| タイトル | User's Guide for ENSAERO_FE Parallel Finite Element Solver |
| 本文（外部サイト） | http://hdl.handle.net/2060/20040081034 |
| 著者（英） | Guruswamy, Guru P.; Eldred, Lloyd B. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1999-04-01 |
| 言語 | eng |
| 内容記述 | A 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 replaces 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 multizonal fluid analysis capability. The new substructure code is used to solve the structural finite element equations for each substructure in parallel. NASTRANKOSMIC is utilized as a front end for this code. Its full library of elements can be used to create an accurate and realistic aircraft model. It is used to create the stiffness matrices for each substructure. The new parallel code then uses an iterative preconditioned conjugate gradient method to solve the global structural equations for the substructure boundary nodes. |
| NASA分類 | Aircraft Stability and Control |
| レポートNO | NASA/TM-1999-208781
A-99V0021 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/222010 |
