Abstract
Multiple-crack on the aircraft structure is a major cause the influences adversely structure reliability and integrity. An approach which considers interaction of cracks and stable tearing is employed to calculate the residual strength of Multiple-Site Damage (MSD) panel. Fracture mechanism finite element model of a certain MSD panel is used to evaluate the residual strength; both fracture toughness and R-curve are considered. On the basis of Weibull distribution of residual strength and normal distribution of load, the residual strength reliability model is developed. Numerical results of 2024-T3 aluminum alloy MSD panels are compared with the test results. The agreement between analysis and experiment is shown to be reasonable. Comparison indicates preliminarily that the proposed approach can give a better prediction and will be useful for investigating MSD panel on aircraft structure.
| Original language | English |
|---|---|
| Pages (from-to) | 195-200 |
| Number of pages | 6 |
| Journal | Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University |
| Volume | 32 |
| Issue number | 2 |
| State | Published - Apr 2014 |
Keywords
- Aircraft
- Aluminum alloys
- Calculations
- Crack propagation
- Crack tips
- Experiments
- Failure mechanical
- Finite element method
- Fracture mechanics
- Fracture toughness
- Mathematical models
- Mathematical transformations
- MSD (Multi-Site Damage) panel
- Normal distribution
- Probability density function
- Reliability
- Reliability analysis
- Reliability model
- Residual strength
- Stress concentration
- Stress intensity factors
- Weibull distribution