compiled. The Fokker F-27 Friendship, Boeing-777 and Airbus A380, which use ARALL and GLARE materials, were selected as the aircraft under study. Formulas are determined and the distribution of normal force flows between metal and composite elements in the composition of MPCM based on aluminum sheets (aluminum-fiberglass – SIAL- 1-1, SIAL-3-1 and SIAL-1441 (9/8)) and titanium alloys (samples of titanium-carbon fiber from the patent-Example 1 and Example 3). To determine these parameters, the formulas used for a composite structure made of different materials are used. On the basis of the specification known MPCM the modified formula mixture rule for calculating the strength of new materials with a given set of orientation angles of PCM and the presence of layers of sheet metal, a comparison with standard mechanical characteristics and to show the efficiency of these formulas. Using these formulas, you can determine the strength characteristics for an arbitrary composition of the MPCM package. The features of the choice of design permissible stresses for the design of the airframe of a mainline aircraft made of metal-polymer composite material are highlighted. The concept of designing aircraft airframe elements using MPCM is considered. The results of this work will allow us to determine the rational components of the metal-polymer composite material and the structure of their distribution in the airframe design at the preliminary design stage.

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17

Kirienko, O. A., E. N. Shurkova, O. S. Volny, and S. L. Barbot’ko. "STUDY OF INFLUENCE OF DIFFERENT PROTECTIVE COATINGS ON CHARACTERISTICS OF FIRE SAFETY OF FUSELAGE THERMAL ACOUSTIC INSULATION." Proceedings of VIAM, no. 10 (October 2014): 7. http://dx.doi.org/10.18577/2307-6046-2014-0-10-7-7.

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18

Серебрянникова, В. Ю. "ШЛЯХИ РЕАЛІЗАЦІЇ КОНСТРУКТИВНО-ТЕХНОЛОГІЧНИХ РІШЕНЬ СУМІЩЕННЯ ФУНКЦІЙ ЗВУ-КОІЗОЛЯЦІЇ САЛОНУ МОДИФІКАЦІЙ ПАСАЖИРСЬКОГО СУДНА З СИЛОВОЮ КОНСТРУКЦІЄЮ ФЮЗЕЛЯЖУ." Open Information and Computer Integrated Technologies, no. 94 (February 9, 2022): 50–57. http://dx.doi.org/10.32620/oikit.2021.94.05.

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An analysis of the promising way to implement constructive technological solutions to combine the soundproofing functions of the passenger aircraft modification salon with the power structure of the fuselage is carried out. It is shown that constructive technological solutions aimed at implementing the principle of combining the functions of structural elements of nodes and aircraft units provide a decrease in their mass and value in the process of design, production and operation, as well as to increase other indicators of the efficiency of aircraft modifications of the transport category. At the same time, its special case is productive - the principle of functional summation of structural elements. An analysis of the multi-step path of promising combination of sound insulation functions of the modification of the aircraft and the power structure of its fuselage is carried out. As a first step, an analysis of the efficiency of combining the functions of the structural elements of the sample panel of the fuselage, consisting of a stringer dialing and a thin casing, fixed on the patchmosts. Replacing the three-layer stringer panel, in which the functions and trim functions are combined, ensures an increase in its carrier ability and a loss of mass. At the same time, the substitution of the material of the structural elements made of aluminum alloys on a polymer composite material reinforced with glass or carbon fibers leads to a known effects of effects and is the next step in implementing a multi-step path of combining functions. It is shown that an example of this path of combining the functions of structural elements is the creation of an experimental fuselage of the an aircraft an-2m three-layer design of fiberglass, which has ensured a decrease in mass by 62 kg or 14%. Examples of the results of experimental studies of other authors confirming the effectiveness of sound insulation in various versions of samples of three-layer panels with aggregate. The need for a long and volumetric process of research for implementation in promising modifications of aircraft principle of functional summation of the carrier body of the aircraft cabin with specific constructive-technological solutions of sound insulation, requiring solutions to the strength of structural elements and nodes of the modified fuselage, acoustics and optimization of properties that implement the modification of structural Materials, taking into account the economic efficiency of the analyzed constructive and technological solution.

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19

Panteleev, M. D., A. V. Sviridov, A. A. Skupov, and N. S. Odintsov. "PERSPECTIVE WELDING TECHNOLOGIES OF ALUMINUM-LITHIUM ALLOY V-1469 APPLIED TO FUSELAGE PANELS." Proceedings of VIAM, no. 12 (2020): 35–46. http://dx.doi.org/10.18577/2307-6046-2020-0-12-35-46.

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In this work, we investigated the technological features of promising technologies for laser welding and friction stir welding of high-strength aluminum-lithium alloy V-1469. The modes of laser welding and friction stir welding have been carried out. In this article, we showed the perspective welding methods provide high values of ductility and impact toughness, while the strength of welded joints is not less than 0,8 of the strength of the base material and values of low cycle fatigue is not less than 110•103 cycles. The results allows to propose laser welding and friction stir welding processes as an alternative to riveted joint for aluminum-lithium alloy V-1469 as applied to the elements of the fuselage.

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20

Ванг, Дж. М., С. Дж. Ванг, Х. Ванг, Й. Ма, and К. Дж. Минг. "РАЗЛОЖЕНИЕ ПО ДИНАМИЧЕСКИМ МОДАМ ТЕЧЕНИЯ НА СТЫКЕ КРЫЛА И ФЮЗЕЛЯЖА, "Известия Российской академии наук. Механика жидкости и газа"." Известия Российской академии наук. Механика жидкости и газа, no. 3 (2018): 112–22. http://dx.doi.org/10.7868/s056852811803012x.

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21

Gusev, Sergei, and Vladimir Nikolaev. "A method for evaluating the thermal state of honeycomb structures in the aircraft fuselage by the numerical solution of stochastic differential equations." Science Bulletin of the Novosibirsk State Technical University, no. 2 (June 20, 2015): 20–32. http://dx.doi.org/10.17212/1814-1196-2015-2-20-32.

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22

Ефимцов, Б. М., and Л. А. Лазарев. "Возможность снижения шума в салоне самолета от турбулентного пограничного слоя путем изменения подкрепляющего набора фюзеляжа при неизменной его массе." Акустический журнал 61, no. 5 (2015): 631–35. http://dx.doi.org/10.7868/s0320791915040048.

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23

Mozhaytsev, V. P., and D. V. Semenikhina. "EVALUATION OF THE SHIELDING COEFFICIENTBY CRITICAL SYSTEM FUSELAGE IN THE COMPOSITION OF THE AIRCRAFT." IZVESTIYA SFedU. ENGINEERING SCIENCES, no. 6 (February 13, 2021): 150–59. http://dx.doi.org/10.18522/2311-3103-2020-6-150-159.

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24

Железнов, Л. П. "Исследование влияния углов укладки монослоев на устойчивость композитной цилиндрической оболочки." Механика композиционных материалов и конструкций 27, no. 3 (September 28, 2021): 382–95. http://dx.doi.org/10.33113/mkmk.ras.2021.27.03.382_395.06.

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В настоящее время в конструкциях современных летательных аппаратов нашли широкое применение полимерные композиционные материалы, что значительно облегчает вес конструкции при сохранении ее прочностных и жесткостных характеристик. Несмотря на то, что имеется достаточно большие число работ по исследованию прочности таких конструкций, тем не менее остаются нерешенными вопросы прочности и устойчивости их в условиях нелинейного исходного напряженно-деформированного состояния. Последнее особенно необходимо для конструкций фюзеляжей самолетов, в которых потеря устойчивости композитной обшивки недопустима. Методы расчета на прочность и устойчивость композитных конструкций с учетом нелинейности исходного напряженно-деформированного состояния в настоящий момент недостаточно развиты. Поэтому разработка надежных и эффективных методов расчета оболочек из композиционных материалов является несомненно актуальной задачей. Наиболее подходящим методом в этом случай является метод конечных элементов. Преимущества его в универсальности, физичности и неограниченной возможности применения к сложным конструкциям при произвольном нагружении. Применение метода конечных элементов к расчету оболочек связано со значительными трудностями, обусловленными толщиной и кривизной оболочки. Построение эффективных конечных элементов оболочек является также актуальной задачей и по настоящее время. Большинство разработанных конечных элементов являются элементами круговых цилиндрических, конических или сферических оболочек. В настоящей работе задача прочности и устойчивости цилиндрических композитных оболочек при произвольном нагружении решена методами конечных элементов и линеаризации Ньютона-Канторовича. Использованы разработанные авторами на основе гипотезы Тимошенко конечные элементы некруговых цилиндрических композитных оболочек и элементов подкреплений естественной кривизны, в аппроксимации перемещений, которых в явном виде выделены их жесткие перемещения (перемещения конечных элементов как твердого тела). Критические нагрузки определяются в процессе решения геометрически нелинейной задачи с использованием метода триангуляции матриц и критерия Сильвестра. Вычисляются также формы деформированных в докритическом состоянии оболочек и их формы при потере устойчивости. Исследована устойчивость круговой цилиндрической оболочки, выполненной из полимерного композиционного материала, при различных видах нагружения: крутящим и изгибающим моментами, краевой сжимающей и поперечной силах и внешнем давлении. Выяснено влияние углов укладки монослоев, нелинейности деформирования на критические нагрузки потери устойчивости оболочки.

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Быкова, И. С., I. S. Bykova, А. Д. Припадчев, A. D. Pripadchev, А. А. Горбунов, and A. A. Gorbunov. "Вопрос компоновки пассажирского салона в рамках автоматизированного проектирования фюзеляжа воздушного судна." Международный журнал "Программные продукты и системы" 9 (April 8, 2016). http://dx.doi.org/10.15827/2311-6749.19.176.

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Mozgovoj, V. F., and V. V. Klochikhin. "ОПЫТ ИЗГОТОВЛЕНИЯ ДЕТАЛЕЙ ФЮЗЕЛЯЖА ВЕРТОЛЁТА ИЗ КОМПОЗИЦИОННЫХ МАТЕРИАЛОВ НА СТАНКАХ С ЧПУ." Технологические системы, no. 89/4 (June 24, 2020). http://dx.doi.org/10.29010/89.6.

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Обосновано, что внедрение высоких технологий и успешная эксплуатация высокоскоростного оборудования с ЧПУ с применением современной инструментальной оснастки при обработке композиционных материалов позволяет успешно развивать украинское вертолётостроение. Исследования, проведенные в производственных условиях, показывают широкие возможности в расширении номенклатуры обрабатываемых деталей из композитных материалов на высокоскоростном оборудовании. Рассмотренные особенности технологии обработки деталей вертолёта могут быть использованы при дальнейших исследованиях в области обработки композиционных материалов и повышения надёжности авиационной техники.

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Алесин, В. С., В. В. Губский, and О. В. Павленко. "Computational investigation of the fuselage shape impact on the pusher thrust." Engineering Journal: Science and Innovation, no. 79 (May 2018). http://dx.doi.org/10.18698/2308-6033-2018-6-1769.

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