Linear Elastic Laminate Analysis Problem: NPIB

Submit batch job to compute stresses in a thin [0/90/45/-45]s "Type-II"
Graphite/Epoxy laminated composite plate
Instructions for using this form:
    1. Enter appropriate numbers in the boxes,
    2. enter your email address,
    3. click on submit, and
    4. wait for results to be returned to your email. (this will take about 10 seconds)
  1. Web location of results: lelpa.out file will be sent to your email address.
  2. If your email does not provide direct email links, copy and paste the web address: http://www.jwave.vt.edu/output/lelpat2_"unique date-time"/lelpa.html from the email into your web browser Location: window and look at this file to see if the job ran correctly.
  3. If the job ran correctly you can now download files from your web browser to your computer for archiving (a 4.6Gbyte read/write optical disk is available for each student to use in the SMVC for archiving large simulation files).
  4. If you submit the form "as-is", a sample of results has been archived in the directory: http://www.jwave.rkriz.net/output/ARCHIVE_Examples_SAVE/lelpat2_10-23-2000-8:37:10:645
    Select lelpat2.html to see a summary of the results.
Results of this 2D stress calculations are compared with the 3D stresses predicted by module09 and module10.

The figure below begins to define terms used in Linear Elastic Laminate Plate Analysis (LELPA) problem and the "Free-Edge Problem". LELPA uses the Kirchoff approximation for thin plates hence all stress associated with the z-direction are neglected. To put it simply, LELPA analysis can only predict stresses and strains within the x-y plane of each layer far from the free edge, whereas the Free-Edge Problem calculates the full three-dimensional state of stress as the differential stress element, shown in the figure below, approaches the Free-Edge.

Although the LELPA problem assumes all stresses in the z-direction are zero, a simplified model approximates the normal stress in the z-direction. The other shear stresses in the xz and yz planes are not calculated.

At present the form can be used by students who are already familar with laminated plate theory. For those already familar with with laminated plate analysis the form and output of results should be usable. Background information is provided that will introduce the student to thin laminated plate analysis.