To read the full version of this content please select one of the options below:

Stress, strain and displacement analysis of geodetic and conventional fuselage structure for future passenger aircraft

Zdobyslaw Jan Goraj (Faculty of Power and Aeronautical Engineering, Warsaw University of Technology, Warszawa, Poland)
Mariusz Kowalski (Faculty of Power and Aeronautical Engineering, Warsaw University of Technology, Warszawa, Poland)
Bartlomiej Goliszek (Faculty of Power and Aeronautical Engineering, Warsaw University of Technology, Warszawa, Poland)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 25 January 2019

Issue publication date: 15 August 2019

Abstract

Purpose

This paper aims to present the results of calculations that checked how the longerons and frames arrangement affects the stiffness of a conventional structure. The paper focuses only on first stage of research – analysis of small displacement. Main goal was to compare different structures under static loads. These results are also compared with the results obtained for a geodetic structure fuselage model of the same dimensions subjected to the same internal and external loads.

Design/methodology/approach

The finite element method analysis was carried out for a section of the fuselage with a diameter of 6.3 m and a length equal to 10 m. A conventional and lattice structure – known as geodetic – was used.

Findings

Finite element analyses of the fuselage model with conventional and geodetic structures showed that with comparable stiffness, the weight of the geodetic fuselage is almost 20 per cent lower than that of the conventional one.

Research limitations/implications

This analysis is limited to small displacements, as the linear version of finite element method was used. Research and articles planned for the future will focus on nonlinear finite element method (FEM) analysis such as buckling, structure stability and limit cycles.

Practical implications

The increasing maturity of composite structures manufacturing technology offers great opportunities for aircraft designers. The use of carbon fibers with advanced resin systems and application of the geodetic fuselage concept gives the opportunity to obtain advanced structures with excellent mechanical properties and low weight.

Originality/value

This paper presents very efficient method of assessing and comparison of the stiffness and weight of geodetic and conventional fuselage structure. Geodetic fuselage design in combination with advanced composite materials yields an additional fuselage weight reduction of approximately 10 per cent. The additional weight reduction is achieved by reducing the number of rivets needed for joining the elements. A fuselage with a geodetic structure compared to the classic fuselage with the same outer diameter has a larger inner diameter, which gives a larger usable space in the cabin. The approach applied in this paper consisting in analyzing of main parameters of geodetic structure (hoop ribs, helical ribs and angle between the helical ribs) on fuselage stiffness and weight is original.

Keywords

Acknowledgements

This paper was written thanks to funding of the project “ConcEpt validatioN sTudy foR fusElage wake-filLIng propulsioN integration (CENTRELINE)” No 723242 funded from European Union’s Horizon 2020 research and innovation program.

Citation

Goraj, Z.J., Kowalski, M. and Goliszek, B. (2019), "Stress, strain and displacement analysis of geodetic and conventional fuselage structure for future passenger aircraft", Aircraft Engineering and Aerospace Technology, Vol. 91 No. 6, pp. 814-819. https://doi.org/10.1108/AEAT-07-2018-0216

Publisher

:

Emerald Publishing Limited

Copyright © 2019, Emerald Publishing Limited