Developing technique for impact action resistance determining of the aircraft parts from composites with honeycomb filler

DOI: 10.34759/vst-2020-3-111-125

Аuthors

Bezzametnov O. N.^*, Mitryaikin V. I.^**, Khaliulin V. I.^***, Krotova E. V.^****

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

*e-mail: bezzametnovoleg@mail.ru
**e-mail: vmitryaykin@bk.ru
***e-mail: pla.kai@mail.ru
****e-mail: kati_mit@mail.ru

Abstract

The presented study is focused on determining the impact resistance and survivability characteristics of panel samples with the honeycomb filler and fragments of helicopter blades. The problems, associated with developing and producing the experimental samples impact tests performing, as well as studying the character and geometry characteristics of damages were being solved while these works execution. The authors developed a technique for impact resistance determining of aircraft sandwiched composite parts with honeycomb filler. The composite sandwiched structures in the form of the helicopter steering and main rotor fragments, and standard samples of the sandwiched panels with the honeycomb filler were the objects of the study. Carbon composite skins and honeycombed filler from aramid paper were employed for the panels manufacturing. The blade fragments represented the structures composed of T-25 fiberglass plastic layers with honeycomb or foam filler placed between them.

A technique for inflicting impact damages by vertically falling load, and registering such parameters as impact energy, maximum loading and impactor penetration depth was developed while laboratory studies. Application of piezometric transducers while impact tests allowed registering diagrams of the impact damage, which, besides the general energy-force assessment, allow step-by-step studying of the impact loading. The impact energy for the samples of sandwich-panels was being selected from the condition of incomplete destruction ensuring (2 J), and initiating significant damages of the skin and filler (10 J). The damages character studies of the helicopter steering and main rotor blades fragments were conducted within the energies range of 5–50 J. The depths of dents and cracks were determined by the digital indicator head. Computer tomography was employed for internal diagnostics of the damaged samples. Tomograms of the blades sections allowed studying stage-by-stage growth of damages in dependence of the impact loading increasing.

It can be declared by the results of this work that already small impact energies lead to dent on the skin forming, and crumpling of the honeycomb filler with partial destruction. At the impact energy of 10 J, significant destruction of skins and filler under them is being observed. The breakdown and cleavage of the skin material along the panel length are being observed on the external side of the sandwich-panel subjected to the impact. The tomographic images of the tail rotor blade show fractures of the fiberglass plastic layer and crumpling of the foam filler. Analysis of the main rotor blade sections also revealed the fracture of the skin upper layer and subsequent compression of the honeycomb filler.

Keywords:

honeycomb panels, composites, sandwiched structures, impact actions, damages, non-destructive inspection, computer tomography

References

1. Kablov E.N. Aviatsionnoe materialovedenie v XXI veke. Aviatsionnye materialy. Izbrannye trudy VIAM 1932-2002, Moscow, VIAM, 2002, pp. 23-47.

2. Kolosova A.S., Sokol’skaya M.K., Vitkalova I.A., Torlova A.S, Pikalov E.S. Mezhdunarodnyi zhurnal prikladnykh i fundamental’nykh issledovanii, 2018, no. 5 (part 1), pp. 245-256.

3. Savin S.P. Izvestiya Samarskogo nauchnogo tsentra Rossiiskoi akademii nauk, 2012, vol. 14, no. 4 (part 2), pp. 686-693.

4. Bazhenov S.L., Berlin A.A., Kul’kov A.A., Oshmyan V.T. Polimernye kompozitsionnye materialy (Polymer composite materials: scientific publication), Dolgoprudnyi, Izdatel’skii dom “Intellekt”, 2010, 352 p.

5. Bilisik K. Multiaxis three-dimensional weaving for composites: A review. Textile Research Journal, 2012, vol. 82, no. 7, pp. 725-743. DOI: 10.1177/0040517511435013

6. Fegenbaum Yu.M., Dubinskii S.V., Bozhevalov D.G., Sokolov Yu.S., Metelkin E.S., Mikolaichuk Yu.A., Shapkin V.S. Obespechenie prochnosti kompozitnykh aviatsionnykh konstruktsii s uchetom sluchainykh ekspluatatsionnykh udarnykh vozdeistvii (Strength ensuring of composite aircraft structures with account for random operational shock effects), Moscow, Tekhnosfera, 2018, 506 p.

7. Serenson S.V., Zaitsev G.P. Nesushchaya sposobnost’ tonkostennykh konstruktsii iz armirovannykh plastikov s defektami (Bearing capacity of thin-walled structures from reinforced plastics with defects), Kiev, Naukova dumka,1982, 296 p.

8. Bezzametnov O.N., Mitryaykin V.I., Khaliulin V.I., Statsenko E.O. Investigation of Composite Materials Impact Damage by a Computer Tomography. Key Engineering Materials, 2019, vol. 822, рp. 362–370. DOI: 10.4028/www.scientific.net/KEM.822.362

9. Kolesnikov Yu.V., Morozov E.M. Mekhanika kontaktnogo razrusheniya (Mechanics of contact destruction), Moscow, LKI, 2013, 224 p.

10. Romano F., Di C.F., Mercurio U. Compression after Impact Analysis of Composite Panels and Equivalent Hole Method. Procedia Engineering, 2016, vol. 167, pp. 182–189. DOI: 10.1016/j.proeng.2016.11.686

11. Singh H., Hazarika B.Ch., Dey S. Low velocity impact responses of functionally graded plates. Procedia Engineering, 2017, vol. 173, pp. 264–270. DOI: 10.1016/j.proeng.2016.12.010

12. Kursun A., Senel M., Enginsoy H.M. Experimental and numerical analysis of low velocity impact on a preloaded composite plate. Advances in Engineering Software, 2015, vol. 90, pp. 41–52. DOI: 10.1016/j.advengsoft.2015.06.010

13. Sidorov I.N., Mitryaikin V.I., Gorelov A.V., Shabalin L.P. Zhurnal Srednevolzhskogo matematicheskogo obshchestva, 2019, vol. 21, no. 3, pp. 343-350. DOI: 10.15507/2079-6900.21.201903.343-352

14. Tan K.T., Watanabe N., Iwahori Y. Finite element model for compression after impact behavior of stitched composites. Copmposites Part B: Engineering, 2015, vol. 79, pp. 53-60. DOI: 10.1016/j.compositesb.2015.04.022

15. Guz’ A.N. (ed.) Metody rascheta obolochek: V 5-ti t. T. 1. Teoriya tonkikh obolochek, oslablennykh otverstiyami (Shells calculating techniques. In 5 vols. Vol. 1 “Theory of thin shells slacken by holes”), Kiev, Naukova dumka, 1980, 636 p.

16. Poliansky V.V., Nesterov V.A. Estimation of reliability alteration for airframe configuration with mechanical damage. Aerospace MAI Journal, 2009, vol. 16, no. 5, pp. 32-39.

17. Nebelov E.V., Pototskii M.V., Rodionov A.V., Gorskii A.N. Mechanism of damage propagation to the propeller blades of composite materials with exposed damaging elements. Aerospace MAI Journal, 2016, vol. 23, no. 1, pp. 26-31.

18. Bezzametnov O.N., Mitryaikin V.I., Khaliulin V.I. Low-speed impact testing of various composites. Aerospace MAI Journal, 2019, vol. 26, no. 4, pp. 216-229. DOI: 10.34759/vst-2019-4-216-229

19. Krylov A.A., Moskaev V.A. A technique for fluoroscopic control and analysis of technical condition of aircraft structural elements with honeycomb filler. Aerospace MAI Journal, 2019, vol. 26, no. 2, pp. 139-146.

20. Kompozity polimernye. Metod opredeleniya predela prochnosti na szhatie parallel’no ploskosti “sendvich”-konstruktsii. GOST R 56809-2015 (Polymer composites. Techniques for ultimate compressive strength determining parallel to the “sandwich”-structure plane. State Standard R 56809-2015), Moscow, Standartinform, 2016, 16 p.