Computation experimental study of three-layer flat panels with the polymer composite sheaths
Authors: Rabinsky L.N., Martirosov M.I., Dedova D.V.
Published in issue: #4(160)/2025
DOI: 10.18698/2308-6033-2025-4-2437
Category: Mechanics | Chapter: Mechanics of Deformable Solid Body
The paper presents results of the computation experimental study of three-layer flat panels with the honeycomb core and sheaths made of the polymer composite material (PCM). The study was conducted under a compressive normal load to the panel plane. The full-scale experiment was carried out using the INSTRON 5985 testing machine. The necessary computation was performed numerically with the LS-DYNA software package and the finite element method. Methodology for simulating and determining strength of the three-layer panels with the honeycomb core and the PCM sheaths was validated based on results of the full-scale experiment by comparing the panel critical failure load and the honeycomb panel failure pattern. Validation results showed that the panel maximum failure load obtained experimentally as a result of the full-scale testing and numerically using the finite element method was differing by no more than 8%.
EDN RBEFSY
References
[1] Lubin G., Dastin S. Aerospace Applications of Composites. Handbook of Composites. Van Nostrand Reinhold, New York, 1982 [In Russ.: Lyubin Dzh., Dastin S. Aerokosmicheskoe primenenie kompozitov. Spravochnik po kompozitsionnym materialam: v dvukh knigakh. Kniga 2. Moscow, Mashinostroenie Publ., 1988, 584 p.].
[2] Volmir A.S. Sovremennye kontseptsii primeneniya kompozitnykh materialov v letatelnykh apparatakh i dvigatelyakh [Modern concepts of composite materials application in aircraft and engines]. Mekhanika kompozitnykh materialov — Mechanics of Composite Materials, 1985, no. 6, pp. 1049–1056.
[3] Grishin V.I., Dzyuba A.S., Dudarkov Yu.I. Prochnost i ustoychivost elementov i soedineniy aviatsionnykh konstruktsiy iz kompozitov [Strength and stability of elements and joints of aircraft structures made of composites] Moscow, Fizmatlit Publ., 2013, 272 p.
[4] Belouettar S., Abbadi A., Azari Z., Belouettar R., Freres P. Experimental investigation of static and fatigue behavior of composites honeycomb materials using four point bending tests. Composite Structures, 2009, vol. 87, pp. 265–273.
[5] Guangyong Sun, Xintao Huo, Dongdong Chen, Qing Li. Experimental and numerical study on honeycomb sandwich panels under bending and in-panel compression. Materials & Design, 2017, vol. 133, pp. 154–168.
[6] Dobritsa D.B. Teoretiko-eksperimentalnaya otsenka stoykosti sotovykh paneley kosmicheskogo korablya pri vozdeystvii meteorno-tekhnogennykh chastits [Theoretical-experimental estimate of resistance of spacecraft honeycomb panels upon impacts from meteoroids and space debris]. Vestnik Tomskogo gosudarstvennogo universiteta — Tomsk State University Journal, 2014, no. 2, pp. 58–68.
[7] Medvedskiy A.L., Martirosov M.I., Khomchenko A.V., Dedova D.V. Behaviour of a cylindrical reinforced carbon fibre shell under impact load. TEM Journal, 2021, vol. 10, no. 4, pp. 1597–1604.
[8] Rabinskiy L.N., Martirosov M.I., Dedova D.V., Khomchenko A.V. Dynamics of composite cylindrical panels with honeycomb filler after internal damage by aircraft engine jet. Russian Engineering Research, 2024, vol. 44, no. 5, pp. 726–729.
[9] Dedova D.V., Kuznetsova E.L., Martirosov M.I., Khomchenko A.V. Chislennoe issledovanie vliyaniya vnytrennikh defektov na napryazhenno-deformirovannoe sostoyanie trekhsloynoy paneli s razlichnymi tipami sotovogo zapolnitelya [Numerical study of the influence of internal defects on the stress-strain state of a three-layer panel with different types of the honeycomb core]. STIN, 2023, no. 10, pp. 27–30.
[10] TU 23.99.14-102-61664530–20218. Prepregi na osnove uglevoloknistykh armiruyushchikh materialov i svyazuyushchego ASM 102 [TU 23.99.14-102-61664530–20218. Prepregs based on carbon fiber reinforcing materials and ASM 102 binder].
[11] TU 1-596-231-01. Polimerosotoplasty PSP-1 [TU 1-596-231-01. Polymer-coated honeycomb plastics PSP-1].
[12] GOST R 56816-2015. Kompozity polimernye. Opredelenie mekhanicheskikh kharakteristik pri szhatii materiala vnutrennego sloya “sendvich”-konstruktsiy perpendikulyarno k ploskosti obraztsa [GOST R 56816-2015. Polymer composites. Determination of flatwise compressive properties of sandwich cores]. Moscow, Standartinform Publ., 2016, 14 p.
[13] ASTM C365/C365M-11a. Standard test method for flatwise compressive properties of sandwich cores. 4 p.