Weight-based optimization of sandwich shelled composite structures with a honeycomb filler

Authors

DOI:

https://doi.org/10.15587/1729-4061.2019.154928

Keywords:

sandwich shelled structures, composite load-bearing skins, honeycomb filler, optimization of parameters

Abstract

Sandwich multi-compartment shelled structures with load-bearing skins from polymer composite materials and honeycomb filler are widely used in products of different classes of equipment. This type of structures makes it possible to realize one of the highest indicators of specific strength and stiffness at minimal weight, which is one of the determining criteria of efficiency of different units. Given the fact that this structural-power configuration contains a very large number of parameters, at the change of which the weight of the product varies significantly, so far there are no generally accepted methodologies for their optimal design. The paper addresses development of the new procedure for optimization of the sandwich shelled composite structures with a honeycomb filler. Variable parameters in the procedure are thicknesses of load-bearing skin, honeycomb filler and bands of frames, geometric parameters of honeycombs; the technological mechanics of structures is also taken into consideration. The distinctive feature of the procedure is consideration in its implementation of the technological (mounting) and operational warpage of the considered shelled systems. This article analyzes the reciprocal impact of such warpages and shows the possibility to study their dependence on load parameters for the specified amplitudes of initial deflections of the technological origin. The obtained results make it possible to determine the optimal type of the reinforcement of load-bearing composite skin under the action of axial compression, transversal pressure and bending moment in the light of technological and operational deflections of the sandwich shelled system. The developed procedure and its software have implemented all major dependences of the mechanical properties of honeycombs on their geometrical parameters and the material. This made it possible to link the process of optimal designing the structures of the considered class to the technological processes of shaping the product and possibilities for a specific production according to structural materials and nomenclature of honeycombs. Implementation of the proposed procedure for optimization of the parameters of the multi-compartment sandwich shelled composite system of the type of nose fairing of a space launch vehicle revealed its efficiency expressed in reducing the weight of the optimal product. It was shown that the application of irregular hexagonal honeycombs is a fairly effective means for reducing the weight of the system

Author Biographies

Andrii Kondratiev, National Aerospace University “Kharkiv Aviation Institute” Chkalova str., 17, Kharkiv, Ukraine, 61070

Doctor of Technical Sciences, Associate Professor, Head of Department

Department of Rocket Design and Engineering

Vitaliy Gaidachuk, National Aerospace University “Kharkiv Aviation Institute” Chkalova str., 17, Kharkiv, Ukraine, 61070

Doctor of Technical Sciences, Professor, Chief Researcher

Problem Research Laboratory of Composite Materials

References

  1. Panin, V. F., Gladkov, Yu. A. (1991). Konstrukcii s zapolnitelem. Moscow: Mashinostroenie, 272.
  2. Nunes, J. P., Silva, J. F. (2016). Sandwiched composites in aerospace engineering. Advanced Composite Materials for Aerospace Engineering, 129–174. doi: https://doi.org/10.1016/b978-0-08-100037-3.00005-5
  3. Herrmann, A. S.; Virson, J. R. (Ed.) (1999). Design and Manufacture of Monolithic Sandwich Structures with Cellular Cares. Stockholm, 274.
  4. Slyvynskyi, V. I., Аlyamovskyi, А. I., Kondratjev, А. V., Kharchenko, М. Е. (2012). Carbon honeycomb plastic as light-weight and durable structural material. 63th International Astronautical Congress, 8, 6519–6529.
  5. Slyvyns’kyy, V., Slyvyns’kyy, M. et. al. (2006). New Concept for Weight Optimization of Launcher Nose Firings Made of Honeycomb Structures. 57th International Astronautical Congress. doi: https://doi.org/10.2514/6.iac-06-c2.p.1.11
  6. Ganguli, R. (2013). Optimal Design of Composite Structures: A Historical Review. Journal of the Indian Institute of Science, 93 (4), 557–570.
  7. Zheng, Q., Jiang, D., Huang, C., Shang, X., Ju, S. (2015). Analysis of failure loads and optimal design of composite lattice cylinder under axial compression. Composite Structures, 131, 885–894. doi: https://doi.org/10.1016/j.compstruct.2015.06.047
  8. Smerdov, A. A. (2000). A computational study in optimum formulations of optimization problems on laminated cylindrical shells for buckling I. Shells under axial compression. Composites Science and Technology, 60 (11), 2057–2066. doi: https://doi.org/10.1016/s0266-3538(00)00102-0
  9. Smerdov, A. A. (2000). A computational study in optimum formulations of optimization problems on laminated cylindrical shells for buckling II. Shells under external pressure. Composites Science and Technology, 60 (11), 2067–2076. doi: https://doi.org/10.1016/s0266-3538(00)00103-2
  10. Totaro, G., Gürdal, Z. (2009). Optimal design of composite lattice shell structures for aerospace applications. Aerospace Science and Technology, 13 (4-5), 157–164. doi: https://doi.org/10.1016/j.ast.2008.09.001
  11. Totaro, G. (2013). Local buckling modelling of isogrid and anisogrid lattice cylindrical shells with hexagonal cells. Composite Structures, 95, 403–410. doi: https://doi.org/10.1016/j.compstruct.2012.07.011
  12. Slyvyns’kyy, V., Slyvyns’kyy, M., Polyakov, N. et. al. (2008). Scientific fundamentals of efficient adhesive joint in honeycomb structures for aerospace applications. 59th International Astronautical Congress 2008.
  13. Vijayakumar, S. (2004). Parametric based design of CFRP honeycomb sandwich cylinder for a spacecraft. Composite Structures, 65 (1), 7–12. doi: https://doi.org/10.1016/s0263-8223(03)00176-4
  14. Karpov, Y. S., Gagauz, P. M. (2010). Structural optimization of composite panels under strength and stability restrictions. Strength of Materials, 42 (6), 631–636. doi: https://doi.org/10.1007/s11223-010-9251-z
  15. Slivinsky, M., Slivinsky, V., Gajdachuk, V., Gajdachuk, A., Kirichenko, V. (2004). New possibilities of creating efficient honeycomb structures for rockets and spacrafts. 55th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law. doi: https://doi.org/10.2514/6.iac-04-i.3.a.10
  16. Slyvyns’kyy, V., Gajdachuk, V., Gajdachuk, А., Slyvyns’ka, N. (2005). Weight Optimization of Honeycomb Structures. 56th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law. doi: https://doi.org/10.2514/6.iac-05-c2.3.07
  17. Gaydachuk, V., Koloskova, G. (2016). Mathematical modeling of strength of honeycomb panel for packing and packaging with regard to deviations in the filler parameters. Eastern-European Journal of Enterprise Technologies, 6 (1 (84)), 37–43. doi: https://doi.org/10.15587/1729-4061.2016.85853
  18. Mackerle, J. (2002). Finite element analyses of sandwich structures: a bibliography (1980–2001). Engineering Computations, 19 (2), 206–245. doi: https://doi.org/10.1108/02644400210419067
  19. Frulloni, E., Kenny, J. M., Conti, P., Torre, L. (2007). Experimental study and finite element analysis of the elastic instability of composite lattice structures for aeronautic applications. Composite Structures, 78 (4), 519–528. doi: https://doi.org/10.1016/j.compstruct.2005.11.013
  20. Slyvyns’kyy, V., Gajdachuk, V., Kirichenko, V., Kondratiev, A. (2012). Basic parameters’ optimization concept for composite nose fairings of launchers. 62nd International Astronautical Congress, 9, 5701–5710.
  21. Vasiliev, V. V., Gurdal, Z. (Eds.) (1999). Optimal Design: Theory and Applications to Materials and Structures. CRC Press, 320.
  22. Xie, Y. (1996). Buckling optimization of hybrid-fiber multilayer-sandwich cylindrical shells under external lateral pressure. Composites Science and Technology, 56 (12), 1349–1353. doi: https://doi.org/10.1016/s0266-3538(96)00079-6
  23. Blyznychenko, V. V., Dzhur, Ye. O., Krasnikov, R. D.; Koniukhov, S. M. (Ed.) (2007). Proektuvannia i konstruiuvannia raket-nosiyiv. Dnipropetrovsk: Vyd-vo DNU, 504.
  24. Bulanov, I. M., Vorobey, V. V. (1998). Tekhnologiya raketnyh i aerokosmicheskih konstrukciy iz kompozicionnyh materialov. Moscow: MGTU im. N. E. Baumana, 516.
  25. Wang, Z.-W. (1997). The geometrically nonlinear theory of anisotropic sandwich shells faced with laminated composites. The Quarterly Journal of Mechanics and Applied Mathematics, 50 (3), 349–378. doi: https://doi.org/10.1093/qjmam/50.3.349
  26. Ivanov, A. A., Kashin, S. M., Semenov, V. I. (2000). Novoe pokolenie sotovyh zapolniteley dlya aviacionno-kosmicheskoy tekhniki. Moscow, 436.
  27. Kondratiev, A., Prontsevych, O. (2018). Stabilization of physical-mechanical characteristics of honeycomb filler based on the adjustment of technological techniques for its fabrication. Eastern-European Journal of Enterprise Technologies, 5 (1 (95)), 71–77. doi: https://doi.org/10.15587/1729-4061.2018.143674
  28. Vasiliev, V. V., Morozov, E. V. (2007). Advanced Mechanics of Composite Materials. Elsevier. doi: https://doi.org/10.1016/b978-0-08-045372-9.x5000-3
  29. Gaidachuk, V. E., Kondratiev, A. V., Chesnokov, A. V. (2017). Changes in the Thermal and Dimensional Stability of the Structure of a Polymer Composite After Carbonization. Mechanics of Composite Materials, 52 (6), 799–806. doi: https://doi.org/10.1007/s11029-017-9631-6
  30. Kulaga, E. S., Olenin, I. G. (2006). Razrabotka golovnyh obtekateley iz kompozicionnyh materialov. Vozdushniy transport, 1, 418–436.

Downloads

Published

2019-01-22

How to Cite

Kondratiev, A., & Gaidachuk, V. (2019). Weight-based optimization of sandwich shelled composite structures with a honeycomb filler. Eastern-European Journal of Enterprise Technologies, 1(1), 24–33. https://doi.org/10.15587/1729-4061.2019.154928

Issue

Vol. 1 No. 1 (2019): Engineering technological systems

Section

Engineering technological systems

License

Copyright (c) 2019 Andrii Kondratiev, Vitaliy Gaidachuk

Creative Commons License

This work is licensed under a Creative Commons Attribution 4.0 International License.

The consolidation and conditions for the transfer of copyright (identification of authorship) is carried out in the License Agreement. In particular, the authors reserve the right to the authorship of their manuscript and transfer the first publication of this work to the journal under the terms of the Creative Commons CC BY license. At the same time, they have the right to conclude on their own additional agreements concerning the non-exclusive distribution of the work in the form in which it was published by this journal, but provided that the link to the first publication of the article in this journal is preserved.

A license agreement is a document in which the author warrants that he/she owns all copyright for the work (manuscript, article, etc.).
The authors, signing the License Agreement with TECHNOLOGY CENTER PC, have all rights to the further use of their work, provided that they link to our edition in which the work was published.
According to the terms of the License Agreement, the Publisher TECHNOLOGY CENTER PC does not take away your copyrights and receives permission from the authors to use and dissemination of the publication through the world's scientific resources (own electronic resources, scientometric databases, repositories, libraries, etc.).
In the absence of a signed License Agreement or in the absence of this agreement of identifiers allowing to identify the identity of the author, the editors have no right to work with the manuscript.
It is important to remember that there is another type of agreement between authors and publishers – when copyright is transferred from the authors to the publisher. In this case, the authors lose ownership of their work and may not use it in any way.