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A Sixteen Node Shell Element with a Matrix Stabilization Scheme.
Interim rept. Oct 86-Mar 87,
MARYLAND UNIV COLLEGE PARK DEPT OF AEROSPACE ENGINEERING
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A sixteen node shell element is developed using a matrix stabilization scheme based on the Hellinger-Reissner principle with independent strain. Initially the assumed independent strain is divided into a lower order part and a higher order part. The stiffness matrix corresponding to the lower order assumed strain is equivalent to the stiffness matrix of the assumed displacement model element with the reduced integration scheme. The spurious kinematic modes of the element are suppressed by introducing a stabilization matrix associated with a judiciously chosen set of higher order assumed strain fields. Numerical results show that this element is free of locking even for very thin plates and shells. Author
APPROVED FOR PUBLIC RELEASE