Curvilinearly T-Stiffened Panel-Optimization Framework Under Multiple Load Cases Using Parallel Processing

Mulani, Sameer B.; Duggirala, Vedavyas; Kapania, Rakesh K.

doi:10.2514/1.c032064

Cited by 12 publications

(5 citation statements)

References 27 publications

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“…where σ stiff is the maximum stress in the stiffener and F cc is the maximum allowable stress for stiffener, which is calculated using Eq. 5 in reference [14]. Therefore, optimization problem for stiffened panel can be formulated as follows:…”

Section: Formulation Of the Optimization Problem Of Stiffened Panelsmentioning

confidence: 99%

“…Mulani et al [13] developed a framework to design grid-stiffener panels using variables include the orientation, the shape of the stiffeners and the spacing between the stiffeners as well as other sizing variables. Mulani et al [14] utilized the optimization framework EBF3PanelOpt to design stiffened panels with T curvilinear stiffeners. The result showed that when the loads were applied through the stiffeners, the best optimal design have the straight T stiffeners.…”

Section: Introductionmentioning

confidence: 99%

“…Since existing charts, formulations and programs, such as PANDA2 [15][16][17] and COSTADE [18], are aim to the traditional stiffened panels, design of new and complex panels with curvilinear stiffeners have to rely more on numerical simulations, such as finite element method. Therefore, optimization of curvilinear stiffened panel in the relative studies [1][2][3][4][5][6][7][8][9][10][11][12][13][14], is based on finite element models-2D shell models. The problem of this kind of model is that as the number of stiffeners increases as well as the stiffener cross-section becomes complex, such as 'T' and 'hat' stiffener, the process of geometry creating and meshing becomes difficult and time consuming.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Optimum Design of Curvilinear Stiffened Panels with Stiffening Beams

Yang

Song

Zhong

2013

AMM

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The paper presents a framework for design and optimization of curvilinear stiffened panels with any cross-section shape of stiffener. Within this framework, the weight of stiffened panel applied complex loads, is minimized under the constraints of structural responses include global buckling, maximum stress and crippling. Then, a stiffened panel with two blade curvilinear stiffeners is optimized using this framework, and the optimum performs better than another existing design. Finally, it is concluded that stiffening beam is suitable for simulate stiffener sustains part of applied load directly.

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Section: Formulation Of the Optimization Problem Of Stiffened Panelsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Optimum Design of Curvilinear Stiffened Panels with Stiffening Beams

Yang

Song

Zhong

2013

AMM

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“…Most of the wing studies focus on the wing structural optimization, in order to determine the lightest and strongest internal wing structure. Characteristic studies are carried out, by several researchers, by employing optimization routines regarding the stiffened panels [2][3][4][5], the position of the spars and ribs [6,7]. Furthermore, topology optimization is frequently employed to determine the optimum location of certain structural components under static and aeroelastic loads [8,9].…”

Section: Introductionmentioning

confidence: 99%

Towards the Design of a Multispar Composite Wing

Stamatelos

Labeas

2020

Computation

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In the pursuit of a lighter composite wing design, fast and effective methodologies for sizing and validating the wing members (e.g., spar, ribs, skins, etc.) are required. In the present paper, the preliminary design methodology of an airliner main composite wing, which has an innovative multispar configuration instead of the conventional two-spar design, is investigated. The investigated aircraft wing is a large-scale composite component, requiring an efficient analysis methodology; for this purpose, the initial wing sizing is mostly based on simplified Finite Element (FE) stress analysis combined to analytically formulated design criteria. The proposed methodology comprises three basic modules, namely, computational stress analysis of the wing structure, comparison of the stress–strain results to specific design allowable and a suitable resizing procedure, until all design requirements are satisfied. The design constraints include strain allowable for the entire wing structure, stability constraints for the upper skin and spar webs, as well as bearing bypass analysis of the riveted/bolted joints of the spar flanges/skins connection. A comparison between a conventional (2-spar) and an innovative 4-spar wing configuration is presented. It arises from the comparison between the conventional and the 4-spar wing arrangement, that under certain conditions the multispar configuration has significant advantages over the conventional design.

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“…In addition to the curvilinear fiber format, a curvilinear stiffener concept was proposed for unitized metal structures driven by the development of aforementioned EBF3 technology. 19 Kapania et al then conducted a series of studies on the curvilinearly stiffened unitized panels, [20][21][22] including the development of an optimization framework EBF3PanelOpt 23 and experimental evaluation of test panels built by EBF3 under compression-shear loading conditions. 24 This curvilinear concept was also extended to the design of supersonic aircraft wing-boxes.…”

Section: Introductionmentioning

confidence: 99%

Optimization design of unitized panels with stiffeners in different formats using the evolutionary strategy with covariance matrix adaptation

Yang

Yue

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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Curvilinear stiffener concept has been introduced to aircraft panel structures most recently for possible further weight reduction during optimization design. However, due to enlarged design space and high design complexity, more computational time is needed to optimize curvilinearly stiffened panels. Considering the requirement for both lighter structure and less design time, optimization designs of a unitized panel with stiffeners in three different formats, i.e. curvilinear, oblique, and evenly distributed straight, are conducted under various loading conditions to figure out which stiffener format should be selected in a real design environment. Four single loading cases with different compression-shear ratios and a set of multiple load cases are considered. Evolution strategy with covariance matrix adaption is combined with sequential quadratic programming to seek out the optimum structure with minimum mass taking into account buckling and strength constraints. Comparative analysis of the optimization results indicates that evenly distributed straight format is suitable for compression-dominant loading conditions whereas curvilinear format become superior in case that shear loading is considerable or multiple biaxial compression and shear loads are applied. Besides, curvilinear format adds more design flexibilities to the stiffeners, which enables them to play a more important role in the optimized structures. Furthermore, evolution strategy with covariance matrix adaption is found to be more efficient than particle swarm optimization for this optimization problem. This study can provide a useful guidance for future optimization design of aircraft structures.

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Curvilinearly T-Stiffened Panel-Optimization Framework Under Multiple Load Cases Using Parallel Processing

Cited by 12 publications

References 27 publications

Optimum Design of Curvilinear Stiffened Panels with Stiffening Beams

Optimum Design of Curvilinear Stiffened Panels with Stiffening Beams

Towards the Design of a Multispar Composite Wing

Optimization design of unitized panels with stiffeners in different formats using the evolutionary strategy with covariance matrix adaptation

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