Soloveichik Y.G.,Novosibirsk State Technical University |
Persova M.G.,Novosibirsk State Technical University |
Vagin D.V.,Novosibirsk State Technical University |
Epanchintseva T.B.,Novosibirsk State Technical University |
And 3 more authors.
Applied Thermal Engineering | Year: 2016
In the paper, the approach to the finite element modeling of the thermoelastic behavior of the composite-made structures at high time-variable thermal and mechanical loads is proposed. This approach makes it possible to perform the computer simulation without homogenization of composite laminates, which can be made of different materials and have various stacking sequences of plies. The developed approach can be applied not only to plates but also to 3D structures with conical or cylindrical surfaces and allows the detailed study of longitudinal and transverse stresses distributions in plies. The developed approach has been applied to studying the thermoelastic behavior of the hypersonic flight vehicle nose caps, the walls of which are made of different composite laminates. The computer simulation has been performed along the flight trajectory at time-variable (during the flight of the hypersonic vehicle) Mach numbers and different angles of attack. © 2016 Elsevier Ltd. All rights reserved.
Stepanova L.N.,Siberian Aeronautical Research Institute Named After S A Chaplygin |
Chernova V.V.,Novosibirsk State University |
Ramazanov I.S.,Siberian Aeronautical Research Institute Named After S A Chaplygin
Russian Journal of Nondestructive Testing | Year: 2015
The results of static tests of specimens that were made from carbon fiber reinforced plastic with a honeycomb filler according to acoustic emission (AE) and strain-gauge measurement are given. When using the two-lag method, the stable locations of AE signals are obtained, which indicates the development of fatigue cracks. The dependences between the main informative parameters of AE signals and features of the destruction of a material are analyzed. According to strain-gauge measurement data, the values of the failure stress are determined. © 2015, Pleiades Publishing, Ltd.
Zheleznov L.P.,Siberian Aeronautical Research Institute Named After S A Chaplygin |
Kabanov V.V.,Siberian Aeronautical Research Institute Named After S A Chaplygin |
Boiko D.V.,Siberian Aeronautical Research Institute Named After S A Chaplygin
Journal of Applied Mechanics and Technical Physics | Year: 2012
A finite-element method for solving problems of nonlinear deformation and stability of nonuniformly discretely reinforced noncircular cylindrical shells is considered. An effective computer algorithm for the study of shells is developed. Stability of stringer cylindrical shells with an elliptical cross section in transverse bending is examined. The effect of ellipticity, nonlinearity of shell deformation at the subcritical stage, reinforcement discreteness, and heterogeneity on shell stability is determined. © 2012 Pleiades Publishing, Ltd.