HyperSizer for Composites: Insanely Fast Laminate Optimization

HyperSizer for Composites: Insanely Fast Laminate Optimization
HyperSizer for Composites: Insanely Fast Laminate Optimization
95% of users, without user manual, and without instruction, will be
able to import their FEM and produce optimum composite laminates
that satisfy all analyses to all load cases within the first 10 minutes.
Your automatically updated model will have minimum weight and fully
producible laminates with global plies identified. These laminates are
optimum and they are manufacturable as the software creates the ply
shapes layer by layer automatically. The sequenced plies can also be
exported to spreadsheets for import into CAD such as CATIA.
and aerospace OEMs for 20 years for advanced composite
optimization that reduces spacecraft and aircraft weight by 25%.
HyperSizer Composites™ provides cost effective (1/3rd cost) and
rapid optimization of general structures. We have taken 20 years of
aerospace software development and packaged the most enabling
technologies into a very easy to use software product.
The software works fast with large FEMs (millions of
elements) and thousands of load cases. Its ability to
optimize is insanely fast.
With its ease of use and robust optimization, the
software is suitable for the general composites
engineer. This includes industries such as:
Sports (bicycle frames, snowboards, sailboats)
Medical (equipment, leg/foot prosthesis)
Automotive (hoods, body panels, floors, chassis)
Industrial (robotic end effectors)
Aerospace (airplane seats, doors, winglets, flaps)
Aerospace Heritage
HyperSizer Design™ is an airframe engineering
analysis software framework and stress reporting
documentation tool. It has been used by NASA
© Collier Research Corporation www.HyperSizer.com
HyperSizer for Composites: Insanely Fast Laminate Optimization
A wizard steps you through the entire process with a series
of green check marks on the status console to confirm your
current progress. The essential steps are model import,
material selection, FEA solver (Nastran/Abaqus) user
selection of analysis criteria (failure theory such as max strain
or Tsai Wu) and design criteria (such as symmetry and
balance and fabrication preferences), laminate optimization
and sequencing, reporting of analysis results such as
controlling load case, failure mode, and reserve safety
factors, and update of your FEM with optimal laminates.
Laminates are optimized for the shape and size of your
current definition of FEM property zones (if they exist).
You have the option to try different FEM property zones for additional weight savings. If
selected the software optimizes the zone patterns (allowed ply boundaries) and displays them
in the graphics along with their weight savings. The user can view all the possible different
ways ply shapes could be defined on the mesh.
FEA Loads
The optimization uses all of the FEA computed shell element in-plane membrane forces, out
of plane transverse shear forces, and bending moments (Nx, Ny, Nxy, Mx, My, Mxy, Qx, Qy).
They result in ply fiber, transverse to fiber, and shear direction stresses. You can select to
include FEA solver iterations for static, buckling, and frequency runs. As the optimization
redistributes the FEM stiffness’s, the iterations will converge the load paths and eigenvalues
to meet requirements.
Closed form buckling solutions are used with tight integration with FEA buckling solutions.
Buckled mode shape locations are identified on the FEM and their eigenvalues extracted and
used by HyperSizer Composites. Frequency FEA solutions are also used in the optimizations.
Analysis Methods
Many different failure criteria are provided and can be selected by the user. Ply based failures include max strain, max stress, quadratic
methods like Tsai Hahn, and physically based methods such as Hashin and Puck 2D and 3D. Laminate based aerospace damage tolerant
criteria are also provided such as Open Hole Compression (OHC), Compression after Impact (CAI), and Barely Visible Impact Damage (BVID).
Material Allowables
The complete offering of
strength failure criteria
though is only part of the
story. Just as important are
the associated material
allowables and correction
factors. The user can create
materials and be able to
according to their OEM and
Tier 1 approaches.
Design Criteria
You can select laminate
design criteria such as
symmetric and balanced
layups, as well as fabrication
techniques such as full body
plies across the part surface.
These are the first sets of
plies placed in the tool.
Cut Plane
Cross Section Plies
© Collier Research Corporation www.HyperSizer.com
Cross Section Cut
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