CSAMS is an initial design screening tool for laminated composite structures. It gives rapid parametric results for laminate architecture and simple structural components.
You can enter CSAMS in either of two ways:
Choice 1. Build the laminate first
1. Click Materials and open PTAMS.
PTAMS calculates the cured ply thickness from the material, gsm and fibre volume fraction.
2. Click MSAMS.
When MSAMS is opened, the PTAMS calculations for the material you selected (for example glass fibre or carbon fibre) are automatically made available for you to choose.
- In MSAMS you type in the number of uni-directional plies, the number of 0/90 plies and the number of ±45° plies.
- MSAMS suggests a stacking sequence arrangement for either a bending-stiffness laminate or a shear-stiffness laminate according to the architecture you have selected.
- MSAMS also reports on laminate homogeneity and symmetry, and on minimum ply-type content.
- Note: it is always better to use even numbers of plies unless you specifically want ply symmetry about the mid-plane of a single ply thickness.
- MSAMS then calculates the composite laminate properties (Exm, Eym, Gxy, thickness and density).
3. SLAMS: Click the Geometry (SLAMS) button.
- Select the composite component, load type (point load or uniform distributed load) and end conditions (cantilever, simply supported, etc.).
- The laminate properties you designed in MSAMS are transferred into the geometry form.
4. Check.
that the transferred values (Exm, Eym, laminate thickness and density) are correct.
5. Enter the load.
in kg and the geometry dimensions of the component. The form returns a Reserve Factor (the initial indicator of strength), deflection and mass.
CHOICE 2. SELECT THE COMPONENT FIRST
1. Click the Geometry (SLAMS) button.
Choose the composite component, load type and end conditions first, then enter the dimensions and load.
2. Return to PTAMS and MSAMS.
to define and build the laminate (entering the numbers of uni-directional, 0/90
and ±45° plies as described above). The properties are then transferred into the geometry form.
Additional results available in some modules
Some modules include a form of optimisation that calculates the number of laminates required to meet minimum mass while still satisfying strength and deflection requirements.
Some modules also provide natural frequency results, Classical Lamination Theory (CLT), the ABD matrix mathematics and a Failure Index for further screening.
Future developments
CSAMS is being upgraded. Further analytical modules will be added, and Classical Lamination Theory, ABD matrices and natural frequency results will be extended to more modules in due course.
A complete suite of Lap and T-peel joint designs (mechanical and/or bonded joints) will also become accessible. This module was previously known as JSAMS (Joint Strength Analysis Modules).
IMPORTANT
All results (Reserve Factor, Failure Index, deflection, mass and natural frequency) are screening values only. They should be checked by other means such a testing before being put into use.
CSAMS is not a certified analysis. Always independently check critical results and test the finished component.
Access continues only while the subscription remains paid.