Crash Analysis of UAV Hybrid Composite Fuselage Structure under Different Impact Conditions

Abstract:

Due to the rapid scientific and technological developments in the aerospace industry, the requirement for safety and energy absorption efficiency is increasing, and in order to achieve that target, the analyzing of the sudden crash is required to know how to reduce it. Therefore, the main objective of the present work is to analyze the crashing response of the hybrid composite fuselage structure during different impact landing conditions. Moreover, extract the maximum acceleration at the most important locations in the UAV fuselage where most of the critical system is installed. The explicit non-linear finite element software LS-DYNA/WORKBENCH ANSYS is chosen to simulate the crushing of the referenced and the proposed UAV fuselage and investigate the maximum crushing accelerations responses on the payload under different landing conditions. The numerical results show that strengthen the fuselage structure using hybrid composite material has a notable effect on the energy absorption, and transferred acceleration on the payload. Moreover, the hybrid composite fuselage structure can reduce the transferred acceleration on the payload up to 39.65% in comparison with the metal fuselage. In addition, to study the crash analysis during sudden accidents is very important, in order to find the way to reduce it, but can’t avoid it. Hence, the UAV payload should be arranged to avoid the maximum acceleration.

• Periodical: Materials Science Forum (Volume 953)
• Pages: 88-94
• DOI: https://doi.org/10.4028/www.scientific.net/MSF.953.88
• Online since: May 2019
• Authors: Mohamed Zahran*, Mostafa Abdelwahab
• Keywords: Crash, Hybrid Composite, Impact, Structure, UAV

References

[1] E. Troiani, M. P. Falaschetti, S. Taddia, and A. Ceruti, CFRP Crash Absorbers in Small UAV: Design and Optimization,, SAE Technical Paper 0148-7191, (2015).

DOI: 10.4271/2015-01-2461

[2] N. Yidris, Crash simulation of a composite unmanned aerial vehicle fuselage,, Universiti Putra Malaysia, (2007).

[3] T. Singhanart, C. Srimontok, N. Pisitpan, S. Chitimaworaphan, and W. Mongkhonchaiwiwat, Design and analysis of UAV fuselage,, in Applied Mechanics and Materials, 2012, pp.305-309.

DOI: 10.4028/www.scientific.net/amm.225.305

[4] S. V. Mahantayya KHiremath, Crash Analysis of Unmanned Aerial Vehicle Using FEA , International Journal of Innovative Research in Science, Engineering and Technology, vol. Vol. 5, (2016).

[5] N. Yidris, R. Zahari, D. Majid, F. Mustapha, M. Sultan, and A. Rafie, Crush simulation of woven c-glass/epoxy unmanned ariel vehicle fuselage section,, International Journal of Mechanical and Materials Engineering, vol. 5, pp.260-267, (2010).

[6] P. Leomar, M. Tamre, T. Riibe, T. Vaher, and T. Haggi, Optimal design and analysis of UAV swan fuselage,, in Solid State Phenomena, 2006, pp.91-96.

DOI: 10.4028/www.scientific.net/ssp.113.91

[7] F. Manual, ANSYS, Release 15.0 ANSYS Documentation. ANSYS Inc, Canonsburg, PA,,, ed, (2013).

DOI: 10.1016/b978-0-12-811768-2.00022-5

[8] M. zahran, UAV Structure Improvement for Protection of Critical System,, (2017).

[9] R. N. Jazar and L. Dai, Nonlinear Approaches in Engineering Applications: Advanced Analysis of Vehicle Related Technologies: Springer, (2016).

[10] L. Dai and L. Dai, Nonlinear Approaches in Engineering Applications: Springer New York, (2012).

[11] T. Belytschko, J. I. Lin, and T. Chen-Shyh, Explicit algorithms for the nonlinear dynamics of shells,, Computer methods in applied mechanics and engineering, vol. 42, pp.225-251, (1984).

DOI: 10.1016/0045-7825(84)90026-4

[12] H. C. Kim, D. K. Shin, J. J. Lee, and J. B. Kwon, Crashworthiness of aluminum/CFRP square hollow section beam under axial impact loading for crash box application,, Composite Structures, vol. 112, pp.1-10, (2014).

DOI: 10.1016/j.compstruct.2014.01.042

[13] P. F. Liu and J. Zheng, Progressive failure analysis of carbon fiber/epoxy composite laminates using continuum damage mechanics,, Materials Science and Engineering: A, vol. 485, pp.711-717, (2008).

DOI: 10.1016/j.msea.2008.02.023

[14] M. Esa, P. Xue, M. Zahran, M. Abdelwahab, and M. Khalil, Novel strategy using crash tubes adaptor for damage levels manipulation and total weight reduction,, Thin-Walled Structures, vol. 111, pp.176-188, (2017).

DOI: 10.1016/j.tws.2016.11.018

[15] Q.-Q. S. D.-N. Zhang, C.-J. Xie, F. Liu, A modified Johnson Cook model of dynamic tensile behaviors for 7075-T6 aluminum alloy,, Journal of Alloys and Compounds, vol. 619, pp.186-194, (2015).

DOI: 10.1016/j.jallcom.2014.09.002

[16] L. A. Marcus Menchawi, Modeling of fiberglass reinforced epoxy composites in LS-DYNA. Linköping University, (2014).

[17] B. Simhachalam, K. Srinivas, and C. L. Rao, Energy absorption characteristics of aluminium alloy AA7XXX and AA6061 tubes subjected to static and dynamic axial load,, International Journal of Crashworthiness, vol. 19, pp.139-152, (2014).

DOI: 10.1080/13588265.2013.878974

[18] D. Siromani, Crashworthy design and analysis of aircraft structures: Drexel University, (2013).

[19] S. G. Gupta, M. M. Ghonge, and P. Jawandhiya, Review of unmanned aircraft system (UAS),, technology, vol. 2, (2013).

DOI: 10.2139/ssrn.3451039

[20] P. Fahlstrom and T. Gleason, Introduction to UAV systems: John Wiley & Sons, (2012).

[21] J. Gundlach, Designing unmanned aircraft systems: A comprehensive approach: American Institute of Aeronautics and Astronautics, (2012).

[22] R. Austin, Unmanned aircraft systems: UAVS design, development and deployment vol. 54: John Wiley & Sons, (2011).