| タイトル | Dynamics Impact Tolerance of Shuttle RCC Leading Edge Panels Using LS-DYNA |
| 本文（外部サイト） | http://hdl.handle.net/2060/20050220706 |
| 著者（英） | Lyle, Karen H.; Melis, Matthew E.; Jones, Lisa E.; Spellman, Regina L.; Hardy, Robin C.; Stockwell, Alan E.; Carney, Kelly S.; Fasanella, Edwin L.; Jackson, Karen E. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2005-01-01 |
| 言語 | eng |
| 内容記述 | This paper describes a research program conducted to enable accurate prediction of the impact tolerance of the shuttle Orbiter leading-edge wing panels using physics-based codes such as LS-DYNA, a nonlinear, explicit transient dynamic finite element code. The shuttle leading-edge panels are constructed of Reinforced-Carbon-Carbon (RCC) composite material, which is used because of its thermal properties to protect the shuttle during reentry into the Earth's atmosphere. Accurate predictions of impact damage from insulating foam and other debris strikes that occur during launch required materials characterization of expected debris, including strain-rate effects. First, analytical models of individual foam and RCC materials were validated. Next, analytical models of foam cylinders impacting 6- in. x 6-in. RCC flat plates were developed and validated. LS-DYNA pre-test models of the RCC flat plate specimens established the impact velocity of the test for three damage levels: no-detectable damage, non-destructive evaluation (NDE) detectable damage, or visible damage such as a through crack or hole. Finally, the threshold of impact damage for RCC on representative Orbiter wing panels was predicted for both a small through crack and for NDE-detectable damage. |
| NASA分類 | Composite Materials |
| レポートNO | AIAA Paper 2005-3631 |
| 権利 | Copyright, Distribution under U.S. Government purpose rights |
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