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УДК 629.783
ИССЛЕДОВАНИЕ ВЛИЯНИЯ ГЕОМЕТРИЧЕСКИХ И УПРУГИХ ПАРАМЕТРОВ НА ЖЕСТКОСТЬ КОНСТРУКЦИИ КОРПУСА КА*
А. П. Попова
Консультант по иностранному языку - Т. В. Стрекалёва
Сибирский государственный университет науки и технологий имени академика М. Ф. Решетнева
Российская Федерация, 660037, г. Красноярск, просп. им. газ. «Красноярский рабочий», 31
E-mail: [email protected]
Выполнено численное исследование влияния геометрических параметров корпуса на жесткость конструкции. Численное моделирование выполнено в пакете Femap.NXNastran. Полученные результаты могут быть использованы при проектировании конструкции корпуса космического аппарата.
Ключевые слова: численное моделирование, корпус, частота колебаний.
THE STUDY OF THE INFLUENCE OF GEOMETRIC PARAMETERS ON THE RIGIDITY OF A SPACECRAFT BODY
A. P. Popova Consultant in a foreign language - T. V. Strekaleva
Reshetnev Siberian State University of Science and Technology 31, Krasnoyarsky Rabochy Av., Krasnoyarsk, 660037, Russian Federation E-mail: [email protected]
The numerical modeling of influence of geometrical parameters on the spacecraft body stiffness is performed in this article. The numerical simulation is performed with the use of the Femap.NX Nastran. The results obtained in this study may be used while designing a spacecraft body.
Keywords: numerical modeling, spacecraft body, oscillation frequency.
Sandwich structures are widely used in aircraft, shipbuilding and many other industries. Three-layer honeycomb structures are used for the manufacture of fuselage fairing, shells of the payload bays of launch vehicles, transitional conical adapters to embed payload into the main compartments of rockets, etc.
The wide use of the items with sandwich structures is caused by their high strength and stiffness characteristics with a relatively small mass, as well as good vibration and radio characteristics, sound and thermal insulation properties [1] .
The paper deals with the new design of a spacecraft body. The aim of the work is to assess the influence of geometric parameters of a body on the rigidity of the structure.
The model of the spacecraft body is a composite structure of three-layer panels rigidly connected to each other (Fig. 1). The main dimensions are the height of the body L = 4 m and the diameter of the body d = 1,2 m.
The geometric model of the spacecraft body is created in the Femap software. Modeling of three-layer panels was carried out by the Laminate finite element. Each three-layer panel is formed by two carrier layers of carbon fiber with elastic modulus E = 70 GPa with the thickness t and aluminum honeycomb core with the thickness h. The variable parameters for the calculation are the elastic
* The work was supported by the Ministry of Education and Science of the Russian Federation on the Federal targeted project, agreement No. 14.575.21.0144.
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characteristics of the bearing layers of the panels, the thickness of the panels and the width of the vertical panels of the body.
The lower edges of the housing were rigidly fixed to simulate its connection to the payload adapter. To assess the rigidity of the structure, the modal analysis of the structure was carried out. As a result of the calculation, the frequencies of natural oscillations of the spacecraft body for different variants of design changes are obtained [2; 3]. The first bending and torsional vibration forms are shown in fig. 2 and fig. 3.
Fig. 1. The construction of the hull of spacecraft
r
Fig. 2. The first bending mode shape
Fig. 3. The first torsional mode shape
The results of the calculation are presented in Table.
The results of the calculation
Changes to the model The first flexural frequency, Hz
The elastic modulus of the bearing layers - 70 GPa The thickness of the bearing layers - 0,3 mm The thickness of the bearing layers - 0,5 mm The thickness of the bearing layers - 01 mm 11,66 12,22 12,15
The width of the vertical panels is increased 13,1
The modulus of elasticity of the bearing layers is increased by 2 The thickness of the bearing layers - 0,3 mm The thickness of the bearing layers - 0,5 mm The thickness of the bearing layers - 1 mm 15,45 15,87 15,33
Increasing the thickness of the vertical panels The thickness of the bearing layers - 0,3 mm The thickness of the bearing layers - 0,5 mm The thickness of the bearing layers - 1 mm 14.1 15.2 15,5
The analysis of the results presented in the table allows us to note that the material of the bearing layers, as well as their thickness, have the greatest impact on the rigidity of the structure. The increase in stiffness can be achieved by changing the thickness of the panels included in the design as well. That will lead to the increase in the weight of the body. The obtained results can be used in the design of a spacecraft hull structure.
References
1. Panin V. F., Gladkov Yu. A. Konstrukcii zapolnitelem : spravochnik. Moskva, Mashinostroenie, 1991, 272 s.
2. Shimkovich D. G. Raschet konstrukcij v MSC/NASTRAN for Windows. Moskva, DMK Press, 2003, 448 s.
3. Rychkov S. P. Modelirovanie konstrukcij v srede Femap with NX Nastran. Moskva, DMK Press, 2013, 784 s.
© Попова А. П., 2019
