Дисертації з теми "Composite aircraft structure"
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Bigand, Audrey. "Damage assessment on aircraft composite structure due to lightning constraints." Thesis, Toulouse, ISAE, 2020. http://www.theses.fr/2020ESAE0027.
Повний текст джерелаAs composite materials are now widely used in the aeronautical industry, the sizing of these structures andtheir protection against lightning has become a major issue. It is important to develop predictive tools to obtaina structure concept that meets certification requirements with a controlled time and cost during the designphase. The interaction of lightning with a composite structure is a complex multi-physics phenomenon, with afurther difficulty due to the presence of a metallic protection on the surface and a layer of paint. In this context,this study aimed to develop an understanding of the forces generated by lightning and to assess itsconsequences in terms of damage to the composite. To this end, the phenomenon was first broken down tostudy its different components and define the impact of their interactions. In a first step, the free arc wascompared to the arc root in interaction with different substrates to define a vaporisation model of the lightningprotection. In a second step, the overpressure generated by the explosion of the surface protection duringvaporisation was evaluated to define spatio-temporal pressure profiles. In a third step, a mechanicalcharacterization of the paint was developed in order to quantify its confinement effect on the surface explosion.At each stage, a theory was developed and analysed via numerical models and tests. Finally, these threedifferent bricks are brought together in a mechanical model simulating the lightning impact on a compositestructure in order to predict the damage. In addition, a user subroutine has been developed to apply thiscomplex loading as well as a damage law. These models are compared with lightning laboratory test results todetermine their validity limits and their ability to predict the damage
Svalstedt, Mats, and Sofia Swedberg. "Commercial Aircraft Wing Structure : - Design of a Carbon Fiber Composite Structure." Thesis, KTH, Skolan för teknikvetenskap (SCI), 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-276702.
Повний текст джерелаDetta projekt utforskar den klassiska vingstrukturen av ett kommersiellt flygplan för en obemannad luftfarkost gjord helt i kolfiberarmerad polymer. Det är en del av ett samarbete som består av flera projektgrupper som forskar på olika delar av flygplanet. Målet med projektet är att designa den inre vingstrukturen för en miljövänligare, mer effektiv uppskalad 2:1 version av drönaren Skywalker X8. För att göra flygplanet så effektiv som möjligt så behöver den vara lättviktig. Lasterna var först uppskattade via XFLR5 och en första design gjordes. Designen testades sedan med finita elementmetoden (FEM) i programmet Ansys Static Structural. Materialet som testades var kolfiber/epoxi prepreg. Den slutgiltiga vingdesignen väger 3.815 kg, och består av en bom och en tjocklek på 1 mm av vingskalet. Totala vikten av flygplanet, inklusive framdrivningssystemet samt virveldämpare på båda vingspetsarna som är framtagna av andra grupper, är 20.262 kg. Glidtalet beräknades även, och är som mest effektiv runt 2-3°.
Mahdi, Stephane. "The performance of bonded repairs to composite structures." Thesis, Imperial College London, 2001. http://hdl.handle.net/10044/1/7815.
Повний текст джерелаBail, Justin L. "Non-desctructive investigation & FEA correlation on an aircraft sandwich composite structure." Akron, OH : University of Akron, 2007. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=akron1196702586.
Повний текст джерела"December, 2007." Title from electronic thesis title page (viewed 02/25/2008) Advisor, Wieslaw Binienda; Faculty readers, Craig Menzemer, Robert Goldbert; Department Chair, Wieslaw Binienda; Dean of the College, George K. Haritos; Dean of the Graduate School, George R. Newkome. Includes bibliographical references.
Bail, Justin. "Non-Destructive Investigation & FEA Correlation on an Aircraft Sandwich Composite STructure." University of Akron / OhioLINK, 2007. http://rave.ohiolink.edu/etdc/view?acc_num=akron1196702586.
Повний текст джерелаLiu, Hongfen. "A structural design comparison of metallic and composite aircraft pressure retaining doors." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7308.
Повний текст джерелаCrump, Duncan Andrew. "Performance analysis of a reduced cost manufacturing process for composite aircraft secondary structure." Thesis, University of Southampton, 2009. https://eprints.soton.ac.uk/142803/.
Повний текст джерелаSatterwhite, Matthew Ryan. "Development and Validation of Fluid-Structure Interaction in Aircraft Crashworthiness Studies." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/51559.
Повний текст джерелаMaster of Science
Backhouse, R. "Multiaxial non-crimp fabrics : characterisation of manufacturing capability for composite aircraft primary structure applications." Thesis, Cranfield University, 1998. http://dspace.lib.cranfield.ac.uk/handle/1826/1929.
Повний текст джерелаXu, Rongxin. "Optimal design of a composite wing structure for a flying-wing aircraft subject to multi-constraint." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7290.
Повний текст джерелаColeman, Robert Mark 1962. "The effects of design, manufacturing processes and operations management on the assembly of aircraft composite structure." Thesis, Massachusetts Institute of Technology, 1991. http://hdl.handle.net/1721.1/42495.
Повний текст джерелаIncludes bibliographical references (leaf 104).
by Robert Mark Coleman.
M.S.
Marengo, Giovanni. "The use of unidirectional carbon fibre rods in high loaded joints for a composite large civil aircraft wing structure." Thesis, Cranfield University, 2002. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.393700.
Повний текст джерелаPecorella, Daniele. "Methodology for the design and optimization of a morphing wing droop-nose structure for greener aircraft." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2022.
Знайти повний текст джерелаCook, Lawrence. "Visual inspection reliability for composite aircraft structures." Thesis, Cranfield University, 2009. http://dspace.lib.cranfield.ac.uk/handle/1826/6834.
Повний текст джерелаNyman, Tonny. "Fatigue and residual strength of composite aircraft structures." Doctoral thesis, KTH, Aeronautical Engineering, 1999. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-2848.
Повний текст джерелаWhisler, Daniel A. "Low velocity blunt impacts on composite aircraft structures." Diss., [La Jolla] : University of California, San Diego, 2009. http://wwwlib.umi.com/cr/ucsd/fullcit?p1470612.
Повний текст джерелаTitle from first page of PDF file (viewed January 12, 2010). Available via ProQuest Digital Dissertations. Includes bibliographical references (p. 102-104).
Watkins, R. I. "Multilevel optimum design of large laminated composite structures." Thesis, Cranfield University, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.374011.
Повний текст джерелаClark, Randal John. "Damage tolerance of bonded composite aircraft repairs for metallic structures." Thesis, University of British Columbia, 2007. http://hdl.handle.net/2429/31275.
Повний текст джерелаApplied Science, Faculty of
Mechanical Engineering, Department of
Graduate
Becerra, Pozo Natalia I. "Analysis and optimisation of composite truss structures for aircraft applications." Thesis, Oxford Brookes University, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.444336.
Повний текст джерелаKapidzic, Zlatan. "Strength analysis and modeling of hybrid composite-aluminum aircraft structures." Licentiate thesis, Linköpings universitet, Hållfasthetslära, 2013. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-91894.
Повний текст джерелаKaufmann, Markus. "Cost Optimization of Aircraft Structures." Doctoral thesis, KTH, Lättkonstruktioner, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-11482.
Повний текст джерелаQC 20100723
European Framework Program 6, project ALCAS, AIP4-CT-2003-516092
Nationella flygtekniska forskningsprogrammet (NFFP) 4, project kostnadseffektiv kompositstruktur (KEKS)
Aljets, Dirk. "Acoustic emission source location in composite aircraft structures using modal analysis." Thesis, University of South Wales, 2011. https://pure.southwales.ac.uk/en/studentthesis/acoustic-emission-source-location-in-composite-aircraft-structures-using-modal-analysis(6871e94b-6e94-4efd-b563-41b254ee27b4).html.
Повний текст джерелаDayyani, Iman. "Mechanical behavior of composite corrugated structures for skin of morphing aircraft." Thesis, Swansea University, 2015. https://cronfa.swan.ac.uk/Record/cronfa42865.
Повний текст джерелаDavies, Thomas Gethin. "The analysis of bonded repair solutions for primary composite aircraft structures." Thesis, Swansea University, 2013. https://cronfa.swan.ac.uk/Record/cronfa42862.
Повний текст джерелаKaufmann, Markus. "Cost/Weight Optimization of Aircraft Structures." Licentiate thesis, Stockholm : Farkost- och flyg, Kungliga Tekniska högskolan, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-4645.
Повний текст джерелаEslimy-Isfahany, Seyed Hamid Reza. "Dynamic response of thin-walled composite structures with application to aircraft wings." Thesis, City University London, 1998. http://openaccess.city.ac.uk/7719/.
Повний текст джерелаBenchekchou, Boutaina. "Stresses around fasteners in composite aircraft structures and effects on fatigue life." Thesis, University of Southampton, 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.241160.
Повний текст джерелаLand, Ian B. (Ian Brett). "Design and manufacture of advanced composite aircraft structures using automated tow placement." Thesis, Massachusetts Institute of Technology, 1996. http://hdl.handle.net/1721.1/31076.
Повний текст джерелаIncludes bibliographical references (leaves 89-91).
by Ian B. Land.
S.M.
Bendemra, Hamza. "Automation of Lay-Up in the Repair of Advanced Composite Aircraft Structures." Phd thesis, Canberra, ACT : The Australian National University, 2016. http://hdl.handle.net/1885/101713.
Повний текст джерелаMativo, John M. "System Design of Composite Thermoelectrics for Aircraft Energy Harvesting." University of Dayton / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1607959975788155.
Повний текст джерелаKapidzic, Zlatan. "Static and Fatigue Failure of Bolted Joints in Hybrid Composite-Aluminium Aircraft Structures." Doctoral thesis, Linköpings universitet, Mekanik och hållfasthetslära, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-122349.
Повний текст джерелаLazarin, Juan Reuben. "Optimum Design of Composite Wing Spar Subjected to Fatigue Loadings." DigitalCommons@CalPoly, 2017. https://digitalcommons.calpoly.edu/theses/1816.
Повний текст джерелаKhan, Jehan Zeb. "Static, dynamic and aeroelastic behaviour of thin-walled composite structures with application to aircraft wings." Thesis, City University London, 1992. http://openaccess.city.ac.uk/7992/.
Повний текст джерелаMohammed, Bizuayehu Y. "Damage characterisation in twill-weave CFRP composite aircraft structures using modal analysis of acoustic emission signals." Thesis, University of South Wales, 2016. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.702330.
Повний текст джерелаSeitz, Timothy J. "Formulation of a structural model for flutter analysis of low aspect ratio composite aircraft wings." Diss., This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-05042006-164511/.
Повний текст джерелаMatt, Howard M. "Structural diagnostics of CFRP composite aircraft components by ultrasonic guided waves and built-in piezoelectric transducers." Connect to a 24 p. preview or request complete full text in PDF format. Access restricted to UC campuses, 2007. http://wwwlib.umi.com/cr/ucsd/fullcit?p3238426.
Повний текст джерелаTitle from first page of PDF file (viewed January 4, 2007). Available via ProQuest Digital Dissertations. Vita. Includes bibliographical references (p. 203-216).
Clermont, Paul Daniel Stanley. "Characterization and prediction of flow electrification phenomena in fuel tanks of aeronautical structures." Thesis, Poitiers, 2016. http://www.theses.fr/2016POIT2258/document.
Повний текст джерелаWith the new generation of composite aircrafts an attention is carried out on fuel systems with respect to prevention of electrostatic discharges (ESD) during the filling phases of the tanks. Most of the work realized in aeronautics (during the 60's) was conducted on metallic fuel tanks. However, the introduction of composite materials has raised new questions, since those materials can have a different behavior than metallic ones with respect to flow electrification, which fully justify new analyses. In order to properly define the tank structures and their protection against ESD hazards, it is crucial to understand how a complex stack of materials (conductive or not, multilayered or homogeneous, painted or not) constituting a fuel tank behaves with respect to the mechanisms of charge creation by flow electrification when these materials are in contact with aviation fuel. The structure of these materials and their electrical properties control the electric potential reached in the tank through a balance between the production, accumulation and leakage of the electrical charge. This potential may exceed the flash point of the fuel vapors/air mixture and induce ignition. Various protective measures can be adopted to control this phenomenon such as using antistatic additives in the fuels, lowering the rates ofthe fuel injection inside the tank, using only bonded metallic tanks or tanks made of non-metallic materials which do not favor charge accumulation or local charge trapping. It is majorly in response to the latter solution that this work is oriented in order to guide optimum choices of materials and a better definition of the tank structures
Isbilir, Ozden. "Optimisation of the geometry of the drill bit and process parameters for cutting hybrid composite/metal structures in new aircrafts." Thesis, University of Sheffield, 2012. http://etheses.whiterose.ac.uk/2890/.
Повний текст джерелаVandeveld, Thierry F. R. "Etude expérimentale multisensorielle de la dynamique des impacts d'oiseaux sur structures d'avions." Doctoral thesis, Universite Libre de Bruxelles, 2009. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/210274.
Повний текст джерелаParmi les acteurs qui luttent contre ce danger, les constructeurs d'avions jouent un rôle prépondérant. Contraints par des réglementations internationales, ils s'attachent à produire des éléments de structure qui résistent à l'impact d'oiseaux.
Dans la mise au point de leur produits, les avionneurs démontrent cette résistance à l'aide d'essais d'impact :on accélère un simulant d'oiseau jusqu'à la vitesse voulue -- de l'ordre de la vitesse de croisière nominale de l'avion -- et on le projette sur un aileron ou un morceau de fuselage.
La présente thèse doctorale, co-dirigée par les professeurs Philippe Bouillard de l'ULB et Marc Pirlot de l'ERM, contribue doublement à l'amélioration de ces techniques d'essais dynamiques.
D'une part, elle réalise la mise au point et la validation d'un lanceur pyrotechnique à double étage pour l'accélération du simulant d'oiseau. Un canon de calibre 20 mm est combiné avec un accélérateur de calibre 160 mm. La combustion d'un mélange de poudre propulsive contenu dans une douille adaptée génère les gaz à haute température et à haute pression nécessaires à l'accélération d'un simulant d'oiseau dûment confiné dans un conteneur de protection. Un dispositif de séparation arrête le conteneur afin que seul le simulant d'oiseau percute l'élément d'avion à l'essai. La solution pyrotechnique à double étage mise au point est validée par de nombreux tirs instrumentés en vitesse, en accélération et en pression ;elle se révèle conforme aux exigences de sécurité et de reproductibilité. Le lanceur pyrotechnique présente par rapport aux solutions pneumatiques, utilisées à notre connaissance dans tous les autres centres d'essais, des avantages indéniables de compacité ainsi que de rapidité et de souplesse de mise en oeuvre.
D'autre part, la migration des alliages métalliques vers les matériaux composites est amorcée depuis plusieurs années déjà dans le monde de la construction aéronautique. Pour optimiser les structures, une connaissance des caractéristiques de ces matériaux est indispensable. Les modes de rupture font partie des caractéristiques encore mal connues. La mesure du déplacement hors-plan lors du tir sur panneaux plans est une des manières de quantifier le comportement du matériau sous l'action d'un impact. Cette mesure s'opère généralement de manière statique, après le tir. Une méthode de mesure dynamique a été mise au point, basée sur l'emploi de techniques de stéréoscopie par corrélation numérique d'images. Cette technique a été validée au moyen d'une méthode métrologique indépendante d'extensométrie laser.
ABSTRACT
Countless collisions occur each year between airplanes and birds. Bird strike is a concern to both civilian and militay aircraft. Statistics show that, although the number of serious accidents fortunately remains low, the number of incidents keeps increasing.
Amongst the actors tackling this issue, aircraft manufacturers play an important role. In compliance with international regulations, they have to produce structural elements that withstand bird impact. During the development of their products, aircraft manufacturers have to demonstrate this resistance through bird impact trials :a bird surrogate is accelerated to the required velocity - often close to the nominal cruise speed of the aircraft - and launched onto a flap or a piece of fuselage.
This PhD thesis has been co-supervised by Professor Philippe Bouillard (ULB) and Professor Marc Pirlot (ERM-KMS). Its contribution to the improvement of the aforementioned dynamic trials is twofold.
One one hand, a two-stage pyrotechnical launcher for bird surrogates has been developed and assessed. A 20 mm caliber gun is connected to a 160 mm diameter launcher. The combustion of a propellant mixture in a cartridge case generates high pressure, high temperature gases which accelerate a bird surrogate protected by a cylindrical container. A stripper refrains the container from hitting the target pane.
The pyrotechnical solution has been assessed through an important number of firings where pressure, velocity and acceleration have been measured. The solution has proven compliance with both the safety requirements and the repeatability specifications. Its advantages compared to the pneumatic solutions used, as far as we know, in all other test centres, include compactedness as well as flexibility and high firing rate.
On the other hand, migration towards composite materials has been initiated years ago in the area of aeronautical constructions.
To optimize structures, a thorough knowledge of these new materials is required. Failure modes belong to the still badly known features of carbon reinforced plastics. Measuring the out-of-plane deformation when firing on a flat pane is one way of quantifying the material's behaviour under impact. This measurement is most frequently made in a static way, after completion of the firing. A dynamic measuring method has been developed, based upon stereoscopic digital image correlation techniques. This technique has been validated by means of an independent laser extensometer measuring method.
Doctorat en Sciences de l'ingénieur
info:eu-repo/semantics/nonPublished
Sakarya, Arzu. "Multidisciplinary Design Of An Unmanned Aerial Vehicle Wing." Master's thesis, METU, 2011. http://etd.lib.metu.edu.tr/upload/12613606/index.pdf.
Повний текст джерелаmade of prepreg and wet lay-up. All wings have the same aerodynamic geometry and structural configuration under the same flight conditions. The structural designs of three wings were done by using Unigraphics NX. The finite element modeling of the wings were built by using MSC Patran package program. After the application of the loads on models, structural analyses were performed by MSC Nastran. Finally, the producibility analysis of prepreg wing model was conducted by using FiberSIM package program. The prepreg wing model was selected as optimum design with studies conducted in the study considering weight, producibility, cruise and gust stress and displacement conditions.
Foschini, Lorenzo. "Studio della produzione di provini laminati manualmente per prove di caratterizzazione meccanica." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2019.
Знайти повний текст джерелаWu, Ching-Shiuh, and 吳清旭. "Use of embedded optical fibers for damage detection in aircraft composite structure." Thesis, 1993. http://ndltd.ncl.edu.tw/handle/03685677949644815214.
Повний текст джерела國立臺灣大學
材料科學(工程)研究所
81
Optical fibers were embedded in the graphite/ epoxy (Gr/Ep) laminates to study their possibility of use as a sensor to detect the structural damage of the laminates. To improve their reliability. Optical fibers were surface-treated by hydrogen fluoride (HF) and/or silane solutions. According to the Weibull statistical analysis and electronic microscopy, as the optical fibers were treated by HF solution,their tensile failure was changed from intrinsic failure to extrinsic failure so that the distribution of tensile strength was narrower. As to the adhesion of optical fibers to the epoxy resins, the one treated with HF solution for 10 minutes and then coated with silane showed the highest adhesion strength. During the lamination , a laser beam was injected to an embedded optical fiber, and found that the light in tensity was decreased with increasing temperature and pressure. However, after the laminate was cured and returned to the ambient environment, the light intensity could be recovered to the original intensity, indicating that the optical fiber did not damage during lamination. Finally, to detect the structural damage of optical fiber-embedded laminates during tensile testing at an extremely slow rate, a transmitted light intensity was recorded. Experimental results revealed that if the optical fibers were treated with HF solution and then coated with silane they were more sensitive to detect the damage of lami- nates.
王怡安. "Fabrication of Stitched Braided Composite Aircraft Window Frame Structure by Resin Film Infusion." Thesis, 2013. http://ndltd.ncl.edu.tw/handle/zc6drv.
Повний текст джерела逢甲大學
纖維與複合材料學系
102
The aim of this project is to develop a manufacturing technology of high performance aircraft window frame composite structure and discuses the interlaminar shear strength and fracture toughness of structure. Combination of stitch-braided and resin film infusion (RFI) processes to fabrication carbon stitch-braided aircraft window frame composite structure. Whole the project, including stitching and braiding and resin film infusion techniques were studied and detail investigate the interlaminar shear strength (ILSS) and fractographic observations of the failure of stitch-braided composites and the fabrication of aircraft window frame composite structure as well studied. The effects of stitching factor and process parameters on the properties of composite structures were studied. Resin film infusion (RFI) technology for manufacturing aircraft window frame composite structures and the effects of stitching parameters, such as; stitching yarn type, stitching density, stitching layer, stitching space and stitching tension on the stitching process were studied. The fracture toughness (GI and GII) of stitch-braided composites tested by mixed fracture modes test and ILSS were used to evaluate the stitched and braiding process conditions. As well as, the torsion property and compression property and fractographic observations of the failure of window frame composite structure were discussed. Finally, the manufacturing processes technologies of aircraft window frame composite structures were established
Κοτζακόλιος, Αθανάσιος. "Blast response of aircraft structures." Thesis, 2011. http://hdl.handle.net/10889/5068.
Повний текст джерелаΣκοπός της εργασίας αυτής είναι η μελέτη αεροπορικών κατασκευών από σύνθετα υλικά όπου θα παρουσιάζουν βελτιωμένες ιδιότητες υπό συνθήκες έκρηξης σε σύγκριση με υπάρχουσες αντίστοιχες κατασκευές.Ο στόχος αυτός επετεύχθη με ελάχιστη προσθήκη βάρους. Μέσα στους στόχους της παρούσας διατριβής είναι να παρέχει μια μεθοδολογία για την προσθήκη μέσων προστασίας για τις μελλοντικές αεροπορικές κατασκευές.
Ajith, V. "Wave Propagation in Healthy and Defective Composite Structures under Deterministic and Non-Deterministic Framework." Thesis, 2012. http://hdl.handle.net/2005/3253.
Повний текст джерелаClark, Randal John. "Prediction of fatigue damage progression in bonded composite repairs to aluminum aircraft structures." Thesis, 2000. http://hdl.handle.net/2429/10395.
Повний текст джерелаRobertson, Cameron David. "Structural Characterization, Optimization, and Failure Analysis of a Human-powered Ornithopter." Thesis, 2009. http://hdl.handle.net/1807/18847.
Повний текст джерелаSalva, Joao Manuel Correia. "A load/cost/mass comparison of aluminium, glass, carbon and asbestos fibre composites for immediate application to aircraft primary structures." Thesis, 2015. http://hdl.handle.net/10539/18603.
Повний текст джерелаA comparison of 4 different materials for immediate app l i cation to aircraft primary structures was made on the basis of load-to-buckle/cost/mass. The materials tested were: Al-2024 T3 (Alclad) , glass fibre cloth, carbon fibre and asbestos fibre (Noramite) composites. A m a t h e matical formulation of the problem was used which was found to give very satisfactory res ults. This method made use of beam vibration modes and the Rayleigh-Ritz energy formulation and it was found that even with onl\ 4 modes of vibration, the results agreed very well with the computer analysis. A working equation lor the design of composite panels in shear is also given.
Sudha, J. "Fatigue Damage Characterization Of Carbon/Epoxy Laminates Under Spectrum Loading." Thesis, 2007. http://etd.iisc.ernet.in/handle/2005/2257.
Повний текст джерелаDuport, Nicolas. "Étude de la stabilité dimensionnelle d'un revêtement polymère sur placage de bois pour structures intérieures d'avions." Thèse, 2016. http://hdl.handle.net/1866/19906.
Повний текст джерела