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Journal articles on the topic 'Composite Aerospace Structures'

Author: Grafiati

Published: 4 June 2021

Last updated: 2 February 2022

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1

Sellitto, Andrea, Aniello Riccio, A. Russo, Antonio Garofano, and Mauro Zarrelli. "Nanofillers’ Effects on Fracture Energy in Composite Aerospace Structures." Key Engineering Materials 827 (December 2019): 43–48. http://dx.doi.org/10.4028/www.scientific.net/kem.827.43.

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Composite materials damage behaviour is, nowadays, extensively investigated in the frame of aerospace research programmes. Among the several failure mechanisms which can affect composites, delamination can be considered as the most critical one, especially when combined to compressive loading conditions. In this context, nanofillers can represent an effective way to increase the composites fracture toughness with a consequent reduction of the delamination onset and evolution. Hence, in this paper, the toughening effect of the nanofillers on the delamination growth in composite material panels, subject to compressive load, has been numerically studied. A validated robust numerical procedure for the prediction of the delamination growth in composite materials panel, named SMXB and based on the VCCT-Fail release approach, has been used to perform numerical analyses by considering two different types of nanofillers. Reference material, without nanofillers insertion, has been used as benchmark in order to assess the capability of nanofillers to enhance the fracture toughness in composite laminates.

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2

Jadhav, Prakash. "Passive Morphing in Aerospace Composite Structures." Key Engineering Materials 889 (June 16, 2021): 53–58. http://dx.doi.org/10.4028/www.scientific.net/kem.889.53.

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Attempts to add the advanced technologies to aerospace composite structures like fan blade have been on in recent times to further improve its performance. As part of these efforts, it has been proposed that the blade morph feasibility could be studied by building and optimizing asymmetric lay up of composite plies inside the blade which will help generate enough passive morphing between max cruise and climb conditions of the flight. This will have a direct efficiency (Specific Fuel Consumption) benefit. This research describes the various ideas that were tried using in house-developed lay-up optimization code and Ansys commercial software to study the possibility of generating enough passive morphing in the blade. In the end, this report concludes that the required degree of passive morphing could not be generated using various ideas with passive morphing technology and only up to some extent of morphing is shown to be feasible using the technologies used here.

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3

van Tooren, M., C. Kasapoglou, and H. Bersee. "Composite materials, composite structures, composite systems." Aeronautical Journal 115, no. 1174 (December 2011): 779–87. http://dx.doi.org/10.1017/s0001924000006527.

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Abstract The first part of the history of composites in aerospace emphasised materials with high specific strength and stiffness. This was followed by a quest for reliable manufacturing techniques that guaranteed sufficiently high fibre volume fractions in complex structural parts with reasonable cost. Further improvements are still possible leading, ultimately to an extension of the functionality of composite structures to non-mechanical functions. Reduction of material scatter and a more probability-based design approach, improved material properties, higher post buckling factors, improved crashworthiness concepts and improved NDI techniques are some of the evolutionary measures that could improve the performance of current composite structures. Modular design, increased co-curing, hybrid material structures, hybrid fabrication methods, innovative structural concepts and reduced development times are more revolutionary steps that could bring today’s solutions further. Manufacturing engineering is also important for achieving revolutionary change. Function integration such as embedded deicing, morphing,, and boundary-layer suction are among the next steps in weight and cost reduction, but now on the system level.

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4

Lee, In. "OS17-1-1 Application of Smart and Composite Materials to Aerospace Structures." Abstracts of ATEM : International Conference on Advanced Technology in Experimental Mechanics : Asian Conference on Experimental Mechanics 2007.6 (2007): _OS17–1–1——_OS17–1–1—. http://dx.doi.org/10.1299/jsmeatem.2007.6._os17-1-1-.

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5

Brischetto, Salvatore. "Analysis of natural fibre composites for aerospace structures." Aircraft Engineering and Aerospace Technology 90, no. 9 (November 14, 2018): 1372–84. http://dx.doi.org/10.1108/aeat-06-2017-0152.

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Purpose The main idea is the comparison between composites including natural fibres (such as the linoleum fibres) and typical composites including carbon fibres or glass fibres. The comparison is proposed for different structures (plates, cylinders, cylindrical and spherical shells), lamination sequences (cross-ply laminates and sandwiches with composite skins) and thickness ratios. The purpose of this paper is to understand if linoleum fibres could be useful for some specific aerospace applications. Design/methodology/approach A general exact three-dimensional shell model is used for the static analysis of the proposed structures to obtain displacements and stresses through the thickness. The shell model is based on a layer-wise approach and the differential equations of equilibrium are solved by means of the exponential matrix method. Findings In qualitative terms, composites including linoleum fibres have a mechanical behaviour similar to composites including glass or carbon fibres. In terms of stress and displacement values, composites including linoleum fibres can be used in aerospace applications with limited loads. They are comparable with composites including glass fibres. In general, they are not competitive with respect to composites including carbon fibres. Such conclusions have been verified for different structure geometries, lamination sequences and thickness ratios. Originality/value The proposed general exact 3D shell model allows the analysis of different geometries (plates and shells), materials and laminations in a unified manner using the differential equilibrium equations written in general orthogonal curvilinear coordinates. These equations written for spherical shells degenerate in those for cylinders, cylindrical shell panels and plates by means of opportune considerations about the radii of curvature. The proposed shell model allows an exhaustive comparison between different laminated and sandwich composite structures considering the typical zigzag form of displacements and the correct imposition of compatibility conditions for displacements and equilibrium conditions for transverse stresses.

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6

Wang, K., D. Kelly, and S. Dutton. "Multi-objective optimisation of composite aerospace structures." Composite Structures 57, no. 1-4 (July 2002): 141–48. http://dx.doi.org/10.1016/s0263-8223(02)00078-8.

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7

Fasel, Urban, Dominic Keidel, Leo Baumann, Giovanni Cavolina, Martin Eichenhofer, and Paolo Ermanni. "Composite additive manufacturing of morphing aerospace structures." Manufacturing Letters 23 (January 2020): 85–88. http://dx.doi.org/10.1016/j.mfglet.2019.12.004.

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8

De Simone, Mario Emanuele, Francesco Ciampa, Salvatore Boccardi, and Michele Meo. "Impact source localisation in aerospace composite structures." Smart Materials and Structures 26, no. 12 (November 13, 2017): 125026. http://dx.doi.org/10.1088/1361-665x/aa973e.

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9

ISHIKAWA, Takashi, Yoichi HAYASHI, Masamichi MATSUSHIMA, and Sunao SUGIMOTO. "Visualization of Damage in Aerospace Composite Structures." Journal of the Visualization Society of Japan 12, no. 47 (1992): 231–38. http://dx.doi.org/10.3154/jvs.12.47_231.

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10

Lee, In, Jin-Ho Roh, and Il-Kwon Oh. "AEROTHERMOELASTIC PHENOMENA OF AEROSPACE AND COMPOSITE STRUCTURES." Journal of Thermal Stresses 26, no. 6 (June 2003): 525–46. http://dx.doi.org/10.1080/713855957.

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11

Davies, G. A. O., and J. Ankersen. "Virtual testing of realistic aerospace composite structures." Journal of Materials Science 43, no. 20 (October 2008): 6586–92. http://dx.doi.org/10.1007/s10853-008-2695-x.

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12

Jadhav, Prakash. "Effect of Ply Drop in Aerospace Composite Structures." Key Engineering Materials 847 (June 2020): 46–51. http://dx.doi.org/10.4028/www.scientific.net/kem.847.46.

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In most of the aerospace laminated composite structures, thickness variation is achieved by introducing the ply drops at the appropriate locations. Ply drop means the resin rich regions created due to abrupt ending of individual plies within the set of plies. This research is focused on understanding and quantifying the effect of these ply drop regions on the mechanical performance of the aerospace composite structures. This is achieved here by designing the appropriate coupons (with and without ply drops) and analyzing them using finite element analysis. Some typical designs of coupons were manufactured using aerospace grade carbon composite materials, and then tested under four-point bend, cantilever and short beam shear tests to check and validate the effect that was seen in the analysis. It is concluded here that allowable failure strains are different for with and without ply drop cases by a significant amount.

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13

Azarov, A. V. "The Problem of Designing Aerospace Mesh Composite Structures." Mechanics of Solids 53, no. 4 (July 2018): 427–34. http://dx.doi.org/10.3103/s0025654418040088.

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14

Azarov, A. "The problem of designing aerospace mesh composite structures." Известия Российской академии наук. Механика твердого тела, no. 4 (August 2018): 85–93. http://dx.doi.org/10.31857/s057232990000700-0.

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15

Dell'Anno, Giuseppe, Ivana Partridge, Denis Cartié, Alexandre Hamlyn, Edmon Chehura, Stephen James, and Ralph Tatam. "Automated manufacture of 3D reinforced aerospace composite structures." International Journal of Structural Integrity 3, no. 1 (March 2, 2012): 22–40. http://dx.doi.org/10.1108/17579861211209975.

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16

Vasiliev, V. V., V. A. Barynin, and A. F. Razin. "Anisogrid composite lattice structures – Development and aerospace applications." Composite Structures 94, no. 3 (February 2012): 1117–27. http://dx.doi.org/10.1016/j.compstruct.2011.10.023.

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17

Sorrentino, Assunta, Fulvio Romano, and Angelo De Fenza. "Advanced debonding detection technique for aerospace composite structures." Aircraft Engineering and Aerospace Technology 93, no. 6 (July 19, 2021): 1011–17. http://dx.doi.org/10.1108/aeat-10-2020-0222.

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Purpose The purpose of this paper is to introduce a methodology aimed to detect debonding induced by low impacts energies in typical aeronautical structures. The methodology is based on high frequency sensors/actuators system simulation and the application of elliptical triangulation (ET) and probability ellipse (PE) methods as damage detector. Numerical and experimental results on small-scale stiffened panels made of carbon fiber-reinforced plastic material are discussed. Design/methodology/approach The damage detection methodology is based on high frequency sensors/actuators piezoceramics system enabling the ET and the PE methods. The approach is based on ultrasonic guided waves propagation measurement and simulation within the structure and perturbations induced by debonding or impact damage that affect the signal characteristics. Findings The work is focused on debonding detection via test and simulations and calculation of damage indexes (DIs). The ET and PE methodologies have demonstrated the link between the DIs and debonding enabling the identification of position and growth of the damage. Originality/value The debonding between two structural elements caused in manufacturing or in-service is very difficult to detect, especially when the components are in low accessibility areas. This criticality, together with the uncertainty of long-term adhesive performance and the inability to continuously assess the debonding condition, induces the aircrafts’ manufacturers to pursuit ultraconservative design approach, with in turn an increment in final weight of these parts. The aim of this research’s activity is to demonstrate the effectiveness of the proposed methodology and the robustness of the structural health monitoring system to detect debonding in a typical aeronautical structural joint.

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18

Baur, Jeff, and Edward Silverman. "Challenges and Opportunities in Multifunctional Nanocomposite Structures for Aerospace Applications." MRS Bulletin 32, no. 4 (April 2007): 328–34. http://dx.doi.org/10.1557/mrs2007.231.

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AbstractOne important application of nanocomposites is their use in engineered structural composites. Among the wide variety of structural applications, fiber-reinforced composites for aerospace structures have some of the most demanding physical, chemical, electrical, thermal, and mechanical property requirements. Nanocomposites offer tremendous po tential to improve the properties of advanced engineered composites with modest additional weight and easy integration into current proc essing schemes. Sig nificant progress has been made in fulfilling this vision. In particular, nanocomposites have been applied at numerous locations within hierarchical composites to improve specific properties and optimize the multifunctional properties of the overall structure. Within this ar ticle, we review the status of nanocomposite incorporation into aerospace composite structures and the need for continued development.

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19

Davies, G. A. O., and R. Olsson. "Impact on composite structures." Aeronautical Journal 108, no. 1089 (November 2004): 541–63. http://dx.doi.org/10.1017/s0001924000000385.

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The problem of impact damage in laminated composite structures, and the consequent reduction in residual strength, has been a topic of continual research for over two decades. The number of journal papers on the subject now runs into four figures and most have been conscientiously reviewed by Abrate(1991, 1994, 1998). This review is not intended to be in the academic tradition, with emphasis on acknowledging the authorship of all the various research initiatives. Instead we present our opinions so that the reader can appreciate our current understanding of the problem, our capability of predicting by analysis, and the scope of the design tools for avoiding structural damage, or at least designing damage tolerant aerospace structures.

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20

ORIFICI, ADRIAN C., RODNEY S. THOMSON, RICHARD DEGENHARDT, CHIARA BISAGNI, and JAVID BAYANDOR. "AN ANALYSIS TOOL FOR DESIGN AND CERTIFICATION OF POSTBUCKLING COMPOSITE AEROSPACE STRUCTURES." International Journal of Structural Stability and Dynamics 10, no. 04 (October 2010): 669–81. http://dx.doi.org/10.1142/s0219455410003671.

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In aerospace, carbon-fiber-reinforced polymer (CFRP) composites and postbuckling skin-stiffened structures are key technologies that have been used to improve structural efficiency. However, the application of composite postbuckling structures in aircraft has been limited due to concerns related to both the durability of composite structures and the accuracy of design tools. In this work, a finite element analysis tool for design and certification of aerospace structures is presented, which predicts collapse by taking the critical damage mechanisms into account. The tool incorporates a global–local analysis technique for predicting interlaminar damage initiation, and degradation models to capture the growth of a pre-existing interlaminar damage region, such as a delamination or skin–stiffener debond, and in-plane ply damage mechanisms such as fiber fracture and matrix cracking. The analysis tool has been applied to single- and multistiffener fuselage-representative composite panels, in both intact and predamaged configurations. This has been performed in a design context, in which panel configurations are selected based on their suitability for experimental testing, and in an analysis context for comparison with experimental results as being representative of aircraft certification studies. For all cases, the tool was capable of accurately capturing the key damage mechanisms contributing to final structural collapse, and suitable for the design of next-generation composite aerospace structures.

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21

Demay, Agathe, Johnathan Hernandez, Perla Latorre, Remelisa Esteves, and Seetha Raghavan. "Functional Coatings for Damage Detection in Aerospace Structures." Technology & Innovation 22, no. 1 (June 28, 2021): 95–103. http://dx.doi.org/10.21300/21.4.2021.10.

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The future of aerospace structures is highly dependent on the advancement of reliable and high-performance materials, such as composite materials and metals. Innovation in high resolution non-invasive evaluation of these materials is needed for their qualification and monitoring for structural integrity. Aluminum oxide (or α-alumina) nanoparticles present photoluminescent properties that allow stress and damage sensing via photoluminescence piezospectroscopy. This work describes how these nanoparticles are added into a polymer matrix to create functional coatings that monitor the damage of the underlying composite or metallic substrates. Different volume fractions of α-alumina nanoparticles in the piezospectroscopic coatings were studied for determining the sensitivity of the coatings and successful damage detection was demonstrated for an open-hole tension composite substrate as well as 2024 aluminum tensile substrates with a subsurface notch.

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22

Mouritz, Adrian P., Fabio Pegorin, Mohd Dali Isa, and Khomkrit Pingkarawat. "Fatigue Properties of Aerospace Z-Pinned Composites." Applied Mechanics and Materials 828 (March 2016): 67–75. http://dx.doi.org/10.4028/www.scientific.net/amm.828.67.

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This paper presents an experimental study into the effect of through-thickness z-pin reinforcement on the in-plane and out-of-plane (delamination) fatigue properties of carbon-epoxy composites used in aerospace structures. The in-plane fatigue strength and fatigue life (load cycles-to-failure) of aerospace composite materials are reduced by z-pins. The in-plane compressive fatigue properties decrease when the volume content of z-pins is increased. Reductions to the in-plane fatigue properties are due to microstructural damage caused by the z-pins. However, the out-of-plane (delamination) fatigue properties of composites are increased greatly by z-pins. The mode I, mode II and mixed mode I/II delamination fatigue properties increase rapidly with increasing volume content of z-pins. The improvement is due to the z-pins forming a large-scale bridging zone along the delamination which resists fatigue crack growth. The work clearly reveals that a trade-off exists between the in-plane and out-of-plane fatigue properties of z-pinned composites. Improvements to the delamination fatigue properties come at the expense of lower in-plane fatigue performance, and this is a key consideration for the design of z-pinned aerospace composite structures.

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23

Al-Madani, Ramadan A., M. Jarnaz, K. Alkharmaji, and M. Essuri. "Finite Element Modeling of Composites System in Aerospace Application." Applied Mechanics and Materials 245 (December 2012): 316–22. http://dx.doi.org/10.4028/www.scientific.net/amm.245.316.

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The characteristics of composite materials are of high importance to engineering applications; therefore the increasing use as a substitute for conventional materials, especially in the field of aircraft and space industries. It is a known fact that researchers use finite element programs for the design and analysis of composite structures, use of symmetrical conditions especially in complicated structures, in the modeling and analysis phase of the design, to reduce processing time, memory size required, and simplifying complicated calculations, as well as considering the response of composite structures to different loading conditions to be identical to that of metallic structures. Finite element methods are a popular method used to analyze composite laminate structures. The design of laminated composite structures includes phases that do not exist in the design of traditional metallic structures, for instance, the choice of possible material combinations is huge and the mechanical properties of a composite structure, which are anisotropic by nature, are created in the design phase with the choice of the appropriate fiber orientations and stacking sequence. The use of finite element programs (conventional analysis usually applied in the case of orthotropic materials) to analysis composite structures especially those manufactured using angle ply laminate techniques or a combination of cross and angle ply techniques, as well considering the loading response of the composite structure to be identical to that of structures made of traditional materials, has made the use of, and the results obtained by using such analysis techniques and conditions questionable. Hence, the main objective of this paper is to highlight and present the results obtained when analyzing and modeling symmetrical conditions as applied to commercial materials and that applied to composite laminates. A comparison case study is carried out using cross-ply and angle-ply laminates which concluded that, if the composition of laminate structure is pure cross-ply, the FEA is well suited for predicting the mechanical response of composite structure using principle of symmetry condition. On the other hand that is not the case for angle-ply or mixed-ply laminate structure.

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24

Yuan, Zheng, Robert Crouch, Jeff Wollschlager, and Jacob Fish. "Assessment of multiscale designer for fatigue life prediction of advanced composite aircraft structures." Journal of Composite Materials 51, no. 15 (August 17, 2016): 2131–41. http://dx.doi.org/10.1177/0021998316665163.

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Multiscale Designer, developed by Altair, has been studied for its suitability for fatigue life prediction of advanced composite aircraft structures made of polymer matrix composites. The extensive experimental data provided by the Air Force Research Laboratory have been utilized to characterize the linear, non-linear, monotonic, and cyclic loading properties of micro-constituents comprising the polymer matrix composite system. The characterized properties have been then utilized to predict fatigue life and residual strength and stiffness of the aerospace grade polymer matrix composites.

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25

Eastep, F. E., V. A. Tischler, V. B. Venkayya, and N. S. Khot. "Aeroelastic Tailoring of Composite Structures." Journal of Aircraft 36, no. 6 (November 1999): 1041–47. http://dx.doi.org/10.2514/2.2546.

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26

Qiu, Jinhao, Jun Cheng, Chao Zhang, Hongli Ji, Toshiyuki Takagi, and Tetsuya Uchimoto. "Novel NDT methods for composite materials in aerospace structures." International Journal of Applied Electromagnetics and Mechanics 52, no. 1-2 (December 29, 2016): 25–33. http://dx.doi.org/10.3233/jae-162203.

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27

Thomas, Daniel J. "Complexity of Understanding the Failure of Aerospace Composite Structures." Journal of Failure Analysis and Prevention 16, no. 4 (July 8, 2016): 513–14. http://dx.doi.org/10.1007/s11668-016-0141-y.

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28

Davies, G. A. O., D. Hitchings, and J. Ankersen. "Predicting delamination and debonding in modern aerospace composite structures." Composites Science and Technology 66, no. 6 (May 2006): 846–54. http://dx.doi.org/10.1016/j.compscitech.2004.12.043.

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29

Kostopoulos, Vassilis, Athanasios Masouras, Athanasios Baltopoulos, Antonios Vavouliotis, George Sotiriadis, and Laurent Pambaguian. "A critical review of nanotechnologies for composite aerospace structures." CEAS Space Journal 9, no. 1 (July 8, 2016): 35–57. http://dx.doi.org/10.1007/s12567-016-0123-7.

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30

Ball, M. J. "The Challenge and Potential of Metal Matrix Composites." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 203, no. 1 (January 1989): 47–52. http://dx.doi.org/10.1243/pime_proc_1989_203_053_01.

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Metal matrix composites offer considerable potential for significant weight savings in aerospace structures. This paper reviews the types of metal matrix composite, particularly with respect to properties and potential applications.

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31

Khosravani, Mohammad Reza. "Composite Materials Manufacturing Processes." Applied Mechanics and Materials 110-116 (October 2011): 1361–67. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.1361.

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— Using Composite materials are growing more and more today and we have to use them in possible situation. One of the Composite materials applications is on the Airplane and aero space. Reduction of Airplane weight and more adaptability with nature are examples of benefit of using composite materials in aerospace industries. In this article process of manufacturing of composite materials and specially carbon fiber composite are explained. Advance composite materials are common today and are characterized by the use of expensive, high-performance resin systems and high-strength, high-stiffness fiber reinforcement. The aerospace industry, including military and commercial aircraft of all types, is the major customer for advanced composites. Product range now includes materials for low pressure and low temperature. Some using composite materials in aero space are as follow: Satellite Components, Thin Walled Tubing for Aircraft and Satellites, launch vehicle components and honeycomb structures.

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32

Ibrahim, Matthew E., Andrew W. Phillips, Robert J. Ditchburn, and Chun H. Wang. "Nondestructive Evaluation of Mechanically Loaded Advanced Marine Composite Structures." Advanced Materials Research 891-892 (March 2014): 594–99. http://dx.doi.org/10.4028/www.scientific.net/amr.891-892.594.

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Marine composite structures subject to dynamic loading typically incorporate more than one material type, and consist of laminate sections up to hundreds of millimetres in thickness. These solid hybrid laminates exhibit different behaviour in static and fatigue loading from thin aerospace composite laminates and sandwich structures. There is therefore a need to better understand the likely damage and degradation mechanisms that will occur in these thick structures and to concurrently develop nondestructive evaluation (NDE) technology to meet the consequent inspection problems. In this paper we present details of an ongoing fatigue program on marine composite blades. The challenges for ultrasonic NDE of thick composites, and emerging inspection methods using state-of-the-art inspection systems and analysis tools will be discussed.

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Naseer, Zainab, and Zaffar Khan. "Graphene Effect on Mechanical Properties of Sandwich Panel for Aerospace Structures." Key Engineering Materials 875 (February 2021): 121–26. http://dx.doi.org/10.4028/www.scientific.net/kem.875.121.

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This research examines the mechanical properties of graphene-based polymer composites and Nomex honeycomb sandwich using a new strain sensing technique. Sandwich panels are fabricated individually with glass fibre reinforced polymers (GFRP) and face-sheets having different filler ratios of graphene nanoparticles (GNPs). These graphene nanoparticles are oxidized with (UV-O3) ozone to get graphene oxide (GO) which in turn improves resin matrix interfacial strength. Filler ratios of GO 0.0%, 0.2%, 0.6% and 1.0% by weight of poly-epoxy are fabricated for the face-sheets of composite sandwich panels. Graphene-based strain sensors are synthesized having a concentration of GNPs 5% by weight of polystyrene (PS). The strain sensors are pasted on the sandwich panels and four-point bending of the sandwich beams is performed to predict its flexural strength. The response of composite under different filler ratios of graphene oxide on mechanical properties is inspected during mechanical testing of sandwich panels and the results of (PS-GNPs) strain sensors will be compared with the strains produced during mechanical testing.

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34

Romano, Maria Grazia, Michele Guida, Francesco Marulo, Michela Giugliano Auricchio, and Salvatore Russo. "Characterization of Adhesives Bonding in Aircraft Structures." Materials 13, no. 21 (October 28, 2020): 4816. http://dx.doi.org/10.3390/ma13214816.

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Structural adhesives play an important role in aerospace manufacturing, since they provide fewer points of stress concentration compared to faster joints. The importance of adhesives in aerospace is increasing significantly because composites are being adopted to reduce weight and manufacturing costs. Furthermore, adhesive joints are also studied to determine the crashworthiness of airframe structure, where the main task for the adhesive is not to dissipate the impact energy, but to keep joint integrity so that the impact energy can be consumed by plastic work. Starting from an extensive campaign of experimental tests, a finite element model and a methodology are implemented to develop an accurate adhesive model in a single lap shear configuration. A single lap joint finite element model is built by MSC Apex, defining two specimens of composite material connected to each other by means of an adhesive; by the Digimat multi-scale modeling solution, the composite material is treated; and finally, by MSC’s Marc, the adhesive material is characterized as a cohesive applying the Cohesive Zone Modeling theory. The objective was to determine an appropriate methodology to predict interlaminar crack growth in composite laminates, defining the mixed mode traction separation law variability in function of the cohesive energy (Gc), the ratio between the shear strength τ and the tensile strength σ (β1), and the critical opening displacement υc.

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35

Mahmood Baitab, Danish, Dayang Laila Abang Haji Abdul Majid, Ermira Junita Abdullah, and Mohd Faisal Abdul Hamid. "A review of techniques for embedding shape memory alloy (SMA) wires in smart woven composites." International Journal of Engineering & Technology 7, no. 4.13 (October 9, 2018): 129. http://dx.doi.org/10.14419/ijet.v7i4.13.21344.

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Metallic structures, in various industrial fields such as transport and aerospace, are mostly replaced by composite structures having less weight and good strength. There is also a need of intensification of the operational dynamic environment with high durability requirements. So a smart composite structure is required that can manifest its functions according to environmental changes. One method of producing smart composite structures is to embed shape memory alloys in composite structures. Shape memory alloys (SMAs) have significant mechanical and thermodynamic properties and are available in very small diameters less than 0.2mm. These SMAs are embedded into composites for obtaining smart composites having tunable properties, active abilities, damping capacity and self-healing properties. Shape memory alloys are available in different shapes as wires, sheets, foils, strips, etc. For smart composites, mostly SMA embedded are in wire shape. Different techniques are used for embedding SMA wires in composites. SMA wires can be embedded between layers of laminates of composites, or embedded directly as reinforcement in matrix and can be woven into fabrics and used as a reinforcement. This paper reviews the different techniques of embedding SMA wires in composite structures, their pros and cons and their applications.

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Barry, Fetzer. "Automated Robotic Systems for Nondestructive Testing of Aerospace Composite Structures." Materials Evaluation 79, no. 7 (July 1, 2021): 678–86. http://dx.doi.org/10.32548/2021.me-04224.

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Automated robotic systems are becoming prevalent in many aerospace manufacturing applications, such as laser ablation, sanding, drilling, final assembly, and painting. There are significant advantages to using automated robotic systems for inspection purposes as well: versatility, speed, and repeatability, to name a few. This paper explores using an automated robotic system for the nondestructive testing (NDT) of composite parts. It has a focus on phased array ultrasonic testing (PAUT) but highlights modularity principles in the system that are not coupled to a single inspection method. Because of the articulation inherent in multi-axis robots, inspections of contoured structures become straightforward if the system modules are designed correctly. Examples of such modules, and their advantages when interfaced to an automated robotic system, are included in this paper. It is the author’s intent to show how these system modules might maximize robot capabilities for a broad range of aerospace inspections while keeping a simplistic design that is modular, fast, and straightforward to use. When compared to other aerospace manufacturing processes already using automated robotic systems, the use of robots for NDT seems not only prudent but a favorable goal. This paper offers practical building blocks for achieving this goal.

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Fortier, Vincent, Jean-E. Brunel, and Louis L Lebel. "Fastening composite structures using braided thermoplastic composite rivets." Journal of Composite Materials 54, no. 6 (August 14, 2019): 801–12. http://dx.doi.org/10.1177/0021998319867375.

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Aerospace composite material components are currently joined using heavy titanium bolts. This joining method is not ideal when considering its weight, thermal expansion, electrical conductivity, and risk of unbalanced load distribution. We propose here an innovative fastening technology using thermoplastic composite rivets. A rivet blank is heated above its melting temperature using Joule heating and is formed directly in the composite laminates by an automated process. Carbon fiber and polyamide blanks were used with two fiber architecture: 2D braid and unidirectional. The braided architecture showed superior manufacturing performance and repeatability. Joints were riveted in less than 40 s per rivet. The temperature measured in the riveted composite laminate in the vicinity of formed rivet reached only 136℃ during riveting. Double fastener lap shear testing showed breaking load of 6146 N per fastener. This joint strength is higher than comparable aluminum-riveted joints, and the specific joint strength is higher than titanium-bolted joints. With these advantages, the technology could be developed and used in the next generations of lighter, cleaner, and safer aircraft.

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Birman, Victor. "Thermomechanical Wrinkling in Composite Sandwich Structures." AIAA Journal 42, no. 7 (July 2004): 1474–79. http://dx.doi.org/10.2514/1.5913.

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Reddy, J. N. "Book Review Mechanics of Composite Structures." AIAA Journal 32, no. 5 (May 1994): 1107. http://dx.doi.org/10.2514/3.48290.

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Horton, B., Y. Song, D. Jegley, F. Collier, and J. Bayandor. "Predictive analysis of stitched aerospace structures for advanced aircraft." Aeronautical Journal 124, no. 1271 (November 18, 2019): 44–54. http://dx.doi.org/10.1017/aer.2019.137.

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ABSTRACTIn recent years, the aviation industry has taken a leading role in the integration of composite structures to develop lighter and more fuel efficient aircraft. Among the leading concepts to achieve this goal is the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept. The focus of most PRSEUS studies has been on developing an hybrid wing body structure, with only a few discussing the application of PRSEUS to a tube-wing fuselage structure. Additionally, the majority of investigations for PRSEUS have focused on experimental validation of anticipated benefits rather than developing a methodology to capture the behavior of stitched structure analytically. This paper presents an overview of a numerical methodology capable of accurately describing PRSEUS’ construction and how it may be implemented in a barrel fuselage platform resorting to high-fidelity mesoscale modeling techniques. The methodology benefits from fresh user defined strategies developed in a commercially available finite element analysis environment. It further proposes a new approach for improving the ability to predict deformation in stitched composites, allowing for a better understanding of the intricate behavior and subtleties of stitched aerospace structures.

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Jadhav, Prakash. "Innovative designs of embedded foam inserts in aerospace composite structures." Materials Today: Proceedings 21 (2020): 1164–68. http://dx.doi.org/10.1016/j.matpr.2020.01.066.

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Mansuri, Heena, and Gopalsamy Murugesan. "Experimental Study of Composite Foam Sandwich Structures for Aerospace Applications." International Journal of Mechanical Engineering 5, no. 3 (March 25, 2018): 17–19. http://dx.doi.org/10.14445/23488360/ijme-v5i3p104.

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Ponzi, C. "Metal matrix composite fabrication processes for high performance aerospace structures." Composites Manufacturing 3, no. 1 (January 1992): 32–42. http://dx.doi.org/10.1016/0956-7143(92)90181-s.

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Al-Dhaheri, M., K. A. Khan, R. Umer, F. van Liempt, and W. J. Cantwell. "Process-induced deformation in U-shaped honeycomb aerospace composite structures." Composite Structures 248 (September 2020): 112503. http://dx.doi.org/10.1016/j.compstruct.2020.112503.

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Staszewski, W. J., S. Mahzan, and R. Traynor. "Health monitoring of aerospace composite structures – Active and passive approach." Composites Science and Technology 69, no. 11-12 (September 2009): 1678–85. http://dx.doi.org/10.1016/j.compscitech.2008.09.034.

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Minakuchi, Shu, and Nobuo Takeda. "Recent advancement in optical fiber sensing for aerospace composite structures." Photonic Sensors 3, no. 4 (October 8, 2013): 345–54. http://dx.doi.org/10.1007/s13320-013-0133-4.

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Totaro, G., and Z. Gürdal. "Optimal design of composite lattice shell structures for aerospace applications." Aerospace Science and Technology 13, no. 4-5 (June 2009): 157–64. http://dx.doi.org/10.1016/j.ast.2008.09.001.

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Chronopoulos, D., M. Ichchou, B. Troclet, and O. Bareille. "Thermal effects on the sound transmission through aerospace composite structures." Aerospace Science and Technology 30, no. 1 (October 2013): 192–99. http://dx.doi.org/10.1016/j.ast.2013.08.003.

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RUSU, Bogdan, Simona BLINDU BLINDU, Andra MICU, and Valentin SOARE. "Guidelines for Aircraft Composite Panels." INCAS BULLETIN 12, no. 1 (March 1, 2020): 217–28. http://dx.doi.org/10.13111/2066-8201.2020.12.1.21.

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The objective of this paper is to give a general perspective and present some elementary steps for manufacturing aircraft sandwich panel composites. Composite materials have been widely used in high performance sectors of the aerospace and automotive industry, and there is considerable knowledge and confidence in their static, dynamic and crashworthiness properties. Sandwich composites are becoming more and more used in airframe structural design, mainly for their ability to substantially reduce weight while maintaining their high mechanical properties. The steps for manufacturing a sandwich composite that meets all the requirements for exploitation are very precise and rigorous, involving specific design requirements, specific materials selection and specific manufacturing conditions starting with the lay-up procedure and up to the curing process inside an autoclave. After the curing process, destructive and nondestructive tests and experiments are performed on the composite structures in order to validate the products. At the same time, this paper presents a short briefing about the implication of 3D printing technologies with high temperature resistance resins for sandwich cores used in aerospace applications.

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Dragan, Krzysztof, Michał Dziendzikowski, Artur Kurnyta, Michal Salacinski, Sylwester Klysz, and Andrzej Leski. "Composite Aerospace Structure Monitoring with use of Integrated Sensors." Fatigue of Aircraft Structures 2015, no. 7 (December 1, 2015): 12–17. http://dx.doi.org/10.1515/fas-2015-0002.

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Abstract One major challenge confronting the aerospace industry today is to develop a reliable and universal Structural Health Monitoring (SHM) system allowing for direct aircraft inspections and maintenance costs reduction. SHM based on guided Lamb waves is an approach capable of addressing this issue and satisfying all the associated requirements. This paper presents an approach to monitoring damage growth in composite aerospace structures and early damage detection. The main component of the system is a piezoelectric transducers (PZT) network integrated with composites. This work describes sensors’ integration with the structure. In particular, some issues concerning the mathematical algorithms giving information about damage from the impact damage presence and its growth are discussed.

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