For large panels, which have to be broken up into elements
for the analysis, the redistribution of internal loads, caused by the change
in element stiffnesses in optimization iterations, must be taken into account.
|Internal FEM module
FEM analysis for large, complex composite structures is computationally
expensive to be performed externally in each optimization iteration.
Internal Finite Element Module is developed and implemented
into COSTADE to determine the internal load redistribution effects.
Internal FEM module generates valid designs and improves
FEA implementation in COSTADE
Full barrel fuselage section design
Fuselage section is modeled by a sandwich type composite
laminate panel with frames along the hoop direction.
Radius of the barrel = 122 in.
Maximum number of plies in the skin = 41.
Number of elements for the FEA = 8x10.
TRI3 Shell elements used in the finite element analysis.
Objective of the optimization = Minimize weight.
Number of design variables = 246.
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