scholarly journals Mathematical simulation of stress-strain state of loaded rods with account of transverse bending

2019 ◽  
Vol 1260 (10) ◽  
pp. 102002 ◽  
Author(s):  
Sh Anarova ◽  
Sh Ismoilov
Keyword(s):  
Mathematical Simulation ◽  
Strain State ◽  
Stress Strain ◽  
Stress Strain State ◽  
Transverse Bending

scholarly journals Calculated cross-sectional model and stages of the stress-strain state of the wood element for transverse bending

2019 ◽  
Author(s):  
Svyatoslav S. Gomon ◽  
Svyatoslav Gomon ◽  
Victor Karavan ◽  
Petro Gomon ◽  
Justyna Sobczak-Piąstka
Keyword(s):  
Strain State ◽  
Stress Strain ◽  
Cross Sectional ◽  
Stress Strain State ◽  
Transverse Bending ◽  
Sectional Model

Mathematical Simulation of Cramped Bending of Sheet Parts Using Finite Element Analysis

2016 ◽  
Vol 685 ◽  
pp. 186-190 ◽  
Author(s):  
Е.V. Eskina ◽  
E.G. Gromova
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Mathematical Simulation ◽  
Process Parameters ◽  
Strain State ◽  
Basic Process ◽  
Ansys Software ◽  
Stress Strain ◽  
Element Analysis ◽  
Stress Strain State

The paper describes the method of manufacture of profiles in cramped bending conditions using polyurethaneThe scope of studies included stress-strain state of elastic die and parent sheet, as well as the influence of the basic process parameters on characteristics of the produced items using ANSYS software.

Research on Nonlinear Deformation and Stability of an Aircraft Fuselage Composite Section under Transverse Bending

2021 ◽  
pp. 106-116
Author(s):  
L.P. Zheleznov ◽  
A.N. Seriosnov
Keyword(s):  
Composite Material ◽  
Strain State ◽  
The Finite Element Method ◽  
Stress Strain ◽  
Aircraft Fuselage ◽  
Stress Strain State ◽  
Classical Formulation ◽  
Reinforced Composite ◽  
Transverse Bending ◽  
Composite Section

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.

ANALYTICAL DESCRIPTION OF THE INCLINED CRACK TRAJECTORY BY THE METHOD OF NONLINEAR DEFORMATION MODEL

2017 ◽  
Vol 7 (3) ◽  
pp. 14-18
Author(s):  
Alexandr A. SUVOROV ◽  
Valery B. FILATOV
Keyword(s):  
Reinforced Concrete ◽  
Nonlinear Deformation ◽  
Strain State ◽  
Deformation Model ◽  
Inclined Crack ◽  
Stress Strain ◽  
Crack Trajectory ◽  
Stress Strain State ◽  
Transverse Bending ◽  
Nonlinear Deformation Model

The article proposes an analytical solution to determine the trajectory of inclined crack with the use of nonlinear deformation model in the area of the transverse bending of a reinforced concrete beam. The use of nonlinear deformation model for the analysis of stress-strain state of the beam in the zone of the transverse bending allows to determine the coordinates of the inclined crack trajectory, the position of its vertex, and the angle of inclination to the longitudinal axis of the beam. It is then possible to move from the empirical dependences for calculating the strength of the inclined sections to precise analytical techniques. The proposed algorithms calculate and analyze the stress-strain state of reinforced concrete beams create preconditions for the implementation of the physical model of a power resistance of reinforced concrete elements under transverse bending.

scholarly journals The effect of shear deformations on the stressed state of the wooden elements of the composite section on inclined metal rods

2019 ◽  
Vol 97 ◽  
pp. 04028
Author(s):  
Vladimir Linkov
Keyword(s):  
Cross Section ◽  
Strain State ◽  
Normal Stresses ◽  
Shear Deformations ◽  
Stress Strain ◽  
Flexible Links ◽  
Stress Strain State ◽  
Transverse Bending ◽  
Composite Section ◽  
Wooden Structures

Wooden structures of composite cross-section can be made on flexible links in the form of inclined metal rods (NMS) without the use of glue. The compliance of joints is manifested in the shear deformations of the elements to be joined and reduces the carrying capacity of the composite wooden structures. The article discusses the effect of compliance of NMS-compounds in the form of inclined screwed rods on the stress-strain state of the wooden structures of the composite section. The results of tests for transverse bending of composite wooden elements of natural dimensions are presented. The effect of deformations of mutual shear of joints on deflections on normal stresses in the middle of the span of structures and stresses in inclined screwed rods is considered. It was established experimentally that a linear dependence of the form is observed between shear deformations and other parameters of the stress-strain state of structures Y = a*X + b, increase in shear deformation of NMS-compound on screwed rods on 1 mm leads to an increase in deflections, stresses in the construction of a composite section and in inclined rods on 8,39 mm, 0,24 MPa и на 20,8 MPa respectively.

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.

Sign in / Sign up

Export Citation Format

Share Document