Development of rational hybrid fuselage structure for prospective civil aircraft

Dubovikov, Evgeny; Fomin, V.; Kondakov, Ivan; Shanygin, A. N.; Vedernikov, Dmitry V.

doi:10.1177/0954410018785501

Cited by 4 publications

(2 citation statements)

References 3 publications

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“…The root of the problem of the BWB concept's low weight efficiency are the expenses related to high weight efficiency, namely, the costs needed to ensure the proper strength characteristics of high-loaded pressurized low-curvature (flat) panels. One solution to this problem was proposed in [6][7][8] based on double-lattice composite panels.…”

Section: Introductionmentioning

confidence: 99%

Manufacturing Aspects of Creating Low-Curvature Panels for Prospective Civil Aircraft

et al. 2019

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For this study, structural and manufacturing schemes for low-curvature pressurized fuselage panels were proposed, making it possible to provide high weight efficiency for the airframes of prospective civil blended wing-body (BWB) aircraft. The manufacturing scheme for low-curvature panels helped to achieve high strength characteristics of the composite details as well as decreased the labor input necessary for manufacturing and assembling. The beneficial features of the proposed structure are that the panels have a low weight, incur low manufacturing costs, and satisfy the demands of repairability.

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Section: Introductionmentioning

confidence: 99%

Manufacturing Aspects of Creating Low-Curvature Panels for Prospective Civil Aircraft

et al. 2019

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“…The analysis of advantages and disadvantages of different layered packages has shown that for concrete maximum level of loads on an investigated design, it is possible to define the most suitable structural layout from the point of view of weight efficiency [1]. In the given work the algorithm of development of hybrid layout for composite wing box has been generated, and its validation by designing the wing box of the plane of small aircraft was carried out.…”

Section: Introductionmentioning

confidence: 99%

Hybrid structural layout of wing box for small aeroplane

Zudova

Fomin

et al. 2019

MATEC Web Conf.

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The algorithm of optimization of the hybrid structural layout for the wing box has been developed. The wing box consisted of two parts; one of them (heavily loaded) had hybrid (lattice-truss) layouts, the other had conventional (black metal) layout. These parts was connected by use of interface structure. The basic objectives were sizing of load-bearing elements for each of the layouts, and to search for the interface position, providing minimum weight of the wing box structure. These tasks were solved with use of genetic algorithm. At searching for the interface optimal position the results of parametric FEM calculations were additionally used. A rational variant (65-73%) of the relative length of the wing box zone with lattice-truss structural layout has been obtained for the aircraft of regional airlines. This variant meets the constraints, and has the weight benefit (13-17%) compared with conventional structural layout.

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Advances and Future Challenges in Aircraft Fuselage Section Crashworthiness: A Critical Review

Rayhan,

Chunjin,

Rahman

et al. 2023

MENG

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Background: Crashworthiness studies the safety qualification of a vehicle (both airborne and road transports) to protect its occupants during an impact. Before an aircraft can receive transport certification, it must meet a number of crashworthiness requirements, such as the structure's deformation pattern, absorbed kinetic energy profile, and acceleration responses experienced by the components and human body models. Therefore, in recent times, crashworthiness has emerged as a crucial field of study during the early design stages of aircraft, along with other key parameters like weight reduction, load factor, fatigue life estimation, etc. Objective: The main objective of the present article is to undertake an in-depth analysis of the developments in crashworthiness related to the civil aircraft fuselage section. Furthermore, it aims to identify and address the future challenges that must be overcome to ensure the utmost safety of the occupants. Method: Based on the research objectives, the available literature is categorized into three major groups: (i) finite element code validation; (ii) improvement of the crashworthiness criteria; and (iii) impact on different surface models. A methodology to solve fuselage section crashworthiness is briefly described. A review of the research articles discussing general purpose energy absorbers for crashworthy design without any implementation to the fuselage structure is out of the scope of this article. Results: Experimental testing of fuselage section crashworthiness is expensive and non-repeatable. Furthermore, the intricate structure of the fuselage, with its numerous components, makes it nearly impossible to devise crashworthy design solutions through classical hand calculations alone. As a result, commercial software codes play a crucial role in the development of fuselage section crashworthiness, offering valuable assistance in overcoming these limitations. Conclusion: Future challenges of crashworthy design involve exploring novel materials and devices to mitigate injury during controlled crash conditions. An intriguing area of study would be the analysis of lattice components, as they have the potential to enhance crashworthiness. Furthermore, as newly designed fuselage sections emerge, it will be crucial to investigate and establish the necessary requirements to ensure compliance with crashworthiness certification standards.

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Development of rational hybrid fuselage structure for prospective civil aircraft

Cited by 4 publications

References 3 publications

Manufacturing Aspects of Creating Low-Curvature Panels for Prospective Civil Aircraft

Manufacturing Aspects of Creating Low-Curvature Panels for Prospective Civil Aircraft

Hybrid structural layout of wing box for small aeroplane

Advances and Future Challenges in Aircraft Fuselage Section Crashworthiness: A Critical Review

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