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Parallel Aeroelastic Analysis Using ENSAERO and NASTRANA high fidelity parallel static structural analysis capability is created and interfaced to the multidisciplinary analysis package ENSAERO-MPI of Ames Research Center. This new module replaced ENSAERO's lower fidelity simple finite element and modal modules. Full aircraft structures may be more accurately modeled using the new finite element capability. Parallel computation is performed by breaking the full structure into multiple substructures. This approach is conceptually similar to ENSAERO's multi-zonal fluid analysis capability. The new substructure code is used to solve the structural finite element equations for each substructure in parallel. NASTRAN/COSMIC is utilized as a front end for this code. Its full library of elements can be used to create an accurate and realistic aircraft mode. It is used to create the stiffness matrices for each sub-structure. The new parallel code then uses an iterative preconditioned conjugate gradient method to solve the global structural equations for the sub-structure boundary nodes. Results are presented for a wing-body configuration.
Document ID
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Eldred, Lloyd B.
(MCAT Inst. Moffett Field, CA United States)
Byun, Chansup
(MCAT Inst. Moffett Field, CA United States)
Guruswamy, Guru P.
(NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
August 19, 2013
Publication Date
January 1, 1999
Publication Information
Publication: HPCCP/CAS Workshop Proceedings 1998
Subject Category
Structural Mechanics
Funding Number(s)
Distribution Limits
Work of the US Gov. Public Use Permitted.
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