Investigation on a multispar composite wing

Stamatelos, D.G.; Labeas, G.

doi:10.1177/0954410011406476

Cited by 6 publications

(5 citation statements)

References 14 publications

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“…The drop is significant at the beginning, up to four spars and less drastic for five and six spars. This trend has been observed by other authors also [8,11]. The present method allows quantifying this trend when the skins are allowed to buckle below ultimate load at any preselected percentage.…”

Section: Effect Of Number Of Sparssupporting

confidence: 82%

“…In Eqs. (11) and 12, a is the length of the flange, and b is the long dimension of the flange cross section.…”

Section: Stability Checksmentioning

confidence: 99%

“…Chintapalli et al [10] focused on the optimization of stiffened panels in a wing box using buckling for compression and fracture mechanics damage tolerance-based analysis for tension dominated loading. Stamatelos and Labeas [11] considered the effect of strain or stress allowables on the wing-box design and showed that multi-spar wings may lead to lower weight designs. Soloshenko [12] studied how various design concepts affect the stress allowables for a wing design with emphasis on local effects such as the wing root splice joint.…”

Section: Introductionmentioning

confidence: 99%

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Weight trades in the design of a composite wing box: effect of various design choices

et al. 2018

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A process to efficiently design composite wing boxes is presented. It uses analytical and semi-empirical equations for failure modes such as material strength, plate buckling, stiffener column buckling and stiffener flange or web crippling. Laminate layups for the different components are selected in accordance with basic engineering rules and guidelines and are updated as necessary to meet the local loads. The emphasis is in allowing buckling of skins at any fraction of the ultimate load and allowing local load redistribution from buckled to non-buckled panels to save weight. The design process is automated and the design can be automatically transferred over to a commercial finite-element code for detailed design and validation. The effects on weight of number of spars, ribs, and stiffeners as well as the fraction of ultimate load at which buckling is allowed are examined and insight is gained to which of these the weight is most sensitive to. In addition, the effect of minimum gage on weight was found to be a driver.

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Section: Effect Of Number Of Sparssupporting

confidence: 82%

“…In Eqs. (11) and 12, a is the length of the flange, and b is the long dimension of the flange cross section.…”

Section: Stability Checksmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Weight trades in the design of a composite wing box: effect of various design choices

et al. 2018

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“…The developed parametric FE model is solved linearly and the stresses, strains and displacements of the flap's structural components are calculated. The preliminary structural sizing results are obtained by comparing the calculated static analysis results (stress, strain and displacement) with the respective allowable values in an iterative procedure (Stamatelos, 2010), as depicted in flow chart of Figure 4. In this manner, the member sizing is checked whether it fulfils the design constraints with a safety factor of 1.5 or not.…”

Section: Description Of the Design Approachmentioning

confidence: 99%

Airfoil morphing based on SMA actuation technology

Karagiannis

Stamatelos

Σπαθόπουλος

et al. 2014

Aircraft Eng & Aerospace Tech

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Purpose -This study aims to develop an innovative actuator for improving the performance of future aircraft, by adapting the airfoil shape according to the flight conditions. The flap's camber of a civil regional transportation aircraft's trailing edge actuated and morphed with the use of shape memory alloys (SMA) actuator technology, instead of the conventional split flap mechanism is studied. Design/methodology/approach -For the flap's members sizing an efficient methodology is utilised based on finite element (FE) stress analysis combined to analytically formulated design criteria. A mechanical simulation within an FE approach simulated the performance of the moving rib, integrating both aerodynamic loads and SMA phenomenology, implementing Lagouda's constitutive model. Aim of this numerical simulation is to provide guidelines for further development of the flap. A three-dimensional assembly of the flap is constructed to produce manufacturing drawing and to ensure that during its morphing no interference between the members occurrs. Eventually, the manufactured flap is integrated on a test rig and the experimental characterisations under no and static loads, and dynamic excitation are performed. Findings -Experimental results showed that the rib's SMA mechanism can adequate function under load providing satisfactory morphing capabilities. Originality/value -The investigated approach is an internal into the flap mechanism based on the shape memory effect of thin wires. In the developed mechanism, SMA wires are attached to the wing structure, where they function as actuating elements.

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“…Another work [25], focusing on the optimization of stiffened panels of a metallic wing box using buckling constraints and fatigue, is aiming to determine a lighter design. A significant contribution is offered by Stamatelos and Labeas in [26], who showed that multispar configurations can lead to lighter designs than the respective conventional under certain circumstances. Their investigation is based on the methodology presented hereafter.…”

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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Investigation on a multispar composite wing

Cited by 6 publications

References 14 publications

Weight trades in the design of a composite wing box: effect of various design choices

Weight trades in the design of a composite wing box: effect of various design choices

Airfoil morphing based on SMA actuation technology

Towards the Design of a Multispar Composite Wing

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