Comparative study on compressive mechanical characteristics of X-shape and pyramidal trussed fillers

Aeronautical and Space-Rocket Engineering

Design, construction and manufacturing of flying vehicles


DOI: 10.34759/vst-2021-2-107-114

Аuthors

Mousavi Safavi S. M.*, Garipov L. A.**, Kluev S. V.***, Yusupov I. R.****

Kazan National Research Technical University named after A.N. Tupolev, 10, Karl Marks str., Kazan, 420111, Russia

*e-mail: sm.mousavi.s@gmail.com
**e-mail: lingar777@mail.ru
***e-mail: 11sergey93@mail.ru
****e-mail: xminusx@mail.ru

Abstract

A wide variety of spatial-truss structures, including pyramidal and X-type trussed cores was developed at present in attempts to create multifunctional core materials of the three-layer structures of aerospace purpose. Computational and optimization methods of these typical trussed cores’ characteristics were considered in many scientific studies. However, very few comparative studies of such core materials mechanical characteristics were conducted. The presented article compares compressive mechanical characteristics of the X-type and pyramidal trussed cores by both analytical and experimental methods. In experimental phase of the study, the two samples of three-layer structures were produced: one with the pyramidal core and the other with the X-type core, to determine the ultimate compressive strength.

3D-models of the samples were designed with the SOLIDWORKS software for manufacturing. Sketches were obtained, and pattern cutting of flat elements was performed based on these models. Further manufacturing was being perpetrated by the flat figures cutting from the aluminum sheet on the laser-cutting machine. Samples for the experiment were assembled from the cut elements. The flat elements fixing with each other is being brought about by the «spike-groove» technique to simplify assembly operations. The assembled samples of the three-layer panels were tested alternately under similar conditions, on the same machine tool. Further, based on the results of compressive testing the «stress-deformation» diagram for both cores was obtained and analyzed. From these diagrams, critical compressive stress and stiffness of the cores were determined. The results of the conducted experiments are in good agreement with the results of analytical calculations. The obtained results demonstrate that with equal relative densities of the cores and similar slope angles of the cores the generalized critical stress of the X-type trussed core cannot be less that the generalized critical compressive stress of the pyramidal trussed core (and at the small relative densities it can be four times more). However, under the above said conditions their generalized compressive stiffness is the same in all cases.

Keywords:

truss core material relative density, X-type truss core material, pyramidal truss core material, generalized compressive stiffness, generalized critical compressive stress

References

  1. Wadley H.N.G. Multifunctional periodic cellular metals. Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences, 2006, vol. 364, no. 1838, pp. 31-68. DOI: 10.1098/rsta.2005.1697

  2. Gainutdinov V.G., Abdullin I.N., Musavi Safavi S.M. Izvestiya vysshikh uchebnykh zavedenii. Aviatsionnaya tekhnika, 2016, no. 1, pp. 59-63.

  3. Gainutdinov V.G., Musavi Safavi S.M., Abdullin I.N. Vestnik Kazanskogo gosudarstvennogo tekhnicheskogo universiteta im. A.N. Tupoleva, 2015, vol. 71, no. 2, pp. 11-15.

  4. Musavi Safavi S.M. Vestnik Samarskogo universiteta. Aerokosmicheskaya tekhnika, tekhnologii i mashinostroenie, 2019, vol. 18, no. 3, pp. 99-108. DOI: 10.18287/2541-7533-2019-18-3-99-108

  5. Khaliulin V.I., Gimadiev R.Sh., Markovtsev V.A., Levshonkov N.V. Vestnik Samarskogo universiteta. Aerokosmicheskaya tekhnika, tekhnologii i mashinostroenie, 2019, vol. 18, no.4, pp. 169-182. DOI: 10.18287/2541-7533-2019-18-4-169-182

  6. Shabalov A.V., Khaliulin V.I., Gimadiev R.Sh., Levshonkov N.V. Izvestiya vysshikh uchebnykh zavedenii. Aviatsionnaya tekhnika, 2019, no. 2, pp. 108-117.

  7. Bokhoeva L.A., Baldanov A.B., Chermoshentseva A.S. Optimal structure of multi-layer wing console of unmanned aerial vehicle with experimental validation. Aerospace MAI Journal, 2020, vol. 27, no. 1, pp. 65-75. DOI: 10.34759/vst-2020-1-65-75

  8. Abdullin I.N. Vestnik Kazanskogo gosudarstvennogo tekhnicheskogo universiteta im. A.N. Tupoleva, 2015, vol. 71, no. 1, pp. 5-11.

  9. Zok F.W., Waltner S.A., Wei Z., Rathbun H.J., McMeeking R.M., Evans A.G. A protocol for characterizing the structural performance of metallic sandwich panels: application to pyramidal truss cores. International Journal of Solids and Structures, 2004, vol. 41, no. 22-23, pp. 6249-6271. DOI: 10.1016/j.ijsolstr.2004.05.045

  10. Queheillalt D.T., Wadley H.N.G. Titanium alloy lattice truss structures. Materials & Design, 2009, vol. 30, no. 6, pp. 1966-1975. DOI: 10.1016/j.matdes.2008.09.015

  11. Queheillalt D.T., Wadley H.N.G. Pyramidal lattice truss structures with hollow trusses. Materials Science and Engineering: A, 2005, vol. 397, no. 1-2, pp. 132–137. DOI: 10.1016/j.msea.2005.02.048

  12. Rathbun H.J., Wei Z., He M.Y., Zok F.W., Evans A.G., Sypeck D.J., Wadley H.N.G. Measurement and simulation of the performance of a lightweight metallic sandwich structure with a tetrahedral truss core. Journal of Applied Mechanics, 2004, vol. 71, no. 3, pp. 368-374. DOI: 10.1115/1.1757487

  13. Woods B.K.S., Hill I, Friswell M.I. Ultra-efficient wound composite truss structures. Composites Part A: Applied Science and Manufacturing, 2016, vol. 90, pp. 111-124. DOI: 10.1016/j.compositesa.2016.06.022

  14. Ryabov A.A., Romanov V.I., Maslov E.E., Strelets D.Yu., Kornev A.V., Ivanov A.I. Comparative analysis impulse deformation of aircraft structure elements made of aluminum alloy and composite material. Aerospace MAI Journal, 2015, vol. 22, no. 2, pp. 152-161.

  15. Tudupova A.N., Strizhius V.E., Bobrovich A.V. Computational and experimental evaluation of fatigue life characteristics of the transport category aircraft composite wing panels. Aerospace MAI Journal, 2020, vol. 27, no. 4, pp. 21-29. DOI: 10.34759/vst-2020-4-21-29

  16. Gregg C.E., Kim J.H., Cheung K.C. Ultra-Light and Scalable Composite Lattice Materials. Advanced Engineering Materials, 2018, vol. 20, no. 9. DOI: 10.1002/adem.201800213

  17. Gurley A., Beale D., Broughton R., Branscomb D.The Design of Optimal Lattice Structures Manufactured by Maypole Braiding. Journal of Mechanical Design, 2015, vol. 137, no. 10, pp. 101401 (8 pages). DOI: 10.1115/1.4031122

  18. Takamoto K., Ogasawara T., Kodama H. et al. Experimental and numerical studies of the open-hole compressive strength of thin-ply CFRP laminates. Composites Part A: Applied Science and Manufacturing, 2021, vol. 145, p. 106365. DOI: 10.1016/j.compositesa.2021.106365

  19. Ju S., Jiang D.Z., Shenoi R.A., Xiao J.Y. Flexural properties of lightweight FRP composite truss structures. Journal of Composite Materials, 2011, vol. 45, no. 19, pp. 1921-1930. DOI: 10.1177/0021998311410237

  20. Jiang Y. On the Compression Mechanism of the Composite Lattice Structures. Composites and Advanced Materials, 2015, vol. 24, no. 5. DOI: 10.1177/096369351502400502

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