Durable and Damage-Tolerant Composite Commercial Aircraft Structure Design Approach

1978 ◽  
Vol 15 (1) ◽  
pp. 33-39 ◽  
Author(s):  
J. E. McCarty ◽  
R. W. Johnson
Keyword(s):  
Structure Design ◽  
Design Approach ◽  
Commercial Aircraft ◽  
Aircraft Structure ◽  
Damage Tolerant

Study on the Impact Limiter Design in Spent Fuel Transfer Cask in Nuclear Power Plants

2020 ◽  
Author(s):  
Yuchen Hao ◽  
Yue Li ◽  
Jinhua Wang ◽  
Bin Wu ◽  
Haitao Wang
Keyword(s):  
Nuclear Power ◽  
Power Plants ◽  
Nuclear Power Plants ◽  
Theoretical Method ◽  
Structure Design ◽  
Design Approach ◽  
Spent Fuel ◽  
Typical Structure ◽  
Explicit Finite Element ◽  
The Impact

Abstract In nuclear power plants, the amount of spent fuel stored on-site is limited. Therefore, it is necessary to be shipped to off-site storage or disposal facilities regularly. The key risk in the transfer of spent fuel involves a release of radiation that could cause harmful effects to people and the environment. Transfer casks with impact limiters on both ends are always employed to ensure safe containment of radioactive materials, which should be verified by the 9 meters drop test onto an unyielding surface according to IAEA SSR-6. In this paper, we focus on the influence of the impact-limiter parameters, including geometry dimensions and mechanical properties, on the results of drop events to achieve an optimized approach for design. The typical structure of impact limiter is bulk energy-absorbed material wrapped by thin stainless-steel shells. Compared to traditional wood, foam has advantages of isotropy and steady quality. In this paper, theoretical and numerical methods are both adopted to investigate the influence of impact limiters during hypothetical accidental conditions for optimizing buffer influence and protecting the internal fuel components. First of all, a series of polyurethane foam is selected according to the theoretical method, because its mechanical property is related to density. Therefore, using explicit finite element method to investigate the influence of parameters of foam in impact limiter. These discrete points from the above result can be utilized to establish damage curves by date fitting. Finally, a design approach for spent fuel transfer cask is summarized, to provide a convenient formula to predict the damage and optimize structure design in drop condition. Furthermore, this design approach can be applied in the multi-module shared system of SNF, which can contain different fuel assemblies.

scholarly journals Towards Direct-Gap Silicon Phases by the Inverse Band Structure Design Approach

2013 ◽  
Vol 110 (11) ◽  
Author(s):  
H. J. Xiang ◽  
Bing Huang ◽  
Erjun Kan ◽  
Su-Huai Wei ◽  
X. G. Gong
Keyword(s):  
Band Structure ◽  
Structure Design ◽  
Design Approach

Structural Optimization Research of Composite Aircraft Based on Different Wing Stiffness Constraints

2012 ◽  
Vol 466-467 ◽  
pp. 282-286
Author(s):  
Li Liang ◽  
Sun Qin
Keyword(s):  
Structural Optimization ◽  
Bending Stiffness ◽  
Structure Design ◽  
Aircraft Structure ◽  
Optimization Analysis ◽  
Torsion Stiffness

Wing stiffness, mainly including bending stiffness and torsion stiffness, is very important in aircraft structure design. In order to research the relation between wing stiffness and optimization results, this paper makes optimization analysis to a composite T-tail configuration and a composite flying wing configuration based on different wing stiffness constraints, and some valuable conclusions are achieved.

scholarly journals Comment on “Towards Direct-Gap Silicon Phases by the Inverse Band Structure Design Approach”

2014 ◽  
Vol 112 (19) ◽  
Author(s):  
Maximilian Amsler ◽  
José A. Flores-Livas ◽  
Silvana Botti ◽  
Miguel A. L. Marques ◽  
Stefan Goedecker
Keyword(s):  
Band Structure ◽  
Structure Design ◽  
Design Approach

Experimental and numerical investigations of compression stability of stiffened composite panel with ply interleaving

2017 ◽  
Vol 51 (26) ◽  
pp. 3647-3656 ◽  
Author(s):  
Xiaoliang Geng ◽  
Fanfan Ji ◽  
Jiu Wang ◽  
Wang Dou ◽  
Peiyan Wang ◽  
...  
Keyword(s):  
Prediction Method ◽  
Adhesive Layer ◽  
Structure Design ◽  
Composite Panel ◽  
Stiffened Panel ◽  
Surrounding Area ◽  
Aircraft Structure ◽  
Internal Damage ◽  
Reliable Solution ◽  
The Relationship

A novel composite layup technique (ply interleaving) is proposed to satisfy the extraordinary needs in aircraft structure design. Buckling experiments and corresponding simulations with different configurations are carried out to study the mechanical properties of the stiffened panel with this ply layout and get a suitable numerical prediction method. A ply-by-ply-based modeling technique is applied to characterize the real discontinuity in each ply. Additionally, the relationship between the macroscopic buckling and damage evolution is investigated by the comparative analyses of experiments and simulations. The investigations show the following results: the panel with ply interleaving has a considerable anti-buckling capability besides its flexible layout; both adhesive layer damage and lamina damage should be included in the simulation for obtaining reliable solution; the panel would buckle while adhesive layer damage occurs between stiffeners and skin, which initiates firstly in the ply interleaving zone and then expands to the surrounding area; internal damage of each ply also originates around discontinuities then develops rapidly, leading to the panel failure. The prediction results of buckling and failure show good agreements with the experimental results, so the suggested simulation technique is verified to be an effective method to study the mechanical behavior of the composite plate with preset discontinuities.

Analysis of Aircraft Composite Structural Health Monitoring and Life Prediction Technology

2011 ◽  
Vol 88-89 ◽  
pp. 515-523
Author(s):  
Xiao Chuang Tao ◽  
Chen Lu
Keyword(s):  
Structural Health Monitoring ◽  
Health Monitoring ◽  
Life Prediction ◽  
Health Management ◽  
Structure Design ◽  
Prognostics And Health Management ◽  
Aircraft Structure ◽  
Reliability Design ◽  
Structural Health ◽  
Critical Issues

Along with the constantly updated aircraft structure design, higher performance and reliability design indexes as well as usage of a large portion of new materials especially lightweight composite materials put forward higher requirements for aircraft structure safety. The damage detection, diagnosis, forecast and management become an important part of aircraft Prognostics and Health Management(PHM).In order to better build the Structural Prognostics and Health Management system of a new generation aircraft for the improvement of security, task reliability and economy, this paper introduced the development situation of aircraft composite structural health monitoring and life prediction technologies, classified the existing technologies, and then discussed the principle, quality point, applicability and application situation, finally, pointed out several critical issues which still need further study.

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