|
| Simulation and Experimental Verification Composite Structure of Empennage Leading Edge against Bird Impact |
| Received:July 21, 2020 Revised:July 22, 2020 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7643/issn.1672-9242.2020.09.026 |
| KeyWord:bird impact composite material numerical simulation constitutive model |
| Author | Institution |
| KONG Ling-yong |
Shanghai Aircraft Design and Research Institute, Shanghai , China |
| LI Na |
Shanghai Aircraft Design and Research Institute, Shanghai , China |
| WU Zhi-bin |
Shanghai Aircraft Design and Research Institute, Shanghai , China |
|
| Hits: |
| Download times: |
| Abstract: |
| The work aims to carry out the simulation analysis and experimental verification to the bird impact resistance of the leading edge structure of composite empennage according to the requirements of airworthiness standards CCAR25.631. The experiment matrix was designed to obtain the dynamic mechanical property parameters of the composite according to the simulation requirements of composite against bird impact, and the dynamic mechanical property test and constitutive model parameter calibration were carried out. Based on the calibrated composite constitutive model parameters, the bird impact resistance of the leading edge structure of the empennage was simulated and verified by experiments. The good consistence between the experiment results and the simulation results showed that the bird impact numerical simulation model established could reasonably predict the damage of the leading edge structure of the empennage. Therefore, the simulation analysis method verified by test matrix and experiment for composite against bird impact has a certain guiding role in the bird impact resistance design of aircraft structures. |
| Close |