METHOD OF DESIGN CALCULATING OF THE STRENGTH OF THE TRANSVERSE JOINT OF THE PANELS OF OUTER WING SECTION AND THE CENTER SECTION OF THE TRANSPORT AIRCRAFT

Sun Yifang, В. Є. Василевский, О. О. Вендін, О. Г. Гребеніков

Abstract


Due to the limitation in the dimensions of the structural elements of the modeled wing contour and the possibility of increasing their cross-sections in the area of the transverse joint, only on the inside, there is a need to find an effective solution for the design, mass of the joint, as well as its statical strength at the modeling stage. The article presents the method and its application using the example of a preliminary analysis of the design calculation of the design of the flange connection of the center section with the outer wing section (OWS) of a transport aircraft. The method is based on the calculation of stresses caused by the discrete transmission of forces between elements. In the calculation method, a simplified statically indeterminate joint model is obtained according to the geometric characteristics and force transmission characteristics of each node section in the flange joint structure. During the calculations, the following are determined: diagrams of the bending moment and axial forces obtained using the force method, the distribution of force loads in each section of the model for subsequent analysis of the static safety factor. The resulting calculation results are compared with the airworthiness requirements to determine whether they meet the design requirements. For components with greater static strength, or those that do not meet the requirements, it is recommended to further modify the design parameters to ensure an effective design of the center section joint with the outer wing section and subsequent re-calculation. The calculation method used has practical value as a preliminary engineering analysis.

The geometric characteristics of the junction of the center section with the negative part of the wing were modeled using the CAD/CAMCAE CATIA system.


Keywords


transport aircraft; flange connection; strength calculation; static safety margin.

References


Grebenikov, A. G. Methodology of integrated designing and modelling of aircraft assembly structures: training guide // A. G. Grebenikov / Kharkov: National Aerospace University “Kharkov Aviation Institute”. – 2010. – 425 s.

Yakimenko, S. I. Raschet poperechnogo styka panelej flancevogo i sreznogo tipa: metodika / S. I. Yakimenko / Kiіv: ANTK «Antonov». – 2000. – 25 s.

Vasilevskij, E. T. Metod integrirovannogo proektirovaniya, konstruirovaniya i modelirovaniya vysokoresursnogo fitingovogo styka kryla s centroplanom samoleta transportnoj kategorii / E. T. Vasilevskij, A. G. Grebenikov, A. Yu. Efremov, N. V. Efremova // Otkrytye informacionnye i komp'yuternye integrirovannye texnologii. – 2010. – Vyp. 46. – S. 277 – 292.

Grebenikov, A. G. Voprosy proektirovaniya sreznyx boltovyx soedinenij kryla s uchetom vynoslivosti / A. G. Grebenikov, L. D. Arson // Nacional'nyj ae'rokosmicheskij universitet "Xar'kovskij aviacionnyj institute". – 1981. – 112 s.

Zhang Shaoshi. New Material Mechanics [Kniga] / Zhang Shaoshi. // Machinery Industry Press – 2010. – 374 s.

Liu Shikui. Structural Mechanics / Liu Shikui // Tsinghua University Press, 2008. – 204 s.

Vasilevskij E. T. Osnovnye polozheniya vozdushnogo kodeksa Ukrainy i norm letnoj godnosti samoletov transportnoj kategorii / E. T. Vasilevskij, V. A. Grebenikov, V. N. Nikolaenko // Nacional'nyj ae'rokosmicheskij universitet “Xar'k. aviac. inst.". – 2006. – 331 s.

Vojt, E. S. Proektirovanie konstrukcij samoletov: Uchebnik dlya studentov vuzov, obuchayushhixsya po special'nosti «Samoletostroenie» / E. S. Vojt, A. I. Endogur, Z. A. Melik-Sarkisyan, I. M. Alyavdin // M.: Mashinostroenie. – 1987. – 416 s.




DOI: https://doi.org/10.32620/oikit.2023.97.09

Refbacks

  • There are currently no refbacks.