Buckling of Composites Under Hot and Wet Environment
Author :
Publisher :
Page : 144 pages
File Size : 12,28 MB
Release : 1984
Category : Buckling (Mechanics)
ISBN :
Author :
Publisher :
Page : 144 pages
File Size : 12,28 MB
Release : 1984
Category : Buckling (Mechanics)
ISBN :
Author : V. Sarma Avva
Publisher :
Page : 140 pages
File Size : 48,49 MB
Release : 1984
Category : Buckling (Mechanics)
ISBN :
Author :
Publisher :
Page : pages
File Size : 11,1 MB
Release :
Category :
ISBN :
This paper deals with the analysis of buckling effects of composites in an hygrothermal environment. It is found from the analysis of various researchers world over that the effect of temperature and moisture which the composite materials are generally subjected to in case of space crafts and all have a considerable effect on the critical load carrying capacity of the composite plates which decreases linearly with uniform increase in moisture content and nonlinearly with increase in temperature. The objective is to check the consistency of above results using different set of material properties of composites and further it within the scope of available resources.
Author : William L. Ko
Publisher :
Page : 32 pages
File Size : 49,45 MB
Release : 1991
Category : Buckling (Mechanics)
ISBN :
Author : G.J. Turvey
Publisher : Springer Science & Business Media
Page : 402 pages
File Size : 25,88 MB
Release : 2012-12-06
Category : Technology & Engineering
ISBN : 9401112282
Contributed by leading authorities in the field from around the world, this text provides a comprehensive insight into buckling and postbuckling. Basic theory, methods of buckling analysis and their application, the effect of external variables such as temperature and humidity on the buckling response and buckling tests are all covered.
Author : Abdul-Hamid Zureick
Publisher : ASTM International
Page : 278 pages
File Size : 33,63 MB
Release : 2002
Category : Carbon fibers
ISBN : 0803128932
From a March 2001 symposium in Phoenix, Arizona, 17 papers consider such topics as tabbed versus untabbed fiber-reinforced composite compression, qualification using a nested experimental design, determining and characterizing imperfections in composite pressure vessels, philosophies for assessing t
Author : K. Vijayaraju
Publisher :
Page : 17 pages
File Size : 41,20 MB
Release : 2002
Category : Buckling load
ISBN :
In typical applications like in the top skin of the wing or in control surfaces of an airframe, laminated composites are often found to be buckling-critical. Under excessive compression loading composite panels may undergo buckling and failure mechanisms would generally involve delamination or fiber breakage. Tapered composite panels with ply drops, when employed in wing skin, are expected to be more prone to the above mode of failure. This is one important area of concern to the designers of composite structures and both analysis and experimental verification of the buckling behavior is recommended as a part of design validation effort. However, data from such analysis are scarce in open literature. In this paper, results of a study on buckling and fracture behavior of laminated Carbon Fiber Composite (CFC) panels containing ply drops are presented. CFC panels of varying thickness with normal and inclined ply drop were tested under compression loading until buckling and ultimate failure. Nearly simply supported boundary conditions at the ends and along the edges were simulated with the help of specially designed test fixtures. Tests were conducted both under room temperature and hot-wet (100°C ± 3 °C and ? 85% RH) environmental conditions. Back-to-back strain gage output and out-of-plane deformation data were recorded and analyzed to determine the critical buckling loads and corresponding mode shapes. Finite element analysis using MSC NASTRAN was also made in order to predict critical buckling loads and corresponding mode shapes. These results were compared with those obtained from experiments and the agreement was found to be good in most cases. It was also found that under hot-wet conditions, both critical buckling loads and failure loads were lower compared to the room temperature values.
Author : Steven J. Hooper
Publisher : ASTM International
Page : 286 pages
File Size : 44,37 MB
Release : 1997
Category : Composite materials
ISBN : 0803124783
Author : Anthony D. Straw
Publisher :
Page : 127 pages
File Size : 23,63 MB
Release : 1985
Category :
ISBN :
An analytical study was conducted to determine the influence of moisture, temperature, and curvature on the bifurcation load of cylindrical, composite panels subjected to a simple shear loading. Two laminate ply orientations, (0/45/-45/90)s and (45/-452)s, were analyzed for six radii, four temperatures, and two initial moisture conditions. The eight-ply composite panels were assumed to be manufactured from a graphite/epoxy, As/3501-5. To evaluate the influence of moisture and temperature, the transverse modulus, E2, and shear modulus, G12, were degraded based on experimental test data for the AS/3501-5 system. Each ply orientation, for a 12 in. panel radius, was evaluated at 20 time/temperature conditions that ranged from 80 to 300 F, and moisture concentrations ranging from a zero moisture content to an equilibrium moisture distribution. The investigation of curvature was conducted only for the (45/-452)s laminate and at a limited number of time/temperature conditions. The bifurcation loads were determined using the STAGS-C1 finite elements shell analysis program. This reduction in the bifurcation load is significantly influenced by the change in curvature at elevated temperatures and moisture content.
Author : AK. Ghosal
Publisher :
Page : 20 pages
File Size : 29,43 MB
Release : 1997
Category : Carbon fiber epoxy composite
ISBN :
Experimental simulation of boundary conditions while carrying out a panel buckling test has been known to be difficult. In this paper, compression buckling tests on 6.0-mm-thick carbon fiber composite (CFC) panels have been described for which a reasonably good simulation of the boundary condition was achieved, especially under the simple supported condition. Carefully designed test fixtures that provided excellent alignment of the panel with the loading axis and adequate lateral stiffness for edge supports during buckling of the CFC panels were used to achieve this goal. Both simply supported and clamped boundary conditions have been studied. Tests in room-temperature-as-received (RT/AR) and hot-wet (H/W) conditions are described. A buckling test on a simply supported panel with prior moisture conditioning was performed under the H/W condition with an environmental test chamber mounted on the test rig to prevent any loss of moisture during the test at 100°C and ?85% relative humidity. Based on these results, a test procedure was developed to identify buckling loads through measurement of out-of-plane displacements rather than relying solely upon longitudinal strain measurement. This procedure facilitated estimation of the buckling load of a hygrothermally aged and simply supported CFC panel under the H/W condition, where accurate strain measurements were found to be rather difficult and at times unreliable. Experimental results were compared with those obtained from finite element analysis with regard to the buckling loads and corresponding mode shapes for the boundary conditions considered. The effect of rounding off the knife edges used for the simply supported condition was specifically studied during FEM analysis and was found to be significant.