Structural analysis and topology design optimization of load bearing elements of aircraft fuselage structure

Htet, Tun Lin

doi:10.1088/1757-899x/709/4/044113

Cited by 9 publications

(3 citation statements)

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“…Суть метода оптимизации топологии заключается в просчете программным комплексом Ansys наиболее выгодного способа размещения заданного количества материала, нагруженного известным набором сил, в ограниченном пространстве таким образом, чтобы обеспечивалась наименьшая масса конструкции при достаточной прочности и жесткости. Результаты работы, опубликованные в статье [26], показывают эффективность данного метода и снижение массы конструкции на 18,36 %.…”

Section: уточнение результатов использования новых конструкционных ма...unclassified

Analysis of Mass Characteristics of Aircraft Fuselage Construction Materials

Припадчев¹,

Osipov²,

Magdin³

et al. 2022

Vestnik IzhGTU imeni M.T. Kalashnikova

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Theoretical formulas for calculating the mass of an airplane fuselage are analyzed, and the parameters affecting the final mass of the structure are determined: geometric and physical characteristics of the power set, that depend on the strength, density, and stiffness of the material of the power set elements. The advantages of weight and strength characteristics of composite materials and the latest structural alloys over the characteristics of traditional materials that are used in aircraft and rocket engineering in the design of aircraft are considered. Comparison and analysis of several types of composite materials, as well as third-generation aluminum alloys with a chemical composition improved by alloying with lithium, by the criteria of density, strength, yield, and stiffness are carried out. The effect of applying different modern structural materials with reduced density and increased strength on the fuselage structure mass of the aircraft is considered and analyzed. The results of several analytical calculations by a number of authors of scientific publications, which show a significant reduction in the weight of the fuselage structure when using composite materials instead of traditional structural metal alloys such as D16-T and AA2124, are presented. An efficiency of a method of additionally aircraft structure weight reduction made of composite materials by optimizing the topology of the power elements of the structure - a method of optimizing the structural material distribution to create a load-bearing structure, which consists of selecting such geometric dimensions and shapes of the power elements, at which the material consumption, and therefore the final structure mass is the lowest with preserved strength characteristics of the structure, is considered. A conclusion about the obvious superiority of mechanical and weight properties of polymer composites reinforced with carbon or organic fiber fillers over lightweight third-generation aluminum alloys and laminated metal-polymer materials has been made based on the analysis of the results of the conducted research. The results of the analyzed studies also confirm the conclusions drawn, showing a 29.9 % decrease in the weight of the fuselage structure, and the optimization of the power element topology proposed as an additional weight reduction will theoretically make it possible to reduce the material intensity of the composite structure, thereby reducing its weight by about 18 %.

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Section: уточнение результатов использования новых конструкционных ма...unclassified

Analysis of Mass Characteristics of Aircraft Fuselage Construction Materials

Припадчев¹,

Osipov²,

Magdin³

et al. 2022

Vestnik IzhGTU imeni M.T. Kalashnikova

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“…Therefore, topological optimization proved to be a powerful tool to support designers in choosing the proper design process. Htet [23] optimized the topology of aircraft fuselage ribs using Ansys software. The results of this research showed that by using the topological optimization method, 18.36 percent of the original weight could be reduced.…”

Section: Introductionmentioning

confidence: 99%

Topological optimization of structures with thermomechanical loading under compliance constraints for 3D printing applications

Mojiri,

Shafiei,

Nourollahi

2024

Preprint

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Currently, due to the high costs of production and expensive raw materials, approaches, including, making models smaller and lighter, are especially considered in the design of structures. In order to better describe the capabilities, efficiency, and limitations of an innovative field in design methodology, called topology optimization, various practical problems under different loadings and boundary conditions were evaluated in this study. Optimization algorithms were used in ANSYS software for the optimization of a cantilever beam under static loading, double-girder beam and a dome-shaped geometry under static and thermal loading, a hot fluid transfer tee and an engine exhaust manifold under static loading and convection heat transfer. The results showed that the reduced volume in the final models were equal to 52.88%, 50.05%, 51.85%, and 35.02%, respectively. Consequently, this reduced volume causes some increase in the tension, and displacement of the final model, which the designer can adjust them according to the limitations governing the problem. Furthermore, the amount of increase in the average value of the stress in the cantilever beam, double-girder beam, and dome-shaped geometry were 88, 800, and 6 MPa, and the average amount of displacement in these samples increased by 10.2%, 200%, and 3.3%, respectively. Unforeseen challenges, and manufacturability of optimized problems were investigated by 3D printing of a dome-shaped model using the FDM method, which illustrated that the output product has a suitable level of accuracy and smoothness. Subsequently, by using supporting structures, three-dimensional holes were created with proper precision in the 3D-printed sample, which satisfied the manufacturability of relatively complex models without using traditional production methods.

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“…Delamination simulation in composite laminates subjected to static or impact loads [19] has benefited greatly from CZM-based approaches. Some authors have subsequently expanded on these methods by include the Paris law within the cohesive constitutive model [20], thereby making it possible to account for degradation due to the cyclic load.…”

Section: Introductionmentioning

confidence: 99%

Determination of the fatigue behavior of the composite Single-Stringer structure based on the quasi-static method

Shomran

Faisal

Hussein

et al. 2023

EEJET

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In this investigation, the Mechanical Behavior of the composite Single-Stringer structure was subjected to numerical analysis in order to better understand its properties. As the primary material for the modeling process, the carbon-epoxy IM7/8552 with quasi-isotropic Layups has been utilized. The outcomes of the numerical analysis that were carried out on the structure while it was in its static state have been put into the structural tool that was developed by the ANSYS programme. The fundamental boundary conditions have been defined on the basis of the information that was received from the testing. Static forces with a combined magnitude of 13.7 kN are being applied to the composite Single-Stringer structure. Shear stresses, direction deformation, von mises stresses, and total deformation have all been shown to have an effect on a material's mechanical behaviour, and this effect has been demonstrated. The calculations indicate that there is a maximum amount of bending that can take place as a direct result of the load that is being applied, and that amount is equal to 0.0147. The maximum amount of bending that can take place as a direct result of the load that is being applied is equal to 0.0147. As a consequence of the application of 13.7 kN of pressure, the von Mises stress, which is also frequently referred to as comparable stresses, has reached 51.9 MPa. Shear stresses have been estimated in three distinct plans, and it was discovered that the shear stress that was applied to the XY plane achieved a maximum of 15 MPa, but the shear stress that was applied to the XZ plane reached a maximum of 9.8 MPa. This was found. Both aeroplanes were put through precisely the same amount of tension at the exact same time. At this time, the shear stress on the plane YZ has reached a level of 1.5 MPa.

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Structural analysis and topology design optimization of load bearing elements of aircraft fuselage structure

Cited by 9 publications

References 0 publications

Analysis of Mass Characteristics of Aircraft Fuselage Construction Materials

Analysis of Mass Characteristics of Aircraft Fuselage Construction Materials

Topological optimization of structures with thermomechanical loading under compliance constraints for 3D printing applications

Determination of the fatigue behavior of the composite Single-Stringer structure based on the quasi-static method

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