The Flexural Fatigue Behavior of Honeycomb Sandwich Composites Following Low Velocity Impacts
Abstract
:Featured Application
Abstract
1. Introduction
2. Materials and Methods
2.1. Static Tests
2.2. Impact Tests
2.3. Fatigue Tests
3. Results and Discussion
3.1. Flexural Tests
3.2. Fatigue Tests
3.3. Damping Ratio and Stiffness Reduction
4. Conclusions
- For three-point bending loads, increasing the core height increased the damage load of the specimen. With increased core height, damage was concentrated on the zone affected by the load. For the three core height values, debonding damage was seen between the core and the face sheet; buckling of the cell walls is the main reason for the damage.
- Increasing face sheet thickness increased the flexural strength of specimens for both face sheet materials. This increase was more apparent in specimens of CFRP.
- While performing fatigue tests, the applied load was determined by using the static damage load of the specimen. This restricted the effect of parameters used in the study on fatigue behavior. Application of the same amount of load to all specimens will clarify the effects of these parameters on fatigue behavior.
- Increasing the core height was found to be the parameter that increased fatigue strength of specimens the most, similar to static loading.
- In fatigue tests performed by three-point bending tests, when the loading ratio decreased, the fatigue lives of undamaged and damaged specimens converged.
- The damping ratio—related to the energy absorbed by specimens during fatigue tests and to rigidity—increased with the increasing impact energy. For undamaged and damaged specimens, the damping ratio approached a steady-state and continued its horizontal trend; it decreased when approaching the damage cycle and became a minimum after permanent damage of the specimen.
- For all cycle numbers, the highest damping ratios were observed in specimens with the aluminum face sheet.
- While normalized fatigue cycle approached the 1, stiffness decreases and dramatical stiffness reduction observed at the end of lifetime for all samples.
Author Contributions
Funding
Acknowledgments
Conflicts of Interest
References
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Specimen Codes | Cell Size (D) mm | Face Sheet Material | Core Height (T) mm | Face Sheet Thickness mm (h) |
---|---|---|---|---|
6AL10a | 6.35 | Aluminum | 10 | 0.5 |
6AL10b | 6.35 | Aluminum | 10 | 1 |
6AL10c | 6.35 | Aluminum | 10 | 1.5 |
6AL15b | 6.35 | Aluminum | 15 | 1 |
6AL20b | 6.35 | Aluminum | 20 | 1 |
9AL10b | 9.525 | Aluminum | 10 | 1 |
6CFRP10a | 6.35 | CFRP | 10 | 0.5 |
6CFRP10b | 6.35 | CFRP | 10 | 1 |
6CFRP10c | 6.35 | CFRP | 10 | 1.5 |
Young’s Modulus | Poisson’s Ratio | Tensile Strength (MPa) | |
---|---|---|---|
3M 2216 Adhesive | 565 MPa | 0.47 | 19.88 |
Al-5754 Face Sheet | 70.3 GPa | 0.33 | 245 |
Al-3003 Core | 68.9 GPa | 0.33 | 131 |
E1 (GPa) | E2 (GPa) | ν12 | G12 (GPa) | XT,YT (MPa) | XC, YC (MPa) | S (MPa) | |
---|---|---|---|---|---|---|---|
CFRP Face Sheet | 83.4 | 83.5 | 0.05 | 6.8 | 1008 | 953 | 125 |
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Solmaz, M.Y.; Topkaya, T. The Flexural Fatigue Behavior of Honeycomb Sandwich Composites Following Low Velocity Impacts. Appl. Sci. 2020, 10, 7262. https://doi.org/10.3390/app10207262
Solmaz MY, Topkaya T. The Flexural Fatigue Behavior of Honeycomb Sandwich Composites Following Low Velocity Impacts. Applied Sciences. 2020; 10(20):7262. https://doi.org/10.3390/app10207262
Chicago/Turabian StyleSolmaz, Murat Yavuz, and Tolga Topkaya. 2020. "The Flexural Fatigue Behavior of Honeycomb Sandwich Composites Following Low Velocity Impacts" Applied Sciences 10, no. 20: 7262. https://doi.org/10.3390/app10207262