PSI - Issue 17

Radek Doubrava et al. / Procedia Structural Integrity 17 (2019) 190–197 Radek Doubrava/ Structural Integrity Procedia 00 (2019) 000 – 000

197

8

The results from the optical sensor measurement on the metal test panel (Fig. 8a) show the influence of the secondary impact of remainder of the polystyrene sabot on the test specimen. The time of the secondary impact was estimated from the high-speed camera pictures (Fig. 8b).

5. Conclusion

A comparison between the test and simulation results demonstrates the consistency of the damage initialization predictions in the composite material and the plastic deformation in the metallic material. The application of a new technique for the dynamic displacement measurement using an optical sensor during the impact process provided unique quantitative results used to verify the numerical models. These tests provide important information for design and computational analysis. Testing and numerical model verification based on different impact speeds also provide important generalizations for the application and optimization of both composite and metal structures. Furthermore, the results demonstrate the need to increase the sensor measurement range for applications related to high-speed impact analyses and to eliminate the secondary impact of the remainder of the sabot.

Acknowledgements

This project was developed with the institutional support of the Ministry of Industry and Trade of the Czech Republic whose funds were directed to the development of research organizations.

References

ABAQUS 6.14, 2017. Theory manual, http://abaqus.software.polimi.it/v6.14/ ASTM F320-05, 2005. Standard Test Method for Hail Impact Resistance of Aerospace Transparent Enclosures, ASTM F330 -10, 2010. Standard Test Method for Bird Impact Testing of Aerospace Transparent Enclosures, Běhal, J., J., Zděnek, P., 2018 . Effect of interlaminar flaw on composite panel behaviour under acoustic loading, MATEC Web Conf. Volume 188, , Art. No. 01005, DOI: https://doi.org/10.1051/matecconf/201818801005 Cleary, E., Dolbeer, R., Wright, S., 2005. Wildlife Strikes to Civil Aircraft in the United States 1990-2005, Federal Aviation Administration National Wildlife Strike Database Doubrava, R., 2013. SPH Technigue Application for Fast Impact Simulation, report VZLU R-5841, http://www.vzlu.cz/en/certified-methodology n-met-c488.html, Field, P.R., Hand, Cappelluti, W. G., McMillan, A., Foreman A., Stubbs, D., Willows, M., 2008. Hail Threat Standardization, FINAL report for EASA.2008.OP.25, Hashin, Z., 1981. Failure criteria for unidirectional fiber composites, ASME Journal of Applied Mechanics, Vol. 47, pp. 329-334. Heimbs, S., 2011. Computational Methods for Bird Strike Simulations: A Review. Computers & Structures, Vol. 89 (23), 2093-2112. HexPly®8552, 2017. Product Data http://www.aerospares.hu/files/hexcel/hexply_8552.pdf. Kay, G., 2003. Failure Modeling of Titanium 6Al-4V and Aluminum 2024-T3 With the Johnson-Cook Material Model, DOT/FAA/AR-03/57 Kustron, K., Horak, V., Doubrava, R., Goraj, Z. J., 2018. New hail impact simulation models on composite laminated wing leading edge, Aircraft Engineering and Aerospace Technology, https://doi.org/10.1108/AEAT-02-2018-0089, Liu, J., Li, Y., Gao, X., 2014. Bird strike on a flat plate: Experiments and numerical simulations. Int. J. Imp. Eng., Vol. 70, http://dx.doi.org/10.1016/j.ijimpeng.2014.03006, pp. 21-37 Růžek, R. , Kadlec, M., Tserpes, K., Karachalios E., 2017. Monitoring of compressive behaviour of stiffened composite panels using embedded fibre optic and strain gauge sensors, International Journal of Structural Integrity 8 (1), pp.134-150 Růžek, R., Tserpes, K., Karachalios, Gi annopoulos, V. I., Prentzias, V., 2014. Strain and damage monitoring in CFRP fuselage panels using fiber Bragg grating sensors. Part I: Design, manufacturing and impact testing. Comp. Struct., Vol. 107,doi: 10.1016/j.compstruct.2013.09.053, pp. 726 – 736 Wilbeck, J., 1978. Impact Behavior of Low Strength Projectiles. Air Force Materials Lab, Air Force Wright Aeronautical Labs, Report No. AFML TR-77-134, Wright-Patterson AFB, OH

Made with FlippingBook Digital Publishing Software