Layup optimisation of laminated composite tubular structures under thermomechanical loading conditions using PSO

2021 ◽  
pp. 114483
Author(s):  
Harry Veivers ◽  
Michael Bermingham ◽  
Mitchell Dunn ◽  
Martin Veidt
Keyword(s):  
Laminated Composite ◽  
Loading Conditions ◽  
Tubular Structures ◽  
Thermomechanical Loading

Simulating the thermomechanical loading conditions for ceramic parts in internal-combustion engines

1996 ◽  
Vol 28 (2) ◽  
pp. 115-120
Author(s):  
L. V. Kravchuk ◽  
K. P. Buiskikh ◽  
D. N. Ozeryanyi ◽  
S. A. Zakharov
Keyword(s):  
Internal Combustion Engines ◽  
Internal Combustion ◽  
Combustion Engines ◽  
Loading Conditions ◽  
Thermomechanical Loading

An analytical investigation of the best stacking sequence of a symmetric laminated composite plate weakened by a hole

2018 ◽  
Vol 24 (5) ◽  
pp. 1387-1404 ◽  
Author(s):  
Nirav P Patel ◽  
Dharmendra S Sharma
Keyword(s):  
Inverse Problem ◽  
Composite Plate ◽  
Fitness Function ◽  
Hybrid Genetic Algorithm ◽  
Laminated Composite ◽  
Stacking Sequence ◽  
Loading Conditions ◽  
Laminated Composite Plate ◽  
Variable Approach ◽  
Fiber Arrangement

The investigation of the best set of fiber arrangements of a composite laminated structure under various loading conditions is very challenging and the analytical derivation is also complex when the laminate contains various shaped discontinuities. In this article, the best stacking sequence is investigated by treating it as an inverse problem, in which the best fiber arrangement is predicted considering maximization of the failure strength as an objective function. This inverse problem is solved using the hybrid genetic algorithm that operates the Tsai–Hill quadratic criterion as a fitness function and stacking sequence as design variables. A 4, 8 and 16-layered symmetrical laminated composite plate containing a triangular and square hole is optimized by considering the in-plane loading conditions, and the stresses in the Tsai–Hill quadratic criterion are calculated by an analytical solution of Muskhelishvili’s complex variable approach. The problem of the calculation of stresses and failure strengths from the estimated fiber arrangement data is presented as a forward problem. The effect of hole geometry and loading angle on an optimum design is also presented. The presented approach will be useful as an effective tool to study composites.

Deformation Modeling and Lifetime Prediction of Ni-Base Gas Turbine Blade Alloys Under TMF-Conditions

2014 ◽  
Author(s):  
Stefan Grützner ◽  
Bernard Fedelich ◽  
Birgit Rehmer ◽  
Maria Mosquera
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Creep Damage ◽  
Material Model ◽  
Lifetime Prediction ◽  
Strain Accumulation ◽  
Loading Conditions ◽  
Gas Turbine Blade ◽  
Thermomechanical Loading ◽  
Cyclic Thermomechanical Loading

Under cyclic thermomechanical loading conditions, various effects such as strain accumulation, creep damage, ageing, fatigue etc. may occur in the material of a gas turbine blade. Depending on the loading conditions, all these effects contribute to reduce the lifetime of the component. Subject of the present work is the development of a lifetime model able to discriminate between the different damage mechanisms, as well as the development of a material model to describe the mentioned effects and thus providing the input data for lifetime prediction.

Modeling and simulation of carbon composite ballistic and blast behavior

2019 ◽  
Vol 54 (4) ◽  
pp. 485-499
Author(s):  
Chian-Fong Yen ◽  
Bob Kaste ◽  
Charles Chih-Tsai Chen ◽  
Nelson Carey
Keyword(s):  
Composite Material ◽  
Progressive Failure ◽  
Laminated Composite ◽  
Blast Loading ◽  
Carbon Composite ◽  
Ballistic Impact ◽  
Failure Behavior ◽  
Loading Conditions ◽  
Failure Model ◽  
Carbon Composite Material

The design of the next generation of aeronautical vehicles is driven by the vastly increased cost of fuel and the resultant imperative for greater fuel efficiency. Carbon fiber composites have been used in aeronautical structures to lower weight due to their superior stiffness and strength-to-weight properties. However, carbon composite material behavior under dynamic ballistic impact and blast loading conditions is relatively unknown. For aviation safety consideration, a computational constitutive model has been used to characterize the progressive failure behavior of carbon laminated composite plates subjected to ballistic impact and blast loading conditions. Using a meso-mechanics approach, a laminated composite is represented by a collection of selected numbers of representative unidirectional layers with proper layup configurations. The damage progression in a unidirectional layer is assumed to be governed by the strain-rate-dependent layer progressive failure model using the continuum damage mechanics approach. The composite failure model has been successfully implemented within LS-DYNA® as a user-defined material subroutine. In this paper, the ballistic limit velocity (V50) was first established for a series of laminates by ballistic impact testing. Correlation of the predicted and measured V50 values has been conducted to validate the accuracy of the ballistic modeling approach for the selected carbon composite material. A series of close-in shock hole blast tests on carbon composite panels were then tested and simulated using the LS-DYNA® Arbitrary-Lagrangian-Eulerian (ALE) method integrated with the Army Research Laboratory (ARL) progressive failure composite model. The computational constitutive model has been validated to characterize the progressive failure behavior in carbon laminates subjected to close-in blast loading conditions with reasonable accuracy. The availability of this modeling tool will greatly facilitate the development of carbon composite structures with enhanced ballistic impact and blast survivability.

Hygro-Thermo-Mechanical Vibration and Buckling Analysis of Composite Laminates with Elliptical Cutouts under Localized Edge Loads

2021 ◽  
pp. 2150150
Author(s):  
K. S. Subash Chandra ◽  
T. Rajanna ◽  
K. Venkata Rao
Keyword(s):  
Boundary Conditions ◽  
Composite Laminates ◽  
Mechanical Vibration ◽  
Laminated Composite ◽  
Free Vibrations ◽  
Primary Objective ◽  
Loading Conditions ◽  
Dependent Model ◽  
Hygrothermal Environment ◽  
Hygrothermal Environments

Perforated composite laminates are frequently encountered in multiple engineering applications as sub-components of complicated structures. In many of these applications, the primary objective of using the panel is to resist buckling under diverse environmental and loading conditions. This paper is mainly focused on the vibration and buckling responses of composite laminates with elliptical cutouts subjected to localized edge loads under different hygrothermal environments. Toward this, a nine-noded heterosis plate element has been utilized to discretize the plate by adopting a refined meshing pattern around the elliptical cutout. The geometric nonlinearity has been incorporated to predict free vibrations under the hygrothermal environment. Considering the plethora of applications of composite laminates in hygrothermal conditions, a new temperature/moisture-dependent model is presented by taking into consideration various mechanical loadings. For a given environmental and loading condition, the stress distribution within the perforated panel is highly non-uniform in nature and hence, a novel dynamic approach has been proposed to solve buckling problems by adopting two sets of boundary conditions. A MATLAB program has been developed to investigate the effect of various parameters such as elliptical cutout size, elliptical orientation, elliptical cutout eccentricity, thickness and boundary conditions of the laminated composite plate under diverse hygrothermomechanical loading conditions. A notable difference in the critical buckling load is observed when the locally prestressed perforated panels are subjected to complex hygrothermal environments, especially at larger elliptical cutouts and hence the importance of localized edge loads under hygrothermal environment is emphasized.

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