Determination of the Relationship between Structural and Technological Parameters of Biaxial Reinforcing Preforms of the Aircraft Structural Elements

Аuthors

Ibragimov M. R.^*, Usmonov R. S.^**, Khaliulin V. I.^***

Kazan National Research Technical University named after A.N. Tupolev, Kazan, Russia

*e-mail: sw1ft1704200@mail.ru
**e-mail: ramazonusmanov@gmail.com
***e-mail: pla.kai@mail.ru

Abstract

To represent the end-use properties of the biaxial type preform manufactured by the radial weaving, knowing only the input data, such as filling-in ratio, both inner and outer diameters of the technological mandrel and reinforcement angle, is not enough. Special attention should be paid to the preform properties at the micro- and mezolevels, and their interrelation with technological parameters.
The goal of the study consists in studying the roving end-use cross-section shape forming in the structure of the biaxial type preform. The tasks of the said study were as follows:
- determining minimum and maximum roving width at the microlevel to define the filaments location within the framework of the roving cross-section;
- defining thickness of the layer being braided, on the assumption of the filaments location in the roving cross-section.
The roving width was being determined by the preforms manufacturing with the radial braiding method with various linear densities and surface mass (Fig. 1), followed by the preform scanning and the roving width determining. Fig. 2 shows the roving width dependence on the preform surface mass.
The monolayer thickness was being determined from the same preforms by the Mitutoyo ID-C112CXB micrometer. Fig. 3 shows the monolayer practical thickness dependence on the reinforcement angle, on the assumption of the data in Table 3. After analysis of the obtained results of the the monolayer thickness dependence on the reinforcement angle by the approximation method, the equation (3) for the monolayer theoretical thickness computing was derived. A slight deviation of the curves from each other is being observed, which indicates the high accuracy and the possibility of the equation (3) application for any brand of the reinforcing material.
There are two basic types of the filament arrangement in the roving cross-section, eirhter triangular and square. The filaments with the triangular arrangement occupy a smaller area in the roving cross-section, hence, an increase in the ratio of filaments with this type of arrangement leads to the monolayer thickness reduction. Thus, it is advisable to determine the filament arrangement effect on the monolayer thickness. A system of equations (5) was obtained as a part of the study, which allowed determining the ratios of filaments forming triangular and square structures.
The obtained data will allow determining henceforth the preform maximum degree of compactness while a multi-layer biaxial structure forming.

Keywords:

radial weaving, monolayer thickness dependence on the reinforcement angle, the filaments location in the roving section, monolayer thickness dependence on the filaments arrangement type

References

1. Hsissou R, Seghiri R, Benzekri Z, et al. Polymer composite materials: A comprehensive review. Composite structures. 2021;262:113640. DOI: 10.1016/j.compstruct.2021.113640
2. Gibson RF. A review of recent research on mechanics of multifunctional composite materials and structures. Composite structures. 2010;92(12):2793-2810. DOI: 10.1016/j.compstruct.2010.05.003
3. Rajak DK, Pagar D, Kumar R, et al. Recent progress of reinforcement materials: a comprehensive overview of composite materials. Journal of Materials Research and Technology. 2019;8(6):6354-6374. DOI: 10.1016/j.jmrt.2019.09.068
4. Bairagi H, Vashishth P, Ji G, et al. Polymers and their composites for corrosion inhibition application: Development, advancement, and future scope – A critical review. Corrosion Communications. 2024;15:79-94. DOI: 10.1016/j.corcom.2023.10.006
5. Nagavally RR. Composite materials - history, types, fabrication techniques, advantages, and applications. International Journal of Mechanical And Production Engineering. 2017;5(9):82-87.  
6. Parveez B, Kittur MI, Badruddin IA, et al. Scientific advancements in composite materials for aircraft applications: a review. Polymers. 2022;14(22):5007. DOI: 10.3390/polym14225007
7. Setlak L, Kowalik R, Lusiak T. Practical use of composite materials used in military aircraft. Materials. 2021;14(17):4812. DOI: 10.3390/ma14174812
8. Zolkin AL, Galanskiy SA, Kuzmin AM. Perspectives for use of composite and polymer materials in aircraft construction. IOP Conference Series: Materials Science and Engineering. 2021;1047(1):012023. DOI: 10.1088/1757-899X/1047/1/012023
9. Zhang L, Wang X, Pei J, et al. Review of automated fibre placement and its prospects for advanced composites. Journal of Materials Science. 2020;55(2):7121–7155. DOI: 10.1007/s10853-019-04090-7
10. Frketic J, Dickens T, Ramakrishnan S. Automated Manufacturing and Processing of Fiber-Reinforced Polymer (FRP) Composites: An Additive Review of Contemporary and Modern Techniques for Advanced Materials Manufacturing. Additive Manufacturing. 2017;14(4):69-86. DOI: 10.1016/j.addma.2017.01.003
11. Munro M. Review of manufacturing of fiber composite components by filament winding. Polymer Composites. 1988;9(5):352–359.
12. Azeem M, Ya HH, Kumar M, et al. Application of filament winding technology in composite pressure vessels and challenges: a review. Journal of Energy Storage. 2022;49:103468. DOI: 10.1016/j.est.2021.103468
13. Patti A, Acierno D. Materials, weaving parameters, and tensile responses of woven textiles. Macromol - A Journal of Macromolecular Research. 2023;3(3):665–680. DOI: 10.3390/macromol3030037
14. Fedyaev VL, Khaliulin VI, Sidorov IN, et al. Capillary impregnation of a semipreg stack in composite aircraft parts production. Aerospace MAI Journal. 2023;30(4):68-78. (In Russ.). URL: https://vestnikmai.ru/eng/publications.php?ID=177608
15. Chesnokov AV. Investigation of the influence of technological parameters of weaving on the structure of the surface layer. Aerospace technic and technology. 2008(3):37-40.
16. Perera YS, Muwanwella RMHW, Fernando PR, et al. Evolution of 3D weaving and 3D woven fabric structures. Fashion and Textiles. 2021;8(1):11. DOI: 10.1186/s40691-020-00240-7
17. Walther J, Decrette M, Tourlonias M, et al. 3D weaving process for composite reinforcements: Critical yarn crossings. Applied Composite Materials. 2025. DOI: 10.1007/s10443-025-10321-9
18. Rawal A, Saraswat H, Sibal A. Tensile response of braided structures: a review. Textile Research Journal. 2015;85(19):2083-2096. DOI: 10.1177/0040517515576331
19. Durville D. A finite element approach of the behaviour of woven materials at microscopic scale. In: Ganghoffer JF., Pastrone F. (eds) Mechanics of Microstructured Solids. Lecture Notes in Applied and Computational Mechanics. Springer, Berlin, Heidelberg; 2008. Vol. 46, pp 39–46. DOI: 10.1007/978-3-642-00911-2_5 
20. Czichos R, Bareiro O, Pickett AK, et al. Experimental and numerical studies of process variabilities in biaxial carbon fiber braids. International Journal of Material Forming. 2021;14(9/10):39-54. DOI: 10.1007/s12289-020-01541-4
21. Samipur SA. Design and manufacturing technology of mesh structures of aircraft with a braided reinforcement system. PhD thesis. Kazan: Kazan National Research Technical University named after A.N. Tupolev – KAI; 2018. 134 p. (In Russ.).
22. van Ravenhorst JH. Design tools for circular overbraiding of complex mandrels. PhD thesis. Enschede, University of Twente; 2018. DOI: 10.3990/1.9789036545860