The analysis of the thermodimensional stability of the composite honeycomb panel for the conditions of thermal loading of space apparatus

Authors

DOI:

https://doi.org/10.20535/2521-1943.2019.85.156494

Keywords:

composite materials, multilayer carbon fiber plates, honeycomb, thermomechanical characteristics, thermal stability, finite element approximations, mathematical model, numerical calculations, stress-strain state

Abstract

The results of the numerical determination of the stress-strain state of the composite honeycomb panel under thermal loads of varying intensity in a near-earth orbit are presented. As a simulation model of the structure under study, a typical structure of a composite cell panel with a known type of cell arrangement of honeycomb aluminum filler and reinforcement schemes for layers of carbon fiber material for upper and lower plates with known thermomechanical properties was chosen. To solve the problems of thermoelasticity, we used the finite element method in mathematical formulations for quasistatic thermomechanical analysis. The distribution of the values of von Mises equivalent stresses in the structural elements of the honeycomb panel under thermal loads in the temperature range from -80 to +80 is determined. The longitudinal and transverse deflections of the honeycomb from the action of thermal loads of various intensities in the near-earth orbit are found. The limiting value of the temperature difference between the outer surfaces of the plates, which ensures the thermal stability of the composite honeycomb panel, has been established.

References

  1. Panin, V.F. (1982), Konstrukcii s sotovym zapolnitelem, Mashinostroenie, Moscow, Russia.
  2. Ivanov, A.A., Kashin, S.M. and Semenov, V.I. (2000), Novoe pokolenie sotovyh zapolnitelej dlya aviacionno-kosmicheskoj tekhniki [New generation of cellular aggregates for aerospace technology], Energoatomizdat, Moscow, Russia.
  3. Degtyarev, A.V., Kovalenko, V.A. and Potapov, A.V. (2012), “The use of composite materials in the creation of promising samples of rocket technology”, Aviacionno-kosmicheskaya tekhnika i tekhnologiya, vol. 89, no. 2, pp. 34-38.
  4. Molodcov, G.A., Bitkin, V.E., Simonov, V.F. and Urmansov, F.F. (2000), Formostabil'nye i intellektual'nye konstrukcii iz kompozicionnyh materialov [Form-stable and intelligent structures made of composite materials], Mashinostroenie, Moscow, Russia.
  5. Maslej, V.N. and Kulik, A.S. (2017), “Methods of designing products made of polymer composite materials”, Space Science and Technology, vol. 23, no. 5 (108), pp. 44-48.
  6. Maslej, V.N., and Krishchuk, N.G. (2017), “Determination of the dynamic characteristics of multilayer carbon fiber plates of high-resolution scanner design”, Mechanics and Advanced Technologies, vol. 80, no. 2, pp. 45-51, https://doi.org/10.20535/2521-1943.2017.80.109689
  7. Maslyey, V., Kulyk, A. and Sanin, A. and dr. (2017), Development of dimentionally stable structure of drawtube of optical device made of composite material, European Commission funded International Workshop “Materials resistant to extreme conditions for future energy systems”, Kyiv, Ukraine, 12-14 June, Book of abstracts, p. 72.
  8. Maslei, V. N., Krishchuk, N.G. and Tsybenko, A.S. (2018), “Analysis of harmonic vibration characteristics for a composite honeycomb panel of the spacecraft scanner”, Strength of Materials, vol. 50, no. 4, pp 655–664.
  9. Maslej, V.N. and Kulik, A.S. (2017), “Analysis of the thermally stable supporting structure of the spacecraft payload device”, Aviacionno-kosmicheskaya tekhnika i tekhnologiya, Har'kov, vol. 140, no. 5, pp. 31-35.
  10. Bitkina, E.V., Denisov, A.V. and Bitkin, V.E. (2012), “Constructive-technological methods of creating dimensionally stable space composite structures of integral type”, Izvestiya Samarskogo nauchnogo centra Rossijskoj akademii nauk, vol.14. no.4(2). pp. 555-560.
  11. Koshkina, V.K. (1975), Osnovy teploperedachi v aviacionnoj i raketno-kosmicheskoj tekhnike [Fundamentals of heat transfer in aviation and rocket-space technology], in Koshkina, V.K. (ed.), Mashinostroenie, Moscow, Russia.
  12. Gilmor D.G. (2002), Spacecraft thermal control handbook, 2nd ed., Fundamental Technologies, EI Segundo, Aerospace Press, vol. 1. California.
  13. Lukas, Dzh. (1974), Teploobmen i teplovoj rezhim kosmicheskih apparatov [Heat transfer and thermal regime of spacecraft], in. Anfimova, N.A. (ed.), Mir, Moscow, Russia.
  14. Zaletaev, V.M. and Kapinos, Yu.V. (1971), Raschet teploobmena kosmicheskogo apparata [Calculation of heat transfer spacecraft], Mashinostroenie, Moscow, Russia.
  15. Horoshun, L.P. and Maslov, B.P. (1980), Metody avtomatizirovannogo rascheta fiziko-mekhanicheskih postoyannyh kompozicionnyh materialov, Naukova Dumka, Kyiv, Ukraine.
  16. Rudakov, К.N. and Masley, V.N. (2018), “To a procedure of definition of the "equivalent" physico-mechanical characteristics of a honeycomb filler of a composite plate”, Mechanics and Advanced Technologies, no. 84, no. 3, pp. 75-85, https://doi.org/10.20535/2521-1943.2018.84.149780
  17. Frolov, G.A., Borovik, D.V. and Kolotilo, A.D. and dr. (2013), “Study of the installation for determining thermal and thermal diffusivity in simulating several factors of outer space”, Vestnik dvigatelestroeniya, no.2, pp. 9-15.
  18. Babenko, A.E., Bobyr, M.І., Bojko, S.L. and Boronko, O.O. (2009) Teorіya pruzhnostі, Chastyna 1 [The theory of elasticity. Part 1], Osnova, Kyiv, Ukraine.
  19. Bathe, K.J. and Wilson, E.L. (1976), Numerical methods in finite element analysis, Prentice Hall.
  20. “ANSYS Structural Analysis Guide ANSYS Release 12.1”, (2009) available at: www.ansys.com/

Downloads

Published

2019-04-14

How to Cite

[1]
M. Kryshchuk, V. Maslyey, and A. Mashtabe, “The analysis of the thermodimensional stability of the composite honeycomb panel for the conditions of thermal loading of space apparatus”, Mech. Adv. Technol., no. 1(85), pp. 57–62, Apr. 2019.

Issue

No. 1(85) (2019)

Section

Original study

License

Copyright (c) 2020 Mechanics and Advanced Technologies

Creative Commons License

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

The ownership of copyright remains with the Authors.
 
Authors may use their own material in other publications provided that the Journal is acknowledged as the original place of publication and National Technical University of Ukraine “Igor Sikorsky Kyiv Polytechnic Institute” as the Publisher.

Authors who publish with this journal agree to the following terms:

  1. Authors retain copyright and grant the journal right of first publication with the work simultaneously licensed under CC BY 4.0 that allows others to share the work with an acknowledgement of the work's authorship and initial publication in this journal.

  2. Authors are able to enter into separate, additional contractual arrangements for the non-exclusive distribution of the journal's published version of the work (e.g., post it to an institutional repository or publish it in a book), with an acknowledgement of its initial publication in this journal.

  3. Authors are permitted and encouraged to post their work online (e.g., in institutional repositories or on their website) prior to and during the submission process, as it can lead to productive exchanges, as well as earlier and greater citation of published work