Checking the adequacy of approximate analytical dependences for the deflection of a thin homogeneous plate under temperature shock


Аuthors

Sedel'nikov A. V.*, Serdakova V. V.**, Nikolaeva A. S.***

Samara National Research University named after Academician S.P. Korolev, 34, Moskovskoye shosse, Samara, 443086, Russia

*e-mail: axe_backdraft@inbox.ru
**e-mail: valeriay.121@yandex.ru
***e-mail: ezhevichka333@gmail.com

Abstract

The paper presents a comparative analysis of approximate analytical relationships modelling the deflection of a homogeneous thin plate under thermal shock for the case of rigid fixation of one edge of the plate and free other edges of the plate. This analysis contains two directions: studies of the deflection temperature field.

The temperature field of the plate is analysed by comparing the results of numerical simulations with the data of in-situ tests. The experiments conducted with a new promising solar panel ROSA (Roll-Out Solar Array) in 2017 on board the International Space Station (ISS) were chosen as field tests. During these experiments, temperature measurements were made with sensors in different parts of ROSA, which allows a more correct comparison of modelling results with measured data. The comparison showed a good convergence of the results, especially near the fixed edge of ROSA. This is due to the closer real picture of the temperature shock to the mathematical formulation of the two-dimensional heat conduction problem.

To confirm the obtained results, a comparative analysis was made with the data of experiments conducted in ground conditions of the space environment simulator laboratory KM7 with the space boom section. The results of numerical modelling and in-situ experiment also have good convergence. And their differences are due to the fact that the beam model is more suitable for the boom than the plate model.

To investigate the fit of the deflection field, an experiment conducted with a reduced model ROSA solar panel in earth laboratory conditions was chosen. The deflection dynamics of the ROSA end section support beam was chosen as data for comparison. A good convergence of the results in the average value of deflections without taking into account thermal oscillations is shown. Since in the mathematical formulation of the thermoelasticity problem thermo-vibrations were not taken into account.

Thus, as a result of the work the limits of applicability of approximate analytical dependences for practical use in accounting for the temperature shock of solar panels of a small spacecraft have been revealed. The results of the work can be used in the study of rotational motion of a small spacecraft around its centre of mass taking into account the effect of temperature shock.

Keywords:

temperature shock, thin homogeneous plate, solar panel, small spacecraft

References

  1. Akhmetov R., Filatov A., Khalilov R. «AIST-2D»: Results of flight tests and application of earth remote sensing data for solving thematic problems, The Egyptian Journal of Remote Sensing and Space Science, 2023, vol. 26 (3), pp. 427-454. DOI: 10.1016/j.ejrs.2023.06.003

  2. Sedel'nikov A.V., Orlov D.I., Serdakova V.V., Nikolaeva A.S. Trudy MAI, 2022, no. 126. URL: https://trudymai.ru/eng/published.php?ID=168997. DOI: 10.34759/trd-2022-126-11

  3. Lia M., Zhang Y., Hu Q., Qi R The pointing and vibration isolation integrated control method for optical payload, Journal of Sound and Vibration, 2019, vol. 438, pp. 441-456. DOI: 10.1016/j.jsv.2018.09.038

  4. Abrashkin V.I., Voronov K.E., Dorofeev A.S. et al. Kosmicheskie issledovaniya, 2019, vol. 57, no. 1, pp. 61–73.

  5. Zhang Y., Sheng C., Hu Q. et al. Dynamic analysis and control application of vibration isolation system with magnetic suspension on satellites, Aerospace Science and Technology, 2018, vol. 75, pp. 99–114. DOI: 10.1016/j.ast.2017.12.041

  6. Zhang J., Guo Z., Zhang Y. Dynamic characteristics of vibration isolation platforms considering the joints of the struts, Acta Astronautica, 2016, vol. 126, pp. 120–137. DOI: 10.1016/j.actaastro.2016.04.001

  7. Sedel'nikov A.V., Nikolaeva A.S., Serdakova V.V. Trudy MAI, 2023, no. 132. URL: https://trudymai.ru/eng/published.php?ID=176836

  8. Abrashkin V.I., Puzin Yu.Ya., Sazonov V.V. Elektromagnitnaya sistema upravleniya vrashchatel'nym dvizheniem sputnika, obespechivayushchaya malyi uroven' mikrouskorenii na ego bortu (Electromagnetic control system of the satellite rotational motion providing a small level of micro-accelerations on its board), Moscow, IPM im. M.V. Keldysha, 2010, preprint no. 22, 36 p.

  9. Wang A., Wang S., Xia H. et al. Dynamic Modeling and Control for a Double-State Microgravity Vibration Isolation System, Microgravity Science and Technology, 2023, vol. 35, no. 1. DOI: 10.1007/s12217-022-10027-8

  10. Sedel'nikov A.V., Taneeva A.S. Omskii nauchnyi vestnik. Seriya aviatsionno-raketnoe i energeticheskoe mashinostroenie, 2023, vol. 7, no. 2, pp. 65–72. DOI: 10.25206/2588-0373-2023-7-2-65-72

  11. Kerber F., Hurlebausb S., Beadle B.M. et al. Control concepts for an active vibration isolation system, Mechanical Systems and Signal Processing, 2007, vol. 21, pp. 3042–3059. DOI: 10.1016/j.ymssp.2007.04.003

  12. Aslanov V.S., Neryadovskaya D.V. Trudy MAI, 2022, no. 122. URL: https://trudymai.ru/eng/published.php?ID=163923. DOI: 10.34759/trd-2022-122-02

  13. Ledkov A.S. Trudy MAI, 2023, no. 131. URL: https://trudymai.ru/eng/published.php?ID=175910. DOI: 10.34759/trd-2023-131-04

  14. Trushlyakov V.I., Yudintsev V.V. Rotary space tether system for active debris removal, Journal of Guidance, Control, and Dynamics, 2020, vol. 43, no. 2, pp. 354–364. DOI: 10.2514/1.G004615

  15. Botta E.M., Sharf I., Misra A.K. Contact Dynamics Modeling and Simulation of TetherNets for Space Debris Capture, Journal of Guidance, Control, and Dynamics, 2017, vol. 40, no. 1, pp. 110-123. DOI: 10.2514/1.g000677

  16. Mironov V.V., Usovik I.V. Kosmicheskie issledovaniya, 2020, vol. 58, no. 2, pp. 117–130. DOI: 10.31857/S0023420620020089

  17. Aslanov V.S., Ledkov A.S. Detumbling of axisymmetric space debris during transportation by ion beam shepherd in 3D case, Advances in Space Research, 2022, vol. 69, no. 1, pp. 570–580. DOI: 10.1016/j.asr.2021.10.002

  18. Priyant C.M. Surekha K. Review of Active Space Debris Removal Methods, Space Policy, 2019, vol. 47, pp. 194–206. DOI: 10.1016/j.spacepol.2018.12.005

  19. Wang Q., Jin D., Rui X. Dynamic Simulation of Space Debris Cloud Capture Using the Tethered Net, Space: Science & Technology, 2021, vol. 2021. DOI: 10.34133/2021/9810375

  20. Orlov D.I. Modeling the Temperature Shock Impact on the Movement of a Small Technological Spacecraft, Proceedings International Conference Problems of Applied Mechanics. AIP Conference Proceedings, 2021, vol. 2340, no. 1, pp. 050001. DOI: 10.1063/5.0047296

  21. Manuilov S.A. Problemy bezopasnosti poletov, 2021, no. 9, pp. 35–53. DOI: 10.36535/0235-5000-2021-09-3

  22. Sedelnikov A.V., Serdakova V.V., Nikolaeva A.S. Method of Taking into Account Influence of Thermal Shock on Dynamics of Small Satellite and its Use in Analysis of Microaccelerations, Microgravity Science and Technology, 2023, vol. 35, no. 3. DOI: 10.1007/s12217-023-10049-w

  23. Sedelnikov A.V., Orlov D.I., Serdakova V.V., Nikolaeva A.S. Investigation of the stress-strain state of a rectangular plate after a temperature shock, Mathematics, 2023, vol. 11, no. 3, pp. 638. DOI: 10.3390/math11030638

  24. Sedelnikov A.V., Serdakova V.V., Orlov D.I., Nikolaeva A.S. Investigating the Temperature Shock of a Plate in the Framework of a Static Two-Dimensional Formulation of the Thermoelasticity Problem, Aerospace, 2023, vol. 10, no. 5, pp. 445. DOI: 10.3390/aerospace10050445

  25. Sedelnikov A.V., Orlov D.I., Serdakova V.V. et al. The importance of a three-dimensional formulation of the thermal conductivity problem in assessing the effect of a temperature shock on the rotational motion of a small spacecraft, E3S Web of Conferences, 2023, vol. 371, pp. 03015. DOI: 10.1051/e3sconf/202337103015

  26. Chamberlain M.K., Kiefer S.H., Banik J.A. On-Orbit Structural Dynamics Performance of the Roll-Out Solar Array, AIAA Spacecraft Structures Conference, 2018. DOI: 10.2514/6.2018-1942

  27. Chamberlain M.K., Kiefer S.H., La Pointe M., La Corte P. On-orbit flight testing of the Roll-Out Solar Array, Acta Astronautica, 2021, vol. 179, pp. 407–414. DOI: 10.1016/j.actaastro.2020.10.024

  28. Liu C., Zhan H.Y., Wang Y., et al. Data management platform for space environment simulator based on real-time database, Spacecraft Environment Eng China, 2010, vol. 12, pp. 715–719.

  29. Su. X.M., Zhang J.H., Wang J., Bi Ya. Q., Qie D.F., Xiang Z.H., Xue M.D. Experimental investigation of the thermally induced vibration of a space boom section, Science China Physics, Mechanics & Astronomy, 2015, vol. 58, no. 4, pp. 044601. DOI: 10.1007/s11433-014-5622-y

  30. Lee B.H., Yamasaki M., Murozono M. Experimental Verification of Thermal Structural Responses of a Flexible Rolled-Up Solar Array, Transactions of the Japan Society for Aeronautical and Space Sciences, 2013, vol. 56, no. 4, pp. 197–204. DOI: 10.2322/tjsass.56.197

  31. Ma J., Dai C., Wang B., Beer M., Wang A. Random dynamic responses of solar array under thermal-structural coupling based on the isogeometric analysis, Acta Mechanica Sinica, 2023, vol. 39, no. 4, pp. 722338. DOI: 10.1007/s10409-023-22338-x


Download

mai.ru — informational site MAI

Copyright © 2000-2024 by MAI

 Вход