| タイトル | The Influence of Mesh Density on the Impact Response of a Shuttle Leading-Edge Panel Finite Element Simulation |
| 本文（外部サイト） | http://hdl.handle.net/2060/20040200980 |
| 著者（英） | Lyle, Karen H.; Jackson, Karen E.; Fasanella, Edwin L.; Spellman, Regina L. |
| 著者所属（英） | NASA Langley Research Center; Army Research Lab. |
| 発行日 | 2004-11-01 |
| 言語 | eng |
| 内容記述 | A study was performed to examine the influence of varying mesh density on an LS-DYNA simulation of a rectangular-shaped foam projectile impacting the space shuttle leading edge Panel 6. The shuttle leading-edge panels are fabricated of reinforced carbon-carbon (RCC) material. During the study, nine cases were executed with all possible combinations of coarse, baseline, and fine meshes of the foam and panel. For each simulation, the same material properties and impact conditions were specified and only the mesh density was varied. In the baseline model, the shell elements representing the RCC panel are approximately 0.2-in. on edge, whereas the foam elements are about 0.5-in. on edge. The element nominal edge-length for the baseline panel was halved to create a fine panel (0.1-in. edge length) mesh and doubled to create a coarse panel (0.4-in. edge length) mesh. In addition, the element nominal edge-length of the baseline foam projectile was halved (0.25-in. edge length) to create a fine foam mesh and doubled (1.0- in. edge length) to create a coarse foam mesh. The initial impact velocity of the foam was 775 ft/s. The simulations were executed in LS-DYNA version 960 for 6 ms of simulation time. Contour plots of resultant panel displacement and effective stress in the foam were compared at five discrete time intervals. Also, time-history responses of internal and kinetic energy of the panel, kinetic and hourglass energy of the foam, and resultant contact force were plotted to determine the influence of mesh density. As a final comparison, the model with a fine panel and fine foam mesh was executed with slightly different material properties for the RCC. For this model, the average degraded properties of the RCC were replaced with the maximum degraded properties. Similar comparisons of panel and foam responses were made for the average and maximum degraded models. |
| NASA分類 | Aircraft Design, Testing and Performance |
| レポートNO | L-19059
NASA/TM-2004-213501
ARL-TR-3337 |
| 権利 | No Copyright |
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