An investigation into the performance characteristics of top-hat stiffener to shell plating joints

Shenoi, R.A.; Hawkins, G.L.

doi:10.1016/0263-8223(94)00032-8

Cited by 22 publications

(13 citation statements)

References 4 publications

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“…This difference is attributed to the different boundary condition -the hat-only models were fixed on all translation and rotation on their cross sections, while the single-hatstiffened panel models were only simply supported on the bottom flange of the stiffener/skin plate. Hat stiffener height h significantly affects stiffened plate deflection, as evident from results of IDs 1,3,7,11;2,5,9,13;4,8,12,15;6,10,14,16 for which h monotonically increases, while W 1 and W 2 are fixed. The effect of hat stiffener width (W 1 and W 2 ) is greater when the height is smaller, but diminishes for stiffeners with greater height.…”

Section: Parametric Finite Element Simulationsmentioning

confidence: 84%

“…(10) a mn is defined as: (11) for all m, n =1, 3, 5, …; where p is the applied pressure, the load per unit area, and (12) for all other m and n.…”

Section: Analytical Solutionmentioning

confidence: 99%

“…Some studies [10,11] focusing on the stiffener plate joints examined the key aspects defining the performance characteristics. In particular, Shenoi and Hawkins [12] reported an initial attempt to understand design sensitivity of composite hat stiffeners and hat-stiffened panels.…”

Section: Introductionmentioning

confidence: 99%

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Parametric modeling, higher order FEA and experimental investigation of hat-stiffened composite panels

Jin

Mier

et al. 2015

Composite Structures

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Section: Parametric Finite Element Simulationsmentioning

confidence: 84%

“…(10) a mn is defined as: (11) for all m, n =1, 3, 5, …; where p is the applied pressure, the load per unit area, and (12) for all other m and n.…”

Section: Analytical Solutionmentioning

confidence: 99%

See 1 more Smart Citation

Parametric modeling, higher order FEA and experimental investigation of hat-stiffened composite panels

Jin

Mier

et al. 2015

Composite Structures

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“…Kumar et al studied the transient response of laminated stiffened plates using MSC/Patran and LS-DYNA3D [6] and Kristinsdottir et al [7] presented an optimization formulation for the design of large panels when loads vary over the panel. Junhou et al and Shenoi et al [8,9] examined the key aspects defining the performance characteristics of hatstiffener joints in marine structures. Paul et al [10] performed an integrated step-by-step design and analysis procedure for the hat-stiffened panels loaded in axial compression using the computer code BUSTCOP.…”

Section: Optimum Composite Structuresmentioning

confidence: 99%

Design Optimization and Higher Order FEA of Hat-Stiffened Aerospace Composite Structures

Jin¹

2019

Optimum Composite Structures

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Sizing of hat-stiffened composite panels is challenging because of the broad design hyperspace in several geometric and material parameters available to the designer. Design tasks can be simplified if parameter sensitivity analysis is performed a priori and design data is made available in terms of a few important parameters. In this chapter, design sensitivity analysis is performed using finite element analysis (FEA) and analytical solution models. Manufacturing and experimental measurements of a hat-stiffened composite structure is performed to validate the FEA and idealized analytical solutions. This is an attempt to initiate a structural architecture methodology to speed the development and qualification of composite aircraft that will reduce design cost, increase the possibility of content reuse, and improve time-to-market. In particular, FEA results were compared with analytical solutions to develop a design methodology that will allow extensive reuse of parametric hat-stiffened panels in the design of composites structural components. This methodology is now widely utilized in developing a library of commonly used, built-in, composite structural elements in design of modern aircrafts. In this chapter, hat stiffened composite panels' geometric parameter sensitivity analysis work were parametrically investigated using finite element analysis (FEA), analytical solution models and experimental testing on manufactured parts in order to develop structural architectures that speed development and qualification of composite aircraft which has broad benefits in reducing cost, increasing content reuse and improving time-to-market. In particular, FEA results were compared with analytical solutions and a design methodology was developed to allow extensive reuse of parametric elements in structural design of composites and to achieve expedited design, verification, validation, and airworthiness certification and qualification. The goal of this work is to provide the aviation industry with the most up-to-date databases for the application of advanced composite materials incorporated into parametric models to eliminate redundancies in the current process. The work results include a correlated material database, an optimized model component library and a standardized

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“…In addition to the manufacturing aspects mentioned above it is important to develop a modelling capability to allow designs to be optimized without extensive fullscale testing. Smith [3] discussed the analysis of stiffened panels and work has been performed by Shenoi and coworkers [4,5]. There are some similarities between the stiffened panels in ships and those used in the aerospace industry.…”

Section: Introductionmentioning

confidence: 99%

Design, manufacture and testing of stiffened panels for marine structures using adhesively bonded pultruded sections

Davies

Choqueuse

Bigourdan

et al. 2004

Proceedings of the Institution of Mechanical Engineers, Part M:

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This paper presents results from a programme designed to evaluate the use of bonded pultrusion sections to replace overlaminated stiffeners on composite sandwich panels for marine applications. First, the existing solution is described and results from uniform pressure loading tests of these panels are presented. Second, the design of bonded pultruded stiffeners is discussed, including results from preliminary tests to evaluate adhesives, and finite element calculations to optimize stiffener geometry. Finally, results from tests on two bonded stiffened panels are given and failure loads and mechanisms are compared to predictions.

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An investigation into the performance characteristics of top-hat stiffener to shell plating joints

Cited by 22 publications

References 4 publications

Parametric modeling, higher order FEA and experimental investigation of hat-stiffened composite panels

Parametric modeling, higher order FEA and experimental investigation of hat-stiffened composite panels

Design Optimization and Higher Order FEA of Hat-Stiffened Aerospace Composite Structures

Design, manufacture and testing of stiffened panels for marine structures using adhesively bonded pultruded sections

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