HyperSizer Tutorial Analyze Composite...
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© 2011 Collier Research Corp. HyperSizer Tutorial Analyze Composite Laminates Collier Research Corporation Hampton, VA
Transcript of HyperSizer Tutorial Analyze Composite...
© 2011 Collier Research Corp.
HyperSizer Tutorial Analyze Composite Laminates
Collier Research Corporation Hampton, VA
© 2011 Collier Research Corporation
Introduction
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© 2011 Collier Research Corporation
Introduction
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In this example we will show you how to view Laminate properties, using the Laminate form and the Laminate Analysis form, and we will show you how to analyze them. We will also introduce you to the various sections on the Laminate Analysis form.
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Objectives
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1. Analyze Composite Laminates to determine ply-by-ply margins of safety
Important: In order to do this tutorial, it is recommended that you first complete the Quickstart, located in the Getting Started > Tutorials section of the Help Documentation.
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Laminate Analysis
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Open Laminate Form
1. On the Database Explorer Tree, expand “Laminate.”
2. Expand “Collier Laminates.”
3. On “Example Laminate 18 ply”: Right-click | Review Laminate Material.
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Laminate Form
4. Click Analyze (a). This will bring up the Laminate Analysis form.
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The Laminate form is used to manage and edit composite materials.
a
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Laminate Analysis Form
The “Laminate Analysis and Equivalent Orthotropic Properties” form displays the [A], [B], [D] stiffness matrices, their corresponding thermal coefficients, and the equivalent laminate elastic engineering constants and effective failure allowables. Once the form is up, any change in the laminate definition instantaneously changes the results shown on this form. In fact, calculated data is displayed on the fly if the user browses other laminate definitions
Effective laminate elastic engineering constants are derived based on temperature-dependent material properties. In fact, there can be specified a non-linear, through-the-thickness temperature gradient on the laminate. This will cause HyperSizer to interpolate from the material database for each ply’s unique temperature
The Laminate Analysis form computes the equivalent orthotropic properties of a laminate and computes the ply-by-ply margins of safety. The tabs are shown on the following pages.
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Enter User Defined Load
5. In the Options sub-frame User Defined/Allowable Load (a), set Nx value = 1111.
6. Select all of the Failure Theories (b).9
The Laminate form is used to manage and edit composite materials.
a
b
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Failure Analysis Tab
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The Failure Analysis tab shows results for each ply, their associated lowest margin-of-safety (MOS), temperature, material type, limiting failure analysis criteria, and controlling ply location (either the top, middle, or bottom surface of the ply). A check in a box indicates this ply has the lowest margin within the laminate. The user can sort the data in any of the columns of the Failure Analysis tab by simply clicking on a column header. By clicking the MOS column, results are sorted by margin, as shown by the cursor below.
7. Click the Failure Analysis tab.
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Strain Plot Tab
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The Strain Plot tab plots strains in the ply coordinate system. You can click on aline or an item in the legend box to highlight the data points of any particular line.
9. Click the Middle Only (a) checkbox to show only one data point per ply or turnthe checkbox off to show the inner and outer values for each ply.
1 is in the fiber/tape direction, 2 is transverse/perpendicular to the fiber, and 12 isshear. The legend is moveable by clicking and dragging to the desired position.
8. Click the Stain Plot tab.
a
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Stress Plot Tab
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The Stress Plot tab plots stresses in the ply coordinate system. Again, you can click on a line or an item in the legend box to highlight the data points of any particular line.
10.Click the Stress Plot tab.
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MOS Plot Tab
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The MOS Plot tab plots the lowest margin of safety per ply for the given, selected failure criteria.
11.Click the MOS Plot tab.
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Failure Envelope Tab
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The failure envelope is used to back-out effective tension and compression laminate stress/strain allowables. Failure envelope and allowables are temperature dependent.
The Failure Envelope tab plots failure envelopes at 0% shear, 25% shear, and 50% shear. If a combination of loading is outside the circle, then the laminate fails. If inside the circle, then the laminate is good.
12.Click the Failure Envelope tab.
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Failure Envelope Tab
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13.In the Failure Theory (a) sub-frame select one or several of the theories and watch the failure envelope change.
a
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Laminate Analysis Form Options
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Other Options include “Tension” or “Compression” radio buttons (a).
14.Click the Compression radio button and watch the results to the right of the Options box change. Click back to Tension.
There are also radio buttons that let HyperSizer know if the loads are “Limit” or “Ultimate”.
Reference Plane Location can be: Outer Fiber, Laminate Midplane, or Inner Fiber.
15.Click the radio buttons in the Reference Plane Location frame (b) and watch the results to the right of the Options box change. Before continuing, be sure Laminate Midplane is selected.
16.You can change the Reference Plane Offset (c) by typing in the units by which to offset. Type 1.5 and watch ply 1 being chosen on the Failure Analysis tab. Now, type 0 as the Reference Plane Offset.
a
b
c
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Laminate Analysis Form Options
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14. Click the checkbox Show Minimum MOS Analysis Only. (a)This lists only the minimum margin for each ply, instead of all 3 Reference Planes (Outer, Inner, Ply Midplane).
The reference temperature is defined at the bottom of the Options frame (b). HyperSizer will interpolate the material database to determine properties at the reference temperature.
15. The final 3 text boxes allow you to change the Delta T for the Outer Fiber, Inner Fiber and Midplane (c). Change the data in these boxes and watch the results to the right of the Options box change. Do not close this window; it will be used in next example.
16. Look at / keep in mind the note at the bottom of the Options box. “Only isotropic and orthotropic plys are analyzed. Other materials are treated as empty space.”
a
bc
