Relevant bibliographies by topics / Composite Aerospace Structures

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Composite Aerospace Structures'

Author: Grafiati
Published: 4 June 2021
Last updated: 2 February 2022

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Journal articles on the topic "Composite Aerospace Structures"

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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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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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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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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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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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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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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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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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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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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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Dissertations / Theses on the topic "Composite Aerospace Structures"

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Spendley, Paul R. "Design allowables for composite aerospace structures." Thesis, University of Surrey, 2012. http://epubs.surrey.ac.uk/810072/.

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Recent developments in aircraft design have seen the Airbus A380 and the Boeing Dreamliner employ significant amounts of advanced composite materials. There is some thought however, und the motivation for this current work, that these materials continue to suffer a weight penalty. In this work tests required to generate design allowables which accommodate environmental effects and holes arc performed on Carbon/epoxy quasi-isotropic laminatcs. The test data is treated statistically to provide B-basis allowables for each specimen type and condition. It was seen that the notched specimens (coupons containing a centrally placed through hole) displayed significantly less scatter in strength than unnotched specimens. This is significant when considering the widespread use of deterministic knock-down factors as an alternative route to obtain design allowables which accommodate environmental effects and/or holes. This results in an over-conservative design allowable being employed in subsequent structural design calculations. The possibility for using notched coupons to determine design allowables was explored using the COG (Critical Damage Growth) model. This showed that. given two of the three parameters. the unnotched and notched strength, and fracture toughness the variation in strengths could be reasonable predicted. This leads to a more representative design allowable by maintaining the statistical nature of the B-basis allowable. During the statistical treatment of the test data it was also seen that although current aerospace guidelines recommend a particular distribution model (i.e. the Wcibull distribution) this can also leads to an artificially reduced design allowable. These findings suggest that the use of notched specimens can lead to a reduced development test programme and reduced structural weight.
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White, Caleb, and caleb white@rmit edu au. "Health Monitoring of Bonded Composite Aerospace Structures." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2009. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20090602.142122.

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Airframe assemblers have long recognised that for a new aircraft to be successful it must use less fuel, have lower maintenance requirements, and be more affordable. One common tactic is the use of innovative materials, such as advanced composites. Composite materials are suited to structural connection by adhesive bonding, which minimises the need for inefficient mechanical fastening. The aim of this PhD project was to investigate the application of existing, yet immature Structural Health Monitoring (SHM) techniques to adhesively bonded composite aerospace structures. The PhD study focused on two emerging SHM technologies - frequency response and comparative vacuum monitoring (CVM). This project aimed to provide missing critical information for each technique. This included determining sensitivity to damage, repeatability of results, and operating limitations for the frequency response method. Study of the CVM technique aimed to address effectiveness of damage detection, manufacture of sensor cavities, and the influence of sensor integration on mechanical performance of bonded structures. Experimental research work is presented examining the potential of frequency response techniques for the detection of debonding in composite-to-composite external patch repairs. Natural frequencies were found to decrease over a discrete frequency range as the debond size increased; confirming that such features could be used to both detect and characterise damage. The effectiveness of the frequency response technique was then confirmed for composite patch and scarf repair specimens for free-free and fixed-fixed boundary conditions. Finally, the viability of the frequency response technique was assessed for a scarf repair of a real aircraft component, where it was found that structural damping limited the maximum useable frequency. The feasibility of CVM technique for the inspection of co-cured stiffener-skin aircraft structures was explored. The creation of sensor cavities with tapered mandrels was found to significantly alter the microstructure of the stiffener, including crimping and waviness of fibres and resin-rich zones between plies. Representative stiffened-skin structure with two sensor cavity configurations (parallel and perpendicular to the stiffener direction) was tested to failure in tension and compression. While tensile failure strength was significantly reduced for both configurations (up to 25%), no appreciable differences in compression properties were found. Two potential sensor cavity configurations were investigated for the extension of the CVM technique to pre-cured and co-bonded scarf repair schemes. The creation of radial and circumferential CVM sensor cavities was found to significantly alter the microstructure of the adhesive bond-line and the architecture of the repair material in the case of the co-bonded repair. These alterations changed the failure mode and reduced the tensile failure strength of the repair. A fibre straightening mechanism responsible for progressive failure (specific to co-bonded repairs with circumferential cavities) was identified, and subsequently supported with acoustic emission testing and numerical analysis. While fatigue performance was generally reduced by the presence of CVM cavities, the circumferential cavities appeared to retard crack progression, reducing sensitivity to the accumulation of fatigue damage. These outcomes have brought forward the implementation of SHM in bonded composite structures, which has great potential to improve the operating efficiency of next generation aircraft.
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Zhang, Haochuan. "Nonlinear aeroelastic effects in damaged composite aerospace structures." Thesis, Georgia Institute of Technology, 1996. http://hdl.handle.net/1853/12150.

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Pozegic, Thomas R. "Nano-modified carbon-epoxy composite structures for aerospace applications." Thesis, University of Surrey, 2016. http://epubs.surrey.ac.uk/809603/.

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Carbon fibre reinforced plastics (CFRP) have revolutionised industries that demand high specific strength materials. With current advancements in nanotechnology there exists an opportunity to not only improve the mechanical performance of CFRP, but to also impart other functionalities, such as thermal and electrical conductivity, with the aim of reducing the reliance on metals, making CFRP attractive to many other industries. This thesis provides a comprehensive analysis of the nano-phase modification to CFRP by growing carbon nanotubes (CNTs) on carbon fibre (CF) and performing mechanical, electrical and thermal conductivity tests, with comparisons made against standard CFRP. Typical CFs are coated with a polymer sizing that plays a vital role in the mechanical performance of the composite, but as a consequence of CNT growth, it is removed. Therefore, in addition, an ‘intermediate’ composite was fabricated – based on CFs without a polymer sizing – which enabled a greater understanding of how the mechanical properties and processability of the material responds to the CNT modification. A water-cooled chemical vapour deposition system was employed for CNT growth and infused into a composite structure with an industrially relevant vacuum-assisted resin transfer moulding (VARTM) process. High quality CNTs were grown on the CF, resulting in properties not reported to date, such as strong intra-tow binding, leading to the possibility of a polymer sizing-free CFRP. A diverse set of spectroscopic, microscopic and thermal measurements were carried out to aid understanding for this CNT modification. Subsequent electrical conductivity tests performed in three directions showed 300%, 230% and 450% improvements in the ‘surface’, ‘through-thickness’ and ‘through-volume’ directions, for the CNT modified CFRP, respectively. In addition, thermal conductivity measurements performed in the through-thickness direction also gave improvements in excess of 98%, boding well for multifunctional applications of this hybrid material concept. A range of mechanical tests were performed to monitor the effect of the CNT modification, including: single fibre tensile tests, tow pull-out tests (from the polymer matrix), composite tensile tests, in-plane shear tests and interlaminar toughness tests. Single fibre tensile tests demonstrated a performance reduction of only 9.7% after subjecting the fibre to the low temperature CNT growth process, which is significantly smaller than previous reports. A reduction in tensile performance was observed in the composite tensile test however, with a reduction of 33% reduction in the ultimate tensile strength, but a 146% increase in the Young’s modulus suggests that the CNTs may have improved the interfacial interactions between the fibre and the polymer matrix. To support this, improvements of 20% in the in-plane shear stress and 74% and the shear chord modulus, were recorded. Negligible differences were observed using a pull-out test to directly measure the interfacial strength as a consequence of the inherently difficult mechanical test procedure. The fracture toughness was tested under mode-I loading of a double cantilever beam configuration and improvements of 83% for CNT modified composite alluded to CNT pull-out fracture mechanism and crack propagation amongst the microstructures. The changes in the physical properties are correlated to the microstructure modifications ensured by the low temperature CNT growth on the CF substrates used in the CFRP composites. This allows for a new generation of modified multifunctional CFRPs to be produced.
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Zhou, Jin. "The energy-absorbing behaviour of novel aerospace composite structures." Thesis, University of Liverpool, 2015. http://livrepository.liverpool.ac.uk/2014139/.

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The aim of this research is to investigate the structural response of PVC foam based sandwich structures, composite reinforced foam cores and fibre metal laminates (FMLs) subjected to quasi-static and dynamic loading conditions. It also includes the investigation of the mechanical properties and energy-absorbing characteristics of the novel hybrid materials and structures for their potential use in aerospace and a wide range of engineering applications. Firstly，a series of experimental tests have been undertaken to obtain the mechanical properties of all constituent materials and structural behavior of the composite structures, which are used to develop and validate numerical models. The material tests carried out include (1) tension properties of composite laminates and aluminium alloys, (2) compression of PVC foams, carbon and glass fibre rods and tubes, and fibre metal laminates in the edge wise and flat wise, (3) shear and bending of PVC foams, (4) Hopkinson Bar, (5) quasi-static and dynamic crushing of composite reinforced foams, and (6) projectile impact on fibre reinforced laminates, aluminium alloy panels, PVC foam based sandwich panels and fibre metal laminates. The corresponding failure modes are obtained to validate the numerical predictions. In addition, perforation energy and specific energy absorptions of various composite structures investigated are evaluated. Moreover, the rate-sensitivity of FMLs based on glass fibre reinforced epoxy and three aluminium alloys has been investigated though a series of quasi-static and impact perforation tests on multilayer configurations ranging from a simple 2/1 lay-up to a 5/4 stacking sequence. FMLs based on a combination of the composite and metal constituents exhibit a low degree of rate-sensitivity, with the impact perforation energy increasing slightly in passing from quasi-static to dynamic rates of loading. Then, finite element (FE) models are developed using the commercial code Abaqus/Explicit to simulate the impact response of PVC foam sandwich structures. The agreement between the numerical predictions and the experimental results is very good across the range of the structures and configurations investigated. The FE models have produced accurate predictions of the impact load-displacement responses, the perforation energies and the failure characteristics recorded. The analyses are used to estimate the energy absorbed by the skins and the core during the perforation process. The validated FE models are also used to investigate the effect of oblique loading and to study the impact response of sandwich panels on an aqueous environment and subjected to a pressure differential (equivalent to flying at an altitude of 10000 m). The modelling has been further undertaken on the low velocity impact response of the sandwich structures based on graded or composite reinforced PVC foam cores, with reasonably good correlation to the corresponding experimental results. Consequently, a series of finite element analyses have been conducted to investigate the influence of varying foam density, rod diameter, rod length and fibre type on the energy-absorbing characteristics of the reinforced foams. Perforation energies, impact resistance performance and unit cost of the structures have been evaluated. Furthermore, the low velocity impact response of fibre metal laminates has been studied numerically. Here, the composite layer in FMLs is modelled using the modified 3D Hashin’s failure criteria, which are implemented into the main programme through a user-defined subroutine, whilst aluminium alloys are modelled using Johnson-Cook plasticity and the corresponding damage criterion. A large number of simulations have been undertaken to cover FMLs with all stacking sequences and alloy types studied, which are compared with the experimental results in terms of the load-displacement trace and failure modes, with very good correlation. Similar modelling work has been carried out on the aluminium layer and composite layer individually. The energy to perforate the various FMLs is plotted and fitted on a single curve that can be used to predict the perforation energies of other configurations. The dynamic characteristics of the composite structures through a series experimental tests and numerical predictions investigated in this project can be used in the design of lightweight composite structures for energy-absorbing applications.
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Orifici, Adrian Cirino, and adrian orifici@student rmit edu au. "Degradation Models for the Collapse Analysis of Composite Aerospace Structures." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2007. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20080619.090039.

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Shengnan, Geng, Wang Xinglai, and Feng Hui. "FIBER BRAGG GRATING SENSOR SYSTEM FOR MONITORING COMPOSITE AEROSPACE STRUCTURES." International Foundation for Telemetering, 2016. http://hdl.handle.net/10150/624242.

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To investigate strain-sensitive characteristics of fiber Bragg grating (FBG) sensors, a minimal sensing system consisting of multiplex FBG sensors and signal demodulating and processing instruments was constructed. FBG sensors were designed with different package structures for respectively sensing strain or temperature parameters, and they returned measurand-dependent wavelengths back to the interrogation system for measurement with high resolution. In this paper, tests were performed on structure samples with step-wise increase of deformations. Both FBG sensing system and strain gages were tested and compared. Experimental work proved that the FBG sensing system had a good level of accuracy in measuring the static response of the tested composite structure. Moreover the additional advantages such as damp proofing, high sampling rates and real-time inspection make the novel system especially appropriate for load monitoring and damage detection of aerospace structures.
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Paget, Christophe. "Active Health Monitoring of Aerospace Composite Structures by Embedded Piezoceramic Transducers." Doctoral thesis, KTH, Aeronautical Engineering, 2001. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3277.

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The objectives of the thesis work were to study theinteraction between embedded piezoceramic transducers andcomposite structures as well as determine techniques tosimplify the Lamb waves analysis. Firstly, this studyconsidered the design of the embedded piezoceramic transducers.Secondly, the effect of the embedded transducer on thecomposite strength as well as the influence of the mechanicallyloaded composite on the characteristics of the embeddedtransducer were investigated. Finally, to simplify the analysisof such complex Lamb wave responses, two techniques weredeveloped. They were based on the wavelet technique and amodelling technique, respectively.

The design of the embedded piezoceramic transducers wasimproved by reducing the stress concentrations in the compositeas well as in all components constituting the piezoceramictransducer, that is, the piezoceramic element, interconnectorand conductive adhesive. The numerical analysis showed that thethickness of the interconnector had no significant influence onthe stress state of the piezoceramic transducer. It was alsofound that a compliant conductive adhesive reduced the stressconcentration located at the edge of the piezoceramic element.The structural integrity of composites embedded with theimproved piezoceramic transducer was investigated. Theexperiments, performed in tensile and compressive staticloading, indicated that the strength of the composite was notsignificantly reduced by the embedded piezoceramic transducer.Further investigations were conducted to evaluate theperformance of the improved piezoceramic transducer used as aLamb wave generator embedded in composites subjected tomechanical loading. The tests were conducted in tensile andcompressive static loading as well as fatigue loading. Thestudy showed a large working range of the embedded piezoceramictransducer. A post processing technique based on the waveletswas further assessed in the detection of damage and in thedamage size evaluation. A new wavelet basis was developedspecially for processing the Lamb wave response. This method,focused on the wavelet coefficients from the decomposition Lambwave response, showed promising results in evaluating thedamage size. The wavelets offered a sensitive tool to detectsmall damage, compared to other detection methods, improvingthe damage detection capabilities. The other technique wasdevoted to the simplification of the generated Lamb waves bythe use of multi-element transducers. The transducers weredesigned using both a normal-mode expansion and a FE-method.This technique allowed reducing the effect of a Lamb wave modetowards another. This technique was successfully implemented ina damage detection system in composites.

Keywords:Embedded piezoceramic, transducer, composite,structural integrity, health monitoring, damage detection, Lambwaves, wavelets, normal-mode expansion, FE-method

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Horton, Brandon Alexander. "Comprehensive Multi-Scale Progressive Failure Analysis for Damage Arresting Advanced Aerospace Hybrid Structures." Diss., Virginia Tech, 2017. http://hdl.handle.net/10919/93961.

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In recent years, the prevalence and application of composite materials has exploded. Due to the demands of commercial transportation, the aviation industry has taken a leading role in the integration of composite structures. Among the leading concepts to develop lighter, more fuel-efficient commercial transport is the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept. The highly integrated structure of PRSEUS allows pressurized, non-circular fuselage designs to be implemented, enabling the feasibility of Hybrid Wing Body (HWB) aircraft. In addition to its unique fabrication process, the through-thickness stitching utilized by PRSEUS overcomes the low post-damage strength present in typical composites. Although many proof-of-concept tests have been performed that demonstrate the potential for PRSEUS, efficient computational tools must be developed before the concept can be commercially certified and implemented. In an attempt to address this need, a comprehensive modeling approach is developed that investigates PRSEUS at multiple scales. The majority of available experiments for comparison have been conducted at the coupon level. Therefore, a computational methodology is progressively developed based on physically realistic concepts without the use of tuning parameters. A thorough verification study is performed to identify the most effective approach to model PRSEUS, including the effect of element type, boundary conditions, bonding properties, and model fidelity. Using the results of this baseline study, a high fidelity stringer model is created at the component scale and validated against the existing experiments. Finally, the validated model is extended to larger scales to compare PRSEUS to the current state-of-the-art. Throughout the current work, the developed methodology is demonstrated to make accurate predictions that are well beyond the capability of existing predictive models. While using commercially available predictive tools, the methodology developed herein can accurately predict local behavior up to and beyond failure for stitched structures such as PRSEUS for the first time. Additionally, by extending the methodology to a large scale fuselage section drop scenario, the dynamic behavior of PRSEUS was investigated for the first time. With the predictive capabilities and unique insight provided, the work herein may serve to benefit future iteration of PRSEUS as well as certification by analysis efforts for future airframe development.
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Gunel, Murat. "Linear And Nonlinear Progressive Failure Analysis Of Laminated Composite Aerospace Structures." Master's thesis, METU, 2011. http://etd.lib.metu.edu.tr/upload/12614033/index.pdf.

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This thesis presents a finite element method based comparative study of linear and geometrically non-linear progressive failure analysis of thin walled composite aerospace structures, which are typically subjected to combined in-plane and out-of-plane loadings. Different ply and constituent based failure criteria and material property degradation schemes have been included in a PCL code to be executed in MSC Nastran. As case studies, progressive failure analyses of sample composite laminates with cut-outs under combined loading are executed to study the effect of geometric non-linearity on the first ply failure and progression of failure. Ply and constituent based failure criteria and different material property degradation schemes are also compared in terms of predicting the first ply failure and failure progression. For mode independent failure criteria, a method is proposed for the determination of separate material property degradation factors for fiber and matrix failures which are assumed to occur simultaneously. The results of the present study show that under combined out-of-plane and in-plane loading, linear analysis can significantly underestimate or overestimate the failure progression compared to geometrically non-linear analysis even at low levels of out-of-plane loading.
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Books on the topic "Composite Aerospace Structures"

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Kassapoglou, Christos. Design and analysis of composite structures: With applications to aerospace structures. Reston, Va: American Institute of Aeronautics and Astronautics, 2010.

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Kassapoglou, Christos. Design and analysis of composite structures: With applications to aerospace structures. Reston, Va: American Institute of Aeronautics and Astronautics, 2010.

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Elhajjar, Rani. Additive Manufacturing of Aerospace Composite Structures: Fabrication and Reliability. Warrendale, PA: SAE International, 2017. http://dx.doi.org/10.4271/pt-181.

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Mei, C. Nonlinear analyses of composite aerospace structures in sonic fatigue. Norfolk, Va: Dept. of Mechanical Engineering & Mechanics, College of Engineering & Technology, Old Dominion University, 1992.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Advanced polymeric & metallic composite materials for space and aerospace vehicle structures & strength optimization of composite structures and their certification. Neuilly-sur-Seine, France: AGARD, 1995.

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Wiedemann, Martin. Adaptive, tolerant and efficient composite structures. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013.

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Gangloff, R. P. NASA-UVa Light Aerospace Alloy and Structures Technology Program (LA2ST): A progress report, January 1, 1991 to June 30, 1991. Charlottesville, VA: School of Engineering & Applied Science, University of Virginia, 1991.

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Gangloff, R. P. NASA-UVa Light Aerospace Alloy and Structures Technology Program (LA2ST): A progress report, January 1, 1991 to June 30, 1991. Charlottesville, VA: School of Engineering & Applied Science, University of Virginia, 1991.

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Sih, George C. Advanced Technology for Design and Fabrication of Composite Materials and Structures: Applications to the Automotive, Marine, Aerospace and Construction Industry. Dordrecht: Springer Netherlands, 1995.

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Paipetis, A. Carbon Nanotube Enhanced Aerospace Composite Materials: A New Generation of Multifunctional Hybrid Structural Composites. Dordrecht: Springer Netherlands, 2013.

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Book chapters on the topic "Composite Aerospace Structures"

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Murthy, C. R. L. "NDT for Diagnosis, Characterisation and Quality Assurance for Products for Aerospace Applications." In Composite Structures, 213–21. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-662-11345-5_10.

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Millán, Javier San, and Iñaki Armendáriz. "Delamination and Debonding Growth in Composite Structures." In Springer Aerospace Technology, 63–88. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-04004-2_3.

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Dzuba, A. S., A. A. Ionov, and V. F. Kutyinov. "Application of the finite-element method to the structural analysis of composite structures." In Composite Materials in Aerospace Design, 372–88. Dordrecht: Springer Netherlands, 1996. http://dx.doi.org/10.1007/978-94-011-0575-0_6.

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Stuchalkin, Yu A., A. V. Stewart, and A. E. Ushakov. "Characteristics of the certification of composite structures." In Composite Materials in Aerospace Design, 389–430. Dordrecht: Springer Netherlands, 1996. http://dx.doi.org/10.1007/978-94-011-0575-0_7.

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Duenas, Terrisa, Jennifer Vander Vennet, Akhilesh Jha, Karen Chai, Christian Nelsen, A. John Ayorinde, and Ajit Mal. "Using Remendable Polymers for Aerospace Composite Structures." In Mechanics of Time-Dependent Materials and Processes in Conventional and Multifunctional Materials, Volume 3, 1–5. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4614-0213-8_1.

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Wandowski, T., P. Malinowski, M. Radzienski, S. Opoka, and W. Ostachowicz. "Methods for Assessment of Composite Aerospace Structures." In Computational Methods in Applied Sciences, 227–44. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-44507-6_12.

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Jha, Ratneshwar, Rani Sullivan, and Ramadas Chennamsetti. "In SituStructural Health Monitoring Systems for Aerospace Structures." In Structural Health Monitoring Technologies and Next-Generation Smart Composite Structures, 395–414. Taylor & Francis Group, 6000 Broken Sound Parkway NW, Suite 300, Boca Raton, FL 33487-2742: CRC Press, 2016. http://dx.doi.org/10.1201/9781315373492-12.

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Trunin, Yu P., A. E. Ushakov, and S. A. Lurie. "Methods for experimental and analytical evaluation of the residual strength of composite structures with stress concentration." In Composite Materials in Aerospace Design, 295–342. Dordrecht: Springer Netherlands, 1996. http://dx.doi.org/10.1007/978-94-011-0575-0_4.

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Nilsson, Sören, Alann André, and Anders Bredberg. "An Experimental Study on the Strength of Out of Plane Loaded Composite Structures." In Springer Aerospace Technology, 223–30. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-04004-2_10.

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Korobenko, A., M. Pigazzini, X. Deng, and Y. Bazilevs. "Multiscale DDDAS Framework for Damage Prediction in Aerospace Composite Structures." In Handbook of Dynamic Data Driven Applications Systems, 677–96. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-95504-9_30.

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Conference papers on the topic "Composite Aerospace Structures"

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HADJRIA, RAFIK, and OSCAR D’ALMEIDA. "Structural Health Monitoring for Aerospace Composite Structures." In Structural Health Monitoring 2019. Lancaster, PA: DEStech Publications, Inc., 2019. http://dx.doi.org/10.12783/shm2019/32280.

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CHAMIS, C. "Computational composite mechanics for aerospace propulsion structures." In 2nd Aerospace Maintenance Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1190.

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Santo, L., F. Quadrini, D. Bellisario, and A. G. Accettura. "Conceptual Prototypes of Composite Structures for Aerospace." In ASME 2016 11th International Manufacturing Science and Engineering Conference. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/msec2016-8621.

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Abstract:
Shape memory composites (SMCs) are very interesting for self-deployable structures in aerospace applications. SMCs have been widely developed but not yet fully applied to space. In this study a lab-scale production of SMC prototypes for aerospace is described. Conceptual design of small-scale structures were prototyped with the aim to define several configurations which are able to self-deploy. SMC prototypes were manufactured by using two layers of carbon/epoxy prepreg with a shape memory epoxy resin interlayer. Two different configurations were produced to prototype complex shape for multiple folding and 3D deployments of de-orbiting structures. In particular, the first prototype tests a de-orbiting system without the sail to study the complex folding and de-folding mechanisms. The second configuration evaluates a de-orbiting dual-sail for satellite applications. The SMC structures were produced in the opened shape and subsequently memorized in the closed configuration. The initial deployed configuration is recovered by heating the prototype. The closed configuration increases the packing efficiency of large structures for space orbiting systems. The shape memory properties were provided only to folding zones. Memory-recovery-cycles have been performed to test SMC performances. As a result, the two configurations can successfully self-deploy following the desired design constraints and recovering the original flatness without noticeable defects.
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Jegley, Dawn, Chauncey Wu, James Phelps, Leonard Oremont, and Martin McKenney. "Structural Efficiency of Composite Struts for Aerospace Applications." In 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-1788.

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Havar, Tamas, Joerg Middendorf, and Carolin Werchner. "Design and Manufacturing of Composite Aerospace Load Introduction Structures." In 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-1737.

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Patel, Sneha, and Scott Case. "Durability of a woven polymer matrix composite in aerospace applications." In 41st Structures, Structural Dynamics, and Materials Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-1680.

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Bauchau, O., H. Zhang, R. Loewy, S. Atluri, O. Bauchau, H. Zhang, R. Loewy, and S. Atluri. "Nonlinear aeroelastic effects in damaged composite aerospace structures." In 35th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-577.

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Hou, Weiguo, Weifang Zhang, and Qingyun Tang. "Progress in patch repair of aerospace composite structures." In Third International Conference on Smart Materials and Nanotechnology in Engineering. SPIE, 2012. http://dx.doi.org/10.1117/12.923795.

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Tewfic, Tarik, and M. Sarhadi. "Novel folding device for manufacturing aerospace composite structures." In Intelligent Systems and Smart Manufacturing, edited by Bhaskaran Gopalakrishnan and Angappa Gunasekaran. SPIE, 2000. http://dx.doi.org/10.1117/12.403654.

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d'Ippolito, Roberto, Stijn Donders, Michael Hack, Nick Tzannetakis, Geert Van der Linden, and Dirk Vandepitte. "Reliability-based design optimization of composite and steel aerospace structures." In 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
14th AIAA/ASME/AHS Adaptive Structures Conference
7th. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-2153.

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Reports on the topic "Composite Aerospace Structures"

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Peters, Kara J., and Mohammed A. Zikry. Intelligent Multi-scale Sensors for Damage Identification and Mitigation in Woven Composites for Aerospace Structural Applications. Fort Belvoir, VA: Defense Technical Information Center, August 2012. http://dx.doi.org/10.21236/ada579751.

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