Parametric study of an elliptical fuselage made of a sandwich composite structure

Boulle, A.; Dubé, Martine; Gosselin, Frédérick P.

doi:10.1016/j.mechrescom.2015.07.002

Cited by 7 publications

(4 citation statements)

References 11 publications

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“…Adrien Boulle et al [3] examined the feasibility of using a pressurized elliptical fuselage over a circular one. Three different elliptical fuselage constructs considered were: monolithic (having no core, only facesheet whose thickness varies with polar angle), symmetric (a core encompassed by 2 facesheets both of equal thickness and varying with polar angle) and asymmetric (a core encompassed by 2 facesheets of unequal thickness and varying with polar angle).…”

Section: Theoretical Analysis Of Aircraft Fuselagementioning

confidence: 99%

“…At certain speeds above the flutter speeds, leads to abrupt and large oscillations and ultimately catastrophic failure of the empennage. The research conducted by QiuJu et al [3] aims to characterize the variation in flutter patterns with modifications in the support stiffness provided by the rear fuselage. The main objective of the paper was to establish detailed designs of the rear fuselage which were modeled using Circumferentially Uniform Stiffness (CUS) or the Circumferentially Asymmetric Stiffness (CAS) configurations as a template, using optimization technique in tandem with Multi-Island Genetic Algorithm (MIGA).…”

Section: Numerical Analysis Of Aircraft Fuselagementioning

confidence: 99%

See 1 more Smart Citation

Recent Developments of an Aircraft Fuselage along Theoretical, Experimental and Numerical Approach - A Review

Potty¹,

Angelo²,

Rao

et al. 2019

ujme

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Expressed in nature's infinite subtleties, the Fuselage draws its inspiration from the streamlined body of a bird or a fish, channelizing the flow of air around, enabling its ease in flight. Spanning most of the aircrafts structure, it plays a crucial role in the ferrying of people and cargo, simultaneously balancing the shears due to the empennage and wing structures all in mid-air. Its structural integrity is often questioned by failures due to load or bad air during maneuvers, causing instability which has led many to intensively explore and develop an ideal fuselage. The behaviour of the fuselage is crucially determined by the structural integrity and aerodynamic performance. This paper is an attempt at collating the recent technological advances pertaining to the fuselage. We've streamlined and categorised the wide-ranging scholarly articles by three fundamentally varying approaches-Theoretical, Experimental and Numerical. The theoretical approach saw the authors test out their hypothesis by utilizing and constructing various mathematical models using scientific principles with no verification by actual experimentation or simulation work. The experimental approach pertains to those papers whose authors devised experiments, whose data was used to draw distinct conclusions. The numerical approach mainly dealt with heavy computational analysis using FEM and CFD analysis. Therefore, this paper serves as a compendium for researchers and developers attempting to familiarise themselves with the current advancements and developments in domain of fuselage technology.

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Section: Theoretical Analysis Of Aircraft Fuselagementioning

confidence: 99%

Section: Numerical Analysis Of Aircraft Fuselagementioning

confidence: 99%

Recent Developments of an Aircraft Fuselage along Theoretical, Experimental and Numerical Approach - A Review

Potty¹,

Angelo²,

Rao

et al. 2019

ujme

View full text Add to dashboard Cite

show abstract

“…More recently, the buckling behaviour and vibrations of elliptical cylindrical shells were investigated by Silvestre, 8 Ruiz-Terana and Gardner, 9 Silvestre and Gardner, 10 Abela and Gardner 11 and Khalifa. 12 Buckling and vibrations of continuous composite cylindrical shells with elliptical cross sections are considered in the papers published by Ganapathi et al, 13 Paschero and Hyer, 14 Khani et al, 15 Lo and Hyer, 16 Tornabene et al, 17 Boullea et al, 18 Kassegne and Chun 19 and Rouhi et al 20 In this paper, an approach to the finite element modelling of the buckling behaviour and vibrations of composite lattice cylindrical shells with elliptical cross sections is developed. This approach is demonstrated for a cantilever lattice shell with a rigid disk attached to its free end.…”

Section: Introductionmentioning

confidence: 99%

“…Buckling and vibrations of continuous composite cylindrical shells with elliptical cross sections are considered in the papers published by Ganapathi et al., 13 Paschero and Hyer, 14 Khani et al., 15 Lo and Hyer, 16 Tornabene et al., 17 Boullea et al., 18 Kassegne and Chun 19 and Rouhi et al. 20…”

Section: Introductionmentioning

confidence: 99%

Buckling and vibration of composite lattice elliptical cylindrical shells

Лопатин

Морозов

Shatov³

2017

Proceedings of the Institution of Mechanical Engineers, Part L:

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An approach to the finite element study of the buckling and dynamic behaviour of composite lattice cylindrical shells with elliptical cross sections is presented in this paper. The lattice shells are modelled as three-dimensional frame structures composed of curvilinear ribs using beam finite elements. A specialised algorithm is developed to generate the finite element model of the lattice shells based on multiple use of the repeating unit cell of the composite lattice structure. Using this model, the buckling behaviour of the shells subjected to axial loading and transverse bending are investigated. Fundamental frequencies of axial and transverse vibrations of the shells with a massive rigid disk attached to their ends are determined based on the modelling approach proposed in this work. The effects of parameters of the lattice structure on the values of critical buckling loads, buckling and vibration mode shapes, and the fundamental frequencies are examined using parametric analyses. Based on the computations, the angles of orientation of helical ribs delivering maximum critical loads and fundamental frequencies are identified. The results of this study can be applied to the design of the composite tubular bodies of spacecraft made in the form of cylindrical lattice shells with elliptical cross sections.

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Analytical and Numerical Solution of Static Problems of Non-Circular Cylindrical Shells

Maksymyuk,

Storozhuk,

Chernyshenko

2023

Advanced Structured Materials

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Parametric study of an elliptical fuselage made of a sandwich composite structure

Cited by 7 publications

References 11 publications

Recent Developments of an Aircraft Fuselage along Theoretical, Experimental and Numerical Approach - A Review

Recent Developments of an Aircraft Fuselage along Theoretical, Experimental and Numerical Approach - A Review

Buckling and vibration of composite lattice elliptical cylindrical shells

Analytical and Numerical Solution of Static Problems of Non-Circular Cylindrical Shells

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