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Article
Publication date: 10 June 2021

Hande Yavuz

Python codes are developed for the versatile structural analysis on a 3 spar multi-cell box beam by means of idealization approach.

Abstract

Purpose

Python codes are developed for the versatile structural analysis on a 3 spar multi-cell box beam by means of idealization approach.

Design/methodology/approach

Shear flow distribution, stiffener loads, location of shear center and location of geometric center are computed via numpy module. Data visualization is performed by using Matplotlib module.

Findings

Python scripts are developed for the structural analysis of multi-cell box beams in lieu of long hand solutions. In-house developed python codes are made available to be used with finite element analysis for verification purposes.

Originality/value

The use of python scripts for the structural analysis provides prompt visualization, especially once dimensional variations are concerned in the frame of aircraft structural design. The developed python scripts would serve as a practical tool that is widely applicable to various multi-cell wing boxes for stiffness purposes. This would be further extended to the structural integrity problems to cover the effect of gaps and/or cut-outs in shear flow distribution in box-beams.

Details

Aircraft Engineering and Aerospace Technology, vol. 93 no. 5
Type: Research Article
ISSN: 1748-8842

Keywords

Article
Publication date: 12 August 2014

Odeh Dababneh and Altan Kayran

In modeling an aircraft wing, structural idealizations are often employed in hand calculations to simplify the structural analysis. In real applications of structural…

Abstract

Purpose

In modeling an aircraft wing, structural idealizations are often employed in hand calculations to simplify the structural analysis. In real applications of structural design, analysis and optimization, finite element methods are used because of the complexity of the geometry, combined and complex loading conditions. The purpose of this paper is to give a comprehensive study on the effect of using different structural idealizations on the design, analysis and optimization of thin walled semi-monocoque wing structures in the preliminary design phase.

Design/methodology/approach

In the design part of the paper, wing structures are designed by employing two different structural idealizations that are typically used in the preliminary design phase. In the structural analysis part, finite element analysis of one of the designed wing configurations is performed using six different one and two dimensional finite element pairs which are typically used to model the sub-elements of semi-monocoque wing structures. Finally in the optimization part, wing structure is optimized for minimum weight by using finite element models which have the same six different finite element pairs used in the analysis phase.

Findings

Based on the results presented in the paper, it is concluded that with the simplified methods, preliminary sizing of the wing configurations can be performed with enough confidence as long as the simplified method based designs are also optimized iteratively, which is what is practiced in the design phase of this study.

Originality/value

This research aims at investigating the effect of using different one and two dimensional element pairs on the final analyzed and optimized configurations of the wing structure, and conclusions are inferred with regard to the sensitivity of the optimized wing configurations with respect to the choice of different element types in the finite element model.

Details

International Journal of Structural Integrity, vol. 5 no. 3
Type: Research Article
ISSN: 1757-9864

Keywords

Article
Publication date: 1 March 1954

P.R. Payne

This paper extends the work of Parts I and II to forward flight conditions, and completes the work on gust clearances.

Abstract

This paper extends the work of Parts I and II to forward flight conditions, and completes the work on gust clearances.

Details

Aircraft Engineering and Aerospace Technology, vol. 26 no. 3
Type: Research Article
ISSN: 0002-2667

Article
Publication date: 1 July 2014

Enrico Cestino and Giacomo Frulla

This study aims to analyse slender thin-walled anisotropic box-beams. Fiber-reinforced laminated composites could play an important role in the design of current and…

Abstract

Purpose

This study aims to analyse slender thin-walled anisotropic box-beams. Fiber-reinforced laminated composites could play an important role in the design of current and future generations of innovative civil aircrafts and unconventional unmanned configurations. The tailoring characteristics of these composites not only improve the structural performance, and thus reduce the structural weight, but also allow possible material couplings to be made. Static and dynamic aeroelastic stability can be altered by these couplings. It is, therefore, necessary to use an accurate and computationally efficient beam model during the preliminary design phase.

Design/methodology/approach

A proper structural beam scheme, which is a modification of a previous first-level approximation scheme, has been adopted. The effect of local laminate stiffness has been investigated to check the possibility of extending the analytical approximation to different structural configurations. The equivalent stiffness has been evaluated for both the case of an isotropic configuration and for simple thin-walled laminated or stiffened sections by introducing classical thin-walled assumptions and the classical beam theory for an equivalent system. Coupling effects have also been included. The equivalent analytical and finite element beam behaviour has been determined and compared to validate the considered analytical stiffness relations that are useful in the preliminary design phase.

Findings

The work has analyzed different configurations and highlighted the effect of flexural/torsion couplings and a local stiffness effect on the global behaviour of the structure. Three types of configurations have been considered, namely, a composite wing box configuration, with and without coupling effects; a wing box configuration with sandwich and cellular constructions; and a wing box with stiffened panels in a coupled or an uncoupled configuration. An advanced aluminium experimental test sample has also been described in detail. Good agreement has been found between the theoretical and numerical analyses and the experimental tests, thus confirming the validity of the analytical relations.

Practical implications

The equivalent beam behaviour that has been determined and the stiffness calculation procedure that has been derived could be useful for future dynamic and aeroelastic analyses.

Originality/value

The article presents an original derivation of the sectional characteristics of a thin-walled composite beam and a numerical/experimental validation.

Details

Aircraft Engineering and Aerospace Technology: An International Journal, vol. 86 no. 4
Type: Research Article
ISSN: 0002-2667

Keywords

Article
Publication date: 1 March 2002

Jaroslav Mackerle

Gives a bibliographical review of the finite element analyses of sandwich structures from the theoretical as well as practical points of view. Both isotropic and composite…

3341

Abstract

Gives a bibliographical review of the finite element analyses of sandwich structures from the theoretical as well as practical points of view. Both isotropic and composite materials are considered. Topics include: material and mechanical properties of sandwich structures; vibration, dynamic response and impact problems; heat transfer and thermomechanical responses; contact problems; fracture mechanics, fatigue and damage; stability problems; special finite elements developed for the analysis of sandwich structures; analysis of sandwich beams, plates, panels and shells; specific applications in various fields of engineering; other topics. The analysis of cellular solids is also included. The bibliography at the end of this paper contains 655 references to papers, conference proceedings and theses/dissertations dealing with presented subjects that were published between 1980 and 2001.

Details

Engineering Computations, vol. 19 no. 2
Type: Research Article
ISSN: 0264-4401

Keywords

Article
Publication date: 1 April 1954

John H. Argyris

WE define as an open tube a thin‐walled structure, the cross‐section of which does not include any closed circuit. This property is common, for example, to the curved…

Abstract

WE define as an open tube a thin‐walled structure, the cross‐section of which does not include any closed circuit. This property is common, for example, to the curved channel, the interspar wing cut‐out and the panel stiffened with Z‐sections, illustrated in FIG. 1 (a, b, c). But the interspar cut‐out with nose cell (FIG. 1d) is not an open tube in the present definition. All structures discussed in this paper are assumed to be cylindrical and to have a constant cross‐section. It is relatively simple to extend the results to conical taper and longitudinally varying thickness, but this would be beyond the scope and space of the present analysis (see, however, ref. 5).

Details

Aircraft Engineering and Aerospace Technology, vol. 26 no. 4
Type: Research Article
ISSN: 0002-2667

Article
Publication date: 1 February 1953

Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Council, Reports and Technical Memoranda of the United…

Abstract

Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Council, Reports and Technical Memoranda of the United States National Advisory Committee for Aeronautics and publications of other similar Research Bodies as issued

Details

Aircraft Engineering and Aerospace Technology, vol. 25 no. 2
Type: Research Article
ISSN: 0002-2667

Article
Publication date: 1 September 1961

A.F. Newell

AT a time when the glamour of space travel is capturing the imagination of the aeronautical world it seems somewhat mundane to be asked to report on the progress of the…

Abstract

AT a time when the glamour of space travel is capturing the imagination of the aeronautical world it seems somewhat mundane to be asked to report on the progress of the past years‘ achievements. The first reaction is to question if there has been any progress, or is this just ’another' year.

Details

Aircraft Engineering and Aerospace Technology, vol. 33 no. 9
Type: Research Article
ISSN: 0002-2667

Article
Publication date: 1 June 1959

J.H. Argyris and S. Kelsey

Following the self‐equilibrating stress systems developed for the single‐cell fuselage, further stress systems are given for the fuselage with a double‐cell cross‐section…

Abstract

Following the self‐equilibrating stress systems developed for the single‐cell fuselage, further stress systems are given for the fuselage with a double‐cell cross‐section. These allow for the direct stress carrying ability of the floor. Wing‐fuselage interaction redundancies are discussed in detail and suitable self‐equilibrating load systems presented. The formation of the associated stress systems in the cover is described with reference to their generation inside the computer. Chapter IV concludes with a brief account of fin attachment loads which serves to introduce two further interaction redundancies to take account of skin attachment. The opening section of Chapter V relates the detailed frame loads to the overall fuselage loading preparatory to the analysis of the closed frames. Matrix equations for the calculation of the statically equivalent wing reactions and of the fuselage moment diagrams are given.

Details

Aircraft Engineering and Aerospace Technology, vol. 31 no. 6
Type: Research Article
ISSN: 0002-2667

Article
Publication date: 1 April 1971

THE engineering design of the Concorde's structure has been carried out in accordance with the requirements agreed between the British and French airworthiness authorities…

Abstract

THE engineering design of the Concorde's structure has been carried out in accordance with the requirements agreed between the British and French airworthiness authorities and published in documents known as TSS Standards.

Details

Aircraft Engineering and Aerospace Technology, vol. 43 no. 4
Type: Research Article
ISSN: 0002-2667

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