Numerical and experimental value added of Multi-Instrumented Technological Evaluator for the analysis of thick monolithic composite structures with singularity details

Torres, Mauricio; Collombet, Francis; Douchin, Bernard; Crouzeix, Laurent; Grunevald, Yves-Henri

doi:10.1016/j.compstruct.2015.02.075

Cited by 9 publications

(20 citation statements)

References 21 publications

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“…The project called "Multi-sensor Instrumentation for the Composite Materials and Structures (I2MC)" puts together the expertise of seven research teams with the goal to study the in-core instrumentation of composites structures by applying the Multi-Instrumented Technological Evaluator toolbox (MITE toolbox) [40][41][42].…”

Section: Introductionmentioning

confidence: 99%

Multi-instrumentation monitoring for the curing process of a composite structure

et al. 2020

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This is a PDF file of an article that has undergone enhancements after acceptance, such as the addition of a cover page and metadata, and formatting for readability, but it is not yet the definitive version of record. This version will undergo additional copyediting, typesetting and review before it is published in its final form, but we are providing this version to give early visibility of the article. Please note that, during the production process, errors may be discovered which could affect the content, and all legal disclaimers that apply to the journal pertain.

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Section: Introductionmentioning

confidence: 99%

Multi-instrumentation monitoring for the curing process of a composite structure

et al. 2020

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“…These failure mechanisms are much more complex than those of conventional metallic materials, leading to new problems for maintenance tasks and repair procedures. Even when numerous analytical, experimental and numerical efforts have been done with the aim to forecast stress, strain and failure mechanics for composite structures, the majority of these studies have been carried out at laboratory scale, where analytic accuracy is still reasonable although budget and infrastructure restrictions [7][8][9][10].…”

Section: Introductionmentioning

confidence: 99%

Manufacturing Process of High Performance–Low Cost Composite Structures for Light Sport Aircrafts

Torres

Piedra

Ledesma³

et al. 2019

Aerospace

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This work describes the technological and scientific efforts on designing, manufacturing and testing validation for high performance-low cost composite structures for Light Sport Aircrafts (LSA). A Mexican initiative to conceive, manufacture and assembly a Light Sport Aircraft has been developed by using Computational Fluid Dynamics (CFD), Finite Element Analysis (FEA) and Liquid Composite Manufacturing (LCM). These consolidated techniques are used to characterize novel approaches to manufacturing and assembly carbon-fiber based structural components. As large structures are manufactured via Vacuum Assisted Resin Infusion (VARI), impregnation strategies are studied to minimize inner flaws and also to improve the manufacturing time and surface quality of each component. The first case of study, to validate this methodology, involves non-structural components such as the cowling. Control surfaces (ailerons, rudder, elevator and flaps) have been manufactured, each of them having common issues but also unique challenges. As an example, a second case of study, the aileron main beam is analyzed. Furthermore, test portfolio will be developed with the goal to perform 1-to-1 scale mechanical tests for validation in compliance with ASTM standards.

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“…This strategy consists in designing a set of composite panels based on B727-200 non-airworthy aircraft to test optimized bonded repairs. The design of the repairs for the stiffened panels will be done using the innovative philosophy of the Multi-Instrumented Technological Evaluator Toolbox [4,16]. Based on limited-sized specimens called Technological Evaluators, the MITE Toolbox is conceived for monitoring structural components from the very beginning of the manufacturing process till the in-service condition, with the aim to study bonded, riveted and bonded/riveted interfaces, to optimize stress transfers during mechanical tests, or to design new repairing configurations.…”

Section: Journal Of Aeronautics and Aerospace Engineeringmentioning

confidence: 99%

“…Finally, the multi-sensor instrumentation, takes advantage on placing sensors inside and outside the composite structure. The instrumentation can be done by using multiple devices (optical fibers, piezoelectric, tunneling sensors, thermocouples, and strain gauges) combined with non-contact technique such as Digital Image Correlation (DIC) [4,9,10]. By confronting the numerical and experimental data sets an accurate calculation/test correlation can be achieved.…”

Section: Introductionmentioning

confidence: 99%

“…Dealing with any aeronautical structural detail involves four aspects: 1) composite structure with singularity details; 2) multi-axial modular testing machine; 3) multi-scale numerical modeling and 4) multisensor instrumentation [4]. Concerning the composite structure, this one has to be created case by case, in a representative scale, in order to regroup the specific singularity details of interest, such as stiffener-skin interfaces.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Mechanical Behavior of a Fuselage Stiffened Carbon-Epoxy Panel under Debonding Load

Torres¹,

Ea²,

Hernández-Moreno³

et al. 2018

J Aeronaut Aerospace Eng

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The present project sets out the analysis of mechanical behaviour of a carbon-epoxy stiffened panel under bending load. For this purpose, the National Polytechnic Institute of Mexico counts with a non-airworthy B727-200 as experimental platform. The first step was to calculate the aerodynamics loads and flight envelope of the aircraft. Secondly, the selection of the fuselage section is performed in order to identify an adequate stiffened panel for the study. The structural elements of the panel, skin and stiffeners were manufactured by VARTM and glued with high strength adhesive. The load, in bending condition, was imposed by a structural testing machine in order to emulate, at lab scale, the flight conditions responsible for debonding the stiffeners from the skin. The displacement field was determined by Digital Image Correlation (DIC) and the strains values at key zone of the fuselage by gages measurements. Finally, the failure mechanisms were analyzed with the goal to improve the knowledge of the stiffened-skin glued joint solution.

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Numerical and experimental value added of Multi-Instrumented Technological Evaluator for the analysis of thick monolithic composite structures with singularity details

Cited by 9 publications

References 21 publications

Multi-instrumentation monitoring for the curing process of a composite structure

Multi-instrumentation monitoring for the curing process of a composite structure

Manufacturing Process of High Performance–Low Cost Composite Structures for Light Sport Aircrafts

Mechanical Behavior of a Fuselage Stiffened Carbon-Epoxy Panel under Debonding Load

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