Stress-strain state of an orthotropic plate under pulse loading

2018 ◽  
Author(s):  
I. V. Scherbakov ◽  
B. A. Lukshin ◽  
S. V. Panin
Keyword(s):  
Orthotropic Plate ◽  
Strain State ◽  
Pulse Loading ◽  
Stress Strain ◽  
Stress Strain State

scholarly journals Nonlinear deformation of circular discrete ribbed plate under influence of pulse loading

2021 ◽  
Vol 264 ◽  
pp. 02018
Author(s):  
Rustam Khalmuradov ◽  
Utkir Nishonov
Keyword(s):  
Numerical Method ◽  
Geometric Nonlinearity ◽  
Nonlinear Deformation ◽  
Strain State ◽  
Circular Disc ◽  
Pulse Loading ◽  
Stress Strain ◽  
Pulsed Loading ◽  
Stress Strain State ◽  
Unit Function

The stress-strain state of a circular disc, discretely finned in a circle, under the influence of the pulse loading, is numerically investigated. Thus the geometric nonlinearity between displacement and deformation is taken into account. The structure consists of boarding and reinforced ribs, the materials of which are the same and obey Hooke's law. The sections of the ribs are constant. The height of the ribs and their locations are specified using a unit function. It is considered that the plate is deformed under the influence of the pulsed loading. A numerical method is used to solve the problem.

scholarly journals Comparative statement analysis of span structures with a reinforced concrete and orthotropic plate under the exposure of solar radiation

2021 ◽  
Vol 263 ◽  
pp. 03020
Author(s):  
Sergey Gridnev ◽  
Igor Podlesnykh ◽  
Aleksandr Rezunov ◽  
Rinat Mukhtarov
Keyword(s):  
Finite Element ◽  
Temperature Field ◽  
Reinforced Concrete ◽  
Solar Radiation ◽  
Orthotropic Plate ◽  
Strain State ◽  
Field Measurements ◽  
Stress Strain ◽  
Steel Reinforced Concrete ◽  
Stress Strain State

Carried out a comparative analysis especially the exposure to solar radiation on the stress-strain state (SSS) of span structures with orthotropic slabs of reinforced concrete. Determine the character limit of the temperature distribution in the elements of the two types of spans according to the results of field measurements. Conducted calculation of Stress-Strain State on specific cases of solar radiation with the use of the developed finite element (FE) models of two types of span structures in the platform LIRA SAPR. The results of SSS features obtained for a steel-reinforced concrete superstructure and a metal superstructure with an orthotropic slab are compared. It is shown that the uneven daytime change in the temperature field under the influence of solar radiation has a significantly different nature of effect on the stress-strain state of elements of metal and steel-reinforced concrete span structures.

КОНСТРУКТИВНО-ТЕХНОЛОГІЧНІ ОСОБЛИВОСТІ ХВОСТО-ВИХ БАЛОК СІТЧАСТОГО ТИПУ З ПОЛІМЕРНИХ КОМПО-ЗИЦІЙНИХ МАТЕРІАЛІВ ВЕРТОЛЬОТІВ ТРАНСПОРТНОЇ КАТЕГОРІЇ

2020 ◽  
pp. 15-30
Author(s):  
А. Г. Гребеников ◽  
И. В. Малков ◽  
В. А. Урбанович ◽  
Н. И. Москаленко ◽  
Д. С. Колодийчик
Keyword(s):  
Finite Element ◽  
Strain State ◽  
Layer Structure ◽  
Metal Structure ◽  
Element Model ◽  
Stress Strain ◽  
Element Analysis ◽  
Mesh Structure ◽  
Stress Strain State ◽  
Mesh Structures

The analysis of the design and technological features of the tail boom (ТB) of a helicopter made of polymer composite materials (PCM) is carried out.Three structural and technological concepts are distinguished - semi-monocoque (reinforced metal structure), monocoque (three-layer structure) and mesh-type structure. The high weight and economic efficiency of mesh structures is shown, which allows them to be used in aerospace engineering. The physicomechanical characteristics of the network structures are estimated and their uniqueness is shown. The use of mesh structures can reduce the weight of the product by a factor of two or more.The stress-strain state (SSS) of the proposed tail boom design is determined. The analysis of methods for calculating the characteristics of the total SSS of conical mesh shells is carried out. The design of the tail boom is presented, the design diagram of the tail boom of the transport category rotorcraft is developed. A finite element model was created using the Siemens NX 7.5 system. The calculation of the stress-strain state (SSS) of the HC of the helicopter was carried out on the basis of the developed structural scheme using the Advanced Simulation module of the Siemens NX 7.5 system. The main zones of probable fatigue failure of tail booms are determined. Finite Element Analysis (FEA) provides a theoretical basis for design decisions.Shown is the effect of the type of technological process selected for the production of the tail boom on the strength of the HB structure. The stability of the characteristics of the PCM tail boom largely depends on the extent to which its design is suitable for the use of mechanized and automated production processes.A method for the manufacture of a helicopter tail boom from PCM by the automated winding method is proposed. A variant of computer modeling of the tail boom of a mesh structure made of PCM is shown.The automated winding technology can be recommended for implementation in the design of the composite tail boom of the Mi-2 and Mi-8 helicopters.

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