Buckling optimization of variable-stiffness composite panels based on flow field function

Hao, Peng; Liu, Chen; Yuan, Xiaojie; Wang, Bo; Li, Gang; Zhu, Tianyu; Niu, Fangyong

doi:10.1016/j.compstruct.2017.08.081

Cited by 73 publications

(19 citation statements)

References 56 publications

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“…One of the key elements of an aircraft is the composite stiffened panel, in which the skin is reinforced via adding a stringer for superior load carrying in both tension and compression. The main concern in the design of a stiffened panel, for sections of an aircraft under compression, is maximising the compressive load carrying due to the buckling phenomenon (Hao et al 2017). For the case of omega-stringer stiffened panels, the initial buckling starts in the skin (Kassapoglou 2013;Wang and Abdalla 2015), here referred to as the fundamental linear buckling load (LBL); however, it is known that beyond the first linear buckling, a stiffened panel could carry loads of several times the magnitude of the fundamental LBL before failure, here referred to as the nonlinear post-buckling strength (NPS).…”

Section: Introductionmentioning

confidence: 99%

Probabilistic optimisation of mono-stringer composite stiffened panels in post-buckling regime

Farokhi

Bacarreza

Aliabadi

2020

Struct Multidisc Optim

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In this paper, a multi-objective probabilistic design optimisation approach is presented for reliability and robustness analysis of composite structures and demonstrated on a mono-omega-stringer stiffened panel. The proposed approach utilises a global surrogate model of the composite structure while accounting for uncertainties in material properties as well as geometry. Unlike the multi-level optimisation approach which freezes some parameters at each level, the proposed approach allows for all parameters to change at the same time and hence ensures global optimum solutions in the given parameter design space (for both probabilistic and deterministic optimisations) within a certain degree of accuracy. The proposed approach is used in this study to conduct extensive multi-objective probabilistic and deterministic optimisations (without considering safety factors) on a mono-stringer stiffened panel. In particular, a global surrogate model is developed utilising the computational power of a highperformance computing facility. The inputs of the surrogate model are the omega-stringer geometry and the mechanical properties of the composite material, while the outputs are the fundamental linear buckling load (LBL) and the nonlinear postbuckling strength (NPS). LBL and NPS are obtained via detailed parametric finite element models of the mono-stringer stiffened panel; in the nonlinear model, the interface between the skin and the omega-stringer is modelled via cohesive elements to allow for debonding in the post-buckled regime. Extensive multi-objective optimisations are conducted on the surrogate model using deterministic and probabilistic approaches to examine the omega-stringer geometric parameters mostly affecting the system robustness and reliability. The differences between deterministic and probabilistic designs are highlighted as well.

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Section: Introductionmentioning

confidence: 99%

Probabilistic optimisation of mono-stringer composite stiffened panels in post-buckling regime

Farokhi

Bacarreza

Aliabadi

2020

Struct Multidisc Optim

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“…Variable angle tow placement technology allows fibre orientations to continuously vary with position over the entire plane of each ply, which provides the designer of aircrafts with a considerable opportunities in stiffness tailoring to design lightweight composite structures with enhanced performance. Previous studies [1,2,3,4,5,6,7,8,9] reveal that substantial improvement in buckling performance can be obtained by appropriately steering fibre path over each ply of the panel and the reason for this enhanced performance is mainly attributed to benign load redistribution offered by the VAT layup configuration.…”

Section: Introductionmentioning

confidence: 99%

Application of Rayleigh-Ritz formulation to thermomechanical buckling of variable angle tow composite plates with general in-plane boundary constraint

Chen

Nie

2020

International Journal of Mechanical Sciences

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Variable Angle Tow (VAT) composites always exhibit in-plane variable stiffness property, which provides the designer with an extended freedom in stiffness tailoring to achieve higher structural performance for lightweight composite structures. In this paper, a methodology based on a generalised Rayleigh-Ritz formulation is developed to study the thermomechanical buckling response of symmetrical VAT composite plates with general in-plane boundary constraint. It is assumed that the material is of temperatureindependent and the panel is exposed to an arbitrary in-plane temperature change. In the framework of thermoelastic theory, the principle of thermoelastic complementary energy in conjunction with Airy's stress function formulation, for the first time, is applied to solve the in-plane thermoelastic problem of the tow-steered plate. The non-uniform distribution of in-plane force resultant over the entire plane is determined by utilizing the Rayleigh-Ritz formulation enhanced by Lagrangian multiplier method. The merit of the proposed modelling strategy lies in that the application of Lagrangian multiplier method removes the restrictions inherent in conventional Rayleigh-Ritz formulation and thus provides generality to model general in-plane boundary constraint against thermal expansion or contraction. During the buckling analysis, the governing equation of thermomechanical buckling problem of the tow-steered plate under a combination of both

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“…Hao et al [20] optimized the stress distribution of variable-stiffness plates with cutout based on flow field formula. Falcó et al [21] analyzed the tow-drop effects on variable-stiffness panels using nonlinear finite element analyses.…”

Section: Introductionmentioning

confidence: 99%

Process-Induced Stress and Deformation of Variable-Stiffness Composite Cylinders During Curing

Zhang

Wang

2019

Materials

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Predicting and controlling process-induced deformation of composites during cure can play a significant role in ensuring the accuracy of manufacture and assembly of composite structures. In this paper the parametric investigation on the process-induced stress and deformation of variable-stiffness composite cylinders was presented. The Kamal model was used to simulate the cure kinetic for carbon/epoxy prepreg. A cure hardening instantaneously linear elastic (CHILE) constitutive model was adopted to determine the modulus of matrix resin. Self-consistent micro-mechanical models were employed to represent the mechanical properties and behaviors of the lamina. The three-dimensional model of a variable-stiffness composite cylinder was established using a linear fiber angle variation. The influence of the inner radius, the fiber end angle and the thickness on the stress and deformation of the variable-stiffness cylinder was evaluated using ABAQUS. The results show that the maximum stress increases with increases of the inner radius, the fiber end angle and the thickness. The inner radius of the cylinder have little effect on deformation, the deformation increases as the fiber end angle and the thickness increases. The present model and method can provide a useful tool for prediction of variable-stiffness composite cylinders.

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Buckling optimization of variable-stiffness composite panels based on flow field function

Cited by 73 publications

References 56 publications

Probabilistic optimisation of mono-stringer composite stiffened panels in post-buckling regime

Probabilistic optimisation of mono-stringer composite stiffened panels in post-buckling regime

Application of Rayleigh-Ritz formulation to thermomechanical buckling of variable angle tow composite plates with general in-plane boundary constraint

Process-Induced Stress and Deformation of Variable-Stiffness Composite Cylinders During Curing

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