scholarly journals Stress-strain state and loss of stability of anisotropic thermal coating under thermal shock

2014 ◽  
Author(s):  
B. A. Lyukshin ◽  
P. A. Lyukshin ◽  
S. A. Bochkareva ◽  
N. Yu. Matolygina ◽  
S. V. Panin
Keyword(s):  
Thermal Shock ◽  
Strain State ◽  
Loss Of Stability ◽  
Stress Strain ◽  
Stress Strain State ◽  
Thermal Coating

Simulating the stress–strain state of a thin plate after a thermal shock

2021 ◽  
Author(s):  
A. V. Sedelnikov ◽  
S. V. Glushkov ◽  
V. V. Serdakova ◽  
M. A. Evtushenko ◽  
E. S. Khnyryova
Keyword(s):  
Temperature Field ◽  
Thermal Shock ◽  
Thin Plate ◽  
Strain State ◽  
Stress Strain ◽  
Homogeneous Plate ◽  
Stress Strain State ◽  
The Impact ◽  
Elastic Elements

The paper is devoted to simulating the impact of a thermal shock on a thin homogeneous plate in the ANSYS package. The assessment of the stress–strain state is carried out and the dynamics of changes in the temperature field of the plate is determined. The obtained results were compared with the data of other authors and can be used when taking into account the thermal shock of large elastic elements of spacecraft.

Simulation of the stress-strain state and stability loss of a thermal barrier coating under thermal shock

2012 ◽  
Vol 15 (1-2) ◽  
pp. 104-111 ◽  
Author(s):  
Pepter A. Lyukshin ◽  
B. A. Lyukshin ◽  
N. Yu. Matolygina ◽  
S. V. Panin
Keyword(s):  
Thermal Shock ◽  
Thermal Barrier Coating ◽  
Strain State ◽  
Stability Loss ◽  
Thermal Barrier ◽  
Stress Strain ◽  
Stress Strain State ◽  
Barrier Coating

scholarly journals Modelling stress-strain state in oxide ceramics under thermal shock

2017 ◽  
Vol 919 ◽  
pp. 012015
Author(s):  
V Promakhov ◽  
I Zhukov ◽  
Ya Dubkova ◽  
V Platov ◽  
N Grunt ◽  
...  
Keyword(s):  
Thermal Shock ◽  
Strain State ◽  
Oxide Ceramics ◽  
Stress Strain ◽  
Stress Strain State

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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