Relevant bibliographies by topics / Composite aircraft joints

Academic literature on the topic 'Composite aircraft joints'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Composite aircraft joints"

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Maier, Raluca. "Study on Increasing Performances of Hybrid Composite Through Pull Out Compression Test Assessement." Materiale Plastice 57, no. 1 (April 17, 2020): 329–35. http://dx.doi.org/10.37358/mp.20.1.5325.

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The exhaustive use of light advanced polymer composites into the development of the future high-efficiency long-range commercial aircrafts (primary) structures for increasing strength while decreasing weight for lower fuel consumption and less pollution has attracted great attention in the last decade. In this context, solutions for the integration and joining composites into the aircraft structures metallic sub-assemblies or components, while providing the necessary strength to sustain heavily loaded joints, are urgently required. The paper comes to meet an area of interest for many researchers and large integrators and manufacturers, by presenting several type of metallic join geometrical designs, along with metallic joint part integration solutions into a composite structure directly during production. Performances evaluation of the developed metallic join geometrical designs was performed in static regime by means of �pull-out� compressive tests. The paper focuses on the strength of the hybrid metallic/advanced polymer composites joints. It was concluded that an efficient design of the metallic joint and a proper transition from hybrid to the composite structure can lead to proper integration solutions while assuring safety requirements.
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Chowdhury, Nabil, Wing Kong Chiu, and John Wang. "Review on the Fatigue of Composite Hybrid Joints Used in Aircraft Structures." Advanced Materials Research 891-892 (March 2014): 1591–96. http://dx.doi.org/10.4028/www.scientific.net/amr.891-892.1591.

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The use of composite materials as a replacement for commonly used metals such as aluminium and steel are increasing in the engineering industry, particularly in the aerospace sector. The move towards light weight and high stiffness structures that have good fatigue durability and corrosion resistance has led to the rapid move from metal to composites. This change allows for further flexibility in design and fabrication of various components and joints. There are three main categories of joints used in composite materials – mechanically fastened joints, adhesively bonded joints and the combination of the two called hybrid joints. In order to adequately understand the effectiveness of these joints, substantial testing and validation is required, particularly in the use of hybrid joints for real life applications. Static testing, load distribution and parametric studies of hybrid joints have been investigated by various researchers; however further work is still required in understanding the durability and fatigue of hybrid joints and ensuring that both the adhesive and mechanical fasteners can work together effectively in producing an optimum joint. Mechanical fastening alone in composite laminates is not a preferred joining method as they create high stress concentrations around the fastener holes. Adhesive bonding although has numerous benefits it is difficult to detect the bond defect particularly in cases where weak bonds can occur during applications and it is sensitive towards the environmental conditions. Thus hybrid joints are seen arguably as being more effective in joining composite components together and offer greater residual strength. Hence the performance, strength and long-term durability of these joints need to be further investigated and be applied to practical situations whilst assisting in repair certification.
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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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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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Rufin, Antonio C., and Robert L. Jochum. "Fatigue Analysis and Design of Composite-Metal Joints in Primary Aircraft Structures." Advanced Materials Research 891-892 (March 2014): 588–93. http://dx.doi.org/10.4028/www.scientific.net/amr.891-892.588.

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Increasingly broader application of composite materials in commercial airplane primary structure has led to a renewed, more in-depth assessment of the effect composite elements in mechanical joints have on the durability of the metal structure to which they are mated. Thermal stresses, clamp-up loss due to composite creep, composite joint properties, and lightning and electrical grounding effects have been found to be some of the parameters most significantly affecting or limiting the fatigue performance of the metallic constituents within these hybrid joints, influencing the way joint design and analysis are approached.
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McCarthy, Michael. "BOJCAS: bolted joints in composite aircraft structures." Air & Space Europe 3, no. 3-4 (May 2001): 139–42. http://dx.doi.org/10.1016/s1290-0958(01)90077-2.

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Chernov, Andrey, Danil Fomin, Ivan Kondakov, Ivan Mareskin, and Alexander Shanygin. "Lightweight and reliable metal–composite joints based on harmonization of strength properties of joined parts." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 14 (May 24, 2018): 2663–72. http://dx.doi.org/10.1177/0954410018778797.

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One of the key problems of designing composite primary aircraft structures is the problem of development of lightweight and reliable joints for such structures. For conventional bolted joints used for connection of laminated composite primary structure elements, the loads are transferred via the contact of metallic and composite parts having considerably different strength and stiffness parameters. As the local strength properties of composites are defined by polymer resins, having several times less strength as compared to the metallic alloys, the maximal load that can be transferred via the joint is limited by the properties of resins. As a consequence, the metallic parts of such joints are loaded to a very low extent, that causes low weight efficiency. In the presented paper, the approach to development of metal–composite joints based on the principle of harmonization is proposed. The harmonization principle is to minimize the disbalance of strength properties of metallic and composite parts in the local zones of contact. This principle can be realized by two ways: either by removing the resin from the zone of contact to increase local stiffness of composite part (“stiff” joint concept) or by creation of metallic part with porous structure to decrease local stiffness of the metallic part (“soft” joint concept). In this paper, the evaluation of both concepts is given, based on numerical and experimental investigations carried out in this work.
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Balinova, Yu A., D. V. Graschenkov, A. A. Shavnev, V. G. Babashov, A. S. Chaynikova, E. I. Kurbatkina, and A. N. Bolshakov. "High-temperature heat-shielding, ceramic and ceramic-metal composite materials for new-generation aviation equipment." Journal of «Almaz – Antey» Air and Defence Corporation, no. 2 (July 19, 2020): 83–92. http://dx.doi.org/10.38013/2542-0542-2020-2-83-92.

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This paper describes achievements of the All-Russian Scientific Research Institute of Aviation Materials in the field of creating high-temperature heat-shielding, ceramic and metal-ceramic composite materials. The advantages and prospects of applying the developed materials in the manufacturing of structural elements of aircraft and friction joints are discussed. The synthesis features and basic properties of metal-ceramic composite materials based on light alloys, refractory metal matrices, ceramic composite materials for use in heavily loaded structural elements of modern aircraft are presented. The main achievements in the field of heat-shielding materials based on refractory oxide fibres are presented, along with their properties and application in new-generation aircrafts.
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Jadee, Khudhayer J., and A. R. Othman. "Fiber Reinforced Composite Structure with Bolted Joint – A Review." Key Engineering Materials 471-472 (February 2011): 939–44. http://dx.doi.org/10.4028/www.scientific.net/kem.471-472.939.

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Fiber reinforced composite structures are widely used in the aerospace, aircraft, civil and automotive applications due to their high strength-to-weight and stiffness-to-weight ratios and these applications require joining composite either to composite or to metal. There are three main methods for joining composite structures namely, bonding, mechanically fastened or a combination of the two. Bolted joint are preferred in structures where the disassembly is required for the purpose of maintenance and repair. Due to the stress concentration around the holes, bolted joints often represents the weakest part in the structure, and therefore it is important to design them safely. A review on the study of bolted joints in fiber reinforced composite structure is presented. It was found that the behavior of bolted joints in composite structure is affected by many factors, such as geometry, joint material, clamping–load provided by the bolts, ply orientations, etc. Accordingly, various researches have been conducted on the analyses of stress distribution, failure prediction, and strength properties of bolted joint both experimentally and numerically. Accurate prediction of stresses in bolted joints is essential for reliable design of the whole structure; if it is not optimally designed, premature and unexpected failures may be occurred.
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Hart-Smith, L. J. "An Engineer'S Viewpoint on Design and Analysis of Aircraft Structural Joints." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 209, no. 2 (April 1995): 105–29. http://dx.doi.org/10.1243/pime_proc_1995_209_278_02.

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The design of structurally efficient joints in aircraft fuselage structures and wing skin splices is addressed. It is contended that the joints should be designed first and the gaps in between filled in afterwards, taking pains not to optimize the basic structure first and then discover that it either cannot be assembled or that, when it is assembled, it is full of weak-link fuses. Both adhesively bonded and mechanically fastened joints are covered. Analogies are drawn between the characteristics of both classes of joints. The aspects of static joint strength and fatigue lives are included. The work is applicable to metallic as well as composite structures, and covers both high-load wing joints which have already been tested and new ideas for fuselage splices which have not. The effects of flaws and defects are associated with the need for damage tolerance, particularly in fuselage structures.
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Dissertations / Theses on the topic "Composite aircraft joints"

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Evans, Simon. "Characterisation of outgassing from carbon fibre composite aircraft joints subjected to lightning current." Thesis, Cardiff University, 2018. http://orca.cf.ac.uk/117887/.

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Outgassing is a lightning direct effect that may occur at structural joints in the fuel laden volume of an aircraft. If uncontrolled, the event is extremely hazardous due to its potential to cause fuel vapour ignition. The aerospace industry has been aware of the threat for many years and lightning strike protection is well established. However, there is a lack of understanding particularly concerning the fundamental mechanisms for the creation of the event. Modern aircraft designs that utilise materials such as carbon fibre reinforced plastic (CFRP), are more dependent on manufacturing process control. Knowledge of the fundamental mechanisms responsible for outgassing can enable relaxation of specifications concerning manufacturing variables that exist, specifically, for the lightning protection of CFRP structures. Evidence from previous studies has revealed the significance of parameters relating to the interface between the fastener and the surrounding structure. However, the electrical parameter that drives the creation of the phenomenon remains unclear. The principle aim of this thesis was to determine a single measurable electrical parameter related to outgassing intensity in CFRP structures which can be used as a performance metric for the optimisation of lightning strike protection. Following the execution of three controlled experiments, it was found that outgassing intensity is a direct consequence of the magnitude of electrical energy absorbed, specifically, at the interface between the fastener shank and the surrounding CFRP structure. Characterisation techniques for robust voltage measurement and the distribution of current to the critical interface were developed to deduce the magnitude of energy absorption. This critical parameter can be now used as a control parameter in future aircraft development for the optimisation of lightning strike protection.
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Kapidzic, 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.

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The use of fibre composites in the design of load carrying aircraft structures has been increasing over the last few decades. At the same time, aluminium alloys are still present in many structural parts, which has led to an increase of the number of hybrid composite-aluminium structures. Often, these materials are joined at their interface by bolted connections. Due to their different response to thermal, mechanical and environmental impact, the composite and the aluminium alloy parts are subject to different design and certification practices and are therefore considered separately.The current methodologies used in the aircraft industry lack well-developed methods to account for the effects of the mismatch of material properties at the interface.One such effect is the thermally induced load which arises at elevated temperature due to the different thermal expansion properties of the constituent materials. With a growing number of hybrid structures, these matters need to be addressed.  The rapid growth of computational power and development of simulation tools in recent years have made it possible to evaluate the material and structural response of hybrid structures without having to entirely rely on complex and expensive testing procedures.However, as the failure process of composite materials is not entirely understood, further research efforts are needed in order to develop reliable material models for the existing simulation tools. The work presented in this dissertation involves modelling and testing of bolted joints in hybrid composite-aluminium structures.The main focus is directed towards understanding the failure behaviour of the composite material under static and fatigue loading, and how to include this behaviour in large scale models of a typical bolted airframe structure in an efficient way. In addition to that, the influence of thermally induced loads on the strength and fatigue life is evaluated in order to establish a design strategy that can be used in the industrial context. The dissertation is divided into two parts. In the first one, the background and the theory are presented while the second one consists of five scientific papers.
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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.

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Harman, Alex Bruce Mechanical &amp Manufacturing Engineering Faculty of Engineering UNSW. "Optimisation and improvement of the design of scarf repairs to aircraft." Awarded by:University of New South Wales. School of Mechanical and Manufacturing Engineering, 2006. http://handle.unsw.edu.au/1959.4/26788.

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Flush repairs to military aircraft are expected to become more prevalent as more thick skin composites are used, particularly on the surface of the fuselage, wings and other external surfaces. The use of these repairs, whilst difficult to manufacture provide an aerodynamic, ???stealthy??? finish that is also more structurally efficient than overlap repairs. This research was undertaken to improve the design methodology of scarf repairs with reduced material removal and to investigate the damage tolerance of scarf repair to low velocity impact damage. Scarf repairs involve shallow bevel angles to ensure the shear stress in the adhesive does not exceed allowable strength. This is important when repairing structures that need to withstand hot and humid conditions, when the adhesive properties degrade. Therefore, considerable amounts of parent material must be machined away prior to repair. The tips of the repair patch and the parent laminate are very sharp, thus a scarf repair is susceptible to accidental damage. The original contributions include: ??? Developed analytic means of predicting the stresses within optimised scarf joints with dissimilar materials. New equations were developed and solved using numerical algorithms. ??? Verified using finite element modelling that a scarfed insert with dissimilar modulus subjected to uniaxial loading attracted the same amount of load as an insert without a scarf. As such, the simple analytic formula used to predict load attraction/diversion through a plate with an insert may be used to predict the load attraction/diversion into a scarf repair that contains a dissimilar adherend patch. ??? Developed a more efficient flush joint with a doubler insert placed near the mid line of the parent structure material. This joint configuration has a lower load eccentricity than external doubler joint. ??? Investigated the damage tolerance of scarf joints, with and without the external doubler. The results showed that scarf joints without external doublers exhibited a considerable strength reduction following low velocity impact. Based on the observations, the major damage mechanics in the scarf joint region following impact have been identified. These results demonstrated that it is important to incorporate damage tolerance in the design of scarf repairs.
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Renart, Canalias Jordi. "Desarrollo de un nuevo ensayo experimental para la evaluación de la calidad de uniones adhesivas entre componentes estructurales de composite para la indústria aeronáutica." Doctoral thesis, Universitat de Girona, 2010. http://hdl.handle.net/10803/296679.

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El uso de los composites en la industria aeronáutica ha experimentado un fuerte crecimiento en los últimos años debido a la utilización de componentes de composite que realizan funciones estructurales. A menudo, para disminuir los costes de producción, las partes esbeltas del fuselaje se unen con elementos rigidizadores mediante uniones adhesivas. Para asegurar que las uniones adhesivas cumplirán la función estructural para la cual se han diseñado se realizan ensayos a nivel de probeta. En el presente trabajo se realiza un análisis de los métodos de ensayo experimental que se llevan a cabo para determinar la calidad de las uniones adhesivas (las cuales dependen principalmente de la calidad de la preparación superficial, las propiedades del adhesivo y la compatibilidad entre el adhesivo y los adherentes). La tesis se enfoca a dos objetivos: la propuesta de mejoras del ensayo de doble viga en voladizo y el desarrollo de un método alternativo de propagación de grieta por avance forzado de una cuña (Wedge Driven Test, WDT). En cuanto al ensayo de doble viga en voladizo, se han diseñado unos utillajes de sujeción mecánica de la probeta a la máquina de ensayo y se ha propuesto una metodología experimental adaptada a la propagación discontinua del frente de grieta. En relación al nuevo método de ensayo, se ha desarrollado un procedimiento dirigido, al igual que el DCB actual, a determinar la tenacidad a la fractura en modo I de la unión adhesiva, mediante la introducción forzada de una cuña. Las ventajas que ofrece el ensayo WDT respecto el DCB es que es más rápido, económico, no se necesita ningún tipo de preparación previa de la probeta y no hace falta realizar mediciones de la longitud de grieta. Para poner a prueba la sensibilidad del ensayo WDT a la calidad de la unión se ha realizado una serie de campañas experimentales, en las cuales se han analizado 4 configuraciones de unión adhesiva distintas (como resultado de la combinación de dos adherentes y dos adhesivos). Así mismo se han ensayado preparaciones intencionadamente defectuosas. De los resultados de las campañas experimentales se ha observado que el ensayo de propagación de grieta por avance forzado de cuña presenta unos resultados equivalentes a los del ensayo DCB y es sensible a la calidad de la preparación superficial.
The use of composite materials in the aircraft industry has been increasing in recent years due to their application in structural parts. To reduce the production costs of these components the join between skins and stiffeners is made by means of an adhesive. In order to guarantee that the bonded joint fulfils the structural requirements, experimental tests on specimens are done from the first development tasks and throughout the production stages. In the present work, an analysis of the experimental test methods to determine the quality of bonded joints has been performed - the quality of bonded joints depends on the quality of the surface preparation, the adhesive properties and the compatibility between the adhesive and the adherents. The work focuses on two objectives: the improvement of the double cantilever beam test, and the development of an alternative method of bonded joint characterization based on driving a wedge into the adhesive layer (Wedge Driven Test, WDT). In the double cantilever beam test, a mechanical fixture tool has been designed and a data reduction method for stick-slip crack propagation has been developed. On the other hand, the alternative test method such as the DCB, focuses on determining the fracture toughness in mode I of the adhesive joint, by means of introducing a wedge inside the specimen at a constant speed rate. To prove the sensitivity of the WDT to the quality of the adhesive joint, a series of testing campaigns has been performed over 4 adhesive joint configurations (combining 2 adhesives and 2 adherents). Moreover, deliberately produced bad surface preparations have been tested. From the test results, it has been observed that the driven wedge test exhibits an equivalent behaviour to the double cantilever beam test and has a similar level of sensitivity to the quality of the bonded joint.
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Books on the topic "Composite aircraft joints"

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., ed. Critical joints in large composite primary aircraft structures. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1988.

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Critical joints in large composite primary aircraft structures. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1988.

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Critical joints in large composite primary aircraft structures. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

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L, Sagui R., and Langley Research Center, eds. Critical joints in large composite primary aircraft structures. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

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Book chapters on the topic "Composite aircraft joints"

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Noeske, Michael, Welchy Leite Cavalcanti, Hauke Brüning, Bernd Mayer, Antonios Stamopoulos, Apostolos Chamos, Thomas Krousarlis, et al. "Introduction to Recent Advances in Quality Assessment for Adhesive Bonding Technology." In Adhesive Bonding of Aircraft Composite Structures, 1–50. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-319-92810-4_1.

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AbstractThe first chapter highlights the relevance of both adhesive bonding technology and in-process quality assessment for mastering twenty-first-century challenges in joining functional and lightweight materials like carbon fibre reinforced polymers. The ongoing developments of the relevant technological and regulatory procedures and frameworks are hereby outlined, following trends for data-driven innovation and standardisation. Advances from monitoring process variables towards the in-depth and objective Extended Non-destructive Testing (ENDT) of material-related features are presented, based on methodological and technological innovation and insights from recent European joint research projects like Horizon 2020s ComBoNDT—“Quality assurance concepts for adhesive bonding of aircraft composite structures by advanced NDT”. Introducing ten heuristic principles for quality assessment in bonding processes, a concept is demonstrated for establishing empirically consolidated sets of quantitative material and process-specific correlations between design-relevant joint features and quality data measured during the manufacture or repair of adhesive joints using ENDT. Each correlation is obtained by systematically introducing disturbances of relevant process features identified by experts and is levelled once by linking findings from standardised mechanical tests with ENDT results obtained for joints that have intentionally been manufactured or repaired in an off-specification way. Subsequent chapters will demonstrate the suitability of the broadly applicable process.
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Tserpes, Konstantinos, Elli Moutsompegka, Mareike Schlag, Kai Brune, Christian Tornow, Ana Reguero Simón, and Romain Ecault. "Characterization of Pre-bond Contamination and Aging Effects for CFRP Bonded Joints Using Reference Laboratory Methods, Mechanical Tests, and Numerical Simulation." In Adhesive Bonding of Aircraft Composite Structures, 51–117. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-319-92810-4_2.

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AbstractIn this chapter, the pre-bond contamination and ageing effects on carbon fiber reinforced plastic (CFRP) adherends and CFRP bonded joints are characterized by means of reference laboratory non-destructive testing (NDT) methods, mechanical tests, and numerical simulation. Contaminations from two fields of application are considered, namely in aircraft manufacturing (i.e. production) and for in-service bonded repair. The production-related scenarios comprise release agent, moisture, and fingerprint, while the repair-related scenarios comprise fingerprint, thermal degradation, de-icing fluid, and a faulty curing of the adhesive. For each scenario, three different levels of contamination were pre-set and applied, namely low, medium and high level. Furthermore, two types of samples were tested, namely coupons and pilot samples (a stiffened panel and scarf repairs). The CFRP adherends were contaminated prior to bonding and the obtained surfaces were characterized using X-ray photoelectron spectroscopy. After bonding, the joints were tested by ultrasonic testing. To characterize the effects of each contamination on the strength of the bonded joints, mode-I and mode-II fracture toughness tests, and novel centrifuge tests were conducted on the coupons, while tensile tests were performed on the scarfed samples. Additionally, numerical simulation was performed on CFRP stiffened panels under compression using the LS-DYNA finite element (FE) platform.
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Malinowski, Paweł H., Tomasz Wandowski, Wiesław M. Ostachowicz, Maxime Sagnard, Laurent Berthe, Romain Ecault, Igor Solodov, Damien Segur, and Marc Kreutzbruck. "Extended Non-destructive Testing for the Bondline Quality Assessment of Aircraft Composite Structures." In Adhesive Bonding of Aircraft Composite Structures, 223–57. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-319-92810-4_4.

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AbstractWe present the results of extended non-destructive testing (ENDT) methods for bond line quality assessment in adhesive joints. The results presented were derived for important application scenarios with regards to aircraft manufacturing and the in-service repair of composite structures. The electromechanical impedance (EMI), laser shock adhesion testing (LASAT), and nonlinear ultrasound scanning (NUS) were used on flat coupon samples, scarfed samples, and curved samples. The EMI method applied to the flat coupons showed some relation of the frequency shift to the level of contamination. For the curved samples, there was insufficient sensitivity to differentiate distinct levels of contamination, while for scarfed samples in most cases both detection and distinction were possible. The LASAT method gave good results for the coupon samples, which were also in accordance with the results of the $${\text{G}}_{\text{IC}}$$ G IC and $${\text{G}}_{\text{IIC}}$$ G IIC tests. For coupon samples with multiple contaminations, we obtained results with varying significance. In the case of NUS, the measurements revealed an increase in nonlinearity affected by contamination at the interphase between the CFRP adherend and the adhesive layer for the majority of scenarios comprising single contamination of flat coupons and scarfed samples. The effect of multiple contaminations was a decrease in nonlinearity for the curved samples.
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Leite Cavalcanti, Welchy, Elli Moutsompegka, Konstantinos Tserpes, Paweł H. Malinowski, Wiesław M. Ostachowicz, Romain Ecault, Neele Grundmann, et al. "Integrating Extended Non-destructive Testing in the Life Cycle Management of Bonded Products—Some Perspectives." In Adhesive Bonding of Aircraft Composite Structures, 331–50. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-319-92810-4_6.

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AbstractIn this chapter, we outline some perspectives on embracing the datasets gathered using Extended Non-destructive Testing (ENDT) during manufacturing or repair process steps within the life cycle of bonded products. Ensuring that the ENDT data and metadata are FAIR, i.e. findable, accessible, interoperable and re-usable, will support the relevant stakeholders in exploiting the contained material-related information far beyond a stop/go decision, while a shorter time-to-information will facilitate a prompter time-to-decision in process and product management. Exploiting the value of ENDT (meta)data will contribute to increased performance by integrating all defined, measured, analyzed and controlled aspects of material transformation across process and company boundaries. This will facilitate the optimization of manufacturing and repair operations, boosting their energy efficiency and productivity. In this regard, some aspects that are currently driving activities in the field of pre-process, in-process and post-process quality assessment will be addressed in the following. Furthermore, some requirements will be contemplated for harmonized and conjoint data transfer ranging from a bonded product’s beginning-of-life through its end-of-life, the customization of stand-alone or linked ENDT tools, and the implementation of sensor arrays and networks in joints, devices and structural parts to gather material-related data during a product’s middle-of-life application phase, thereby fostering structural health monitoring (SHM).
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Vallejo, Nabil, L. A. Reyes, G. M. Hernández-Muñoz, and P. Zambrano-Robledo. "Parametric Effects in Hybrid Lap Joints of Composite Materials Used in Aircraft Structures." In Proceedings of the Symposium of Aeronautical and Aerospace Processes, Materials and Industrial Applications, 129–39. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-65611-3_12.

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Faisal, Nadimul, Ömer Necati Cora, Muhammed Latif Bekci, Romana Ewa Śliwa, Yehuda Sternberg, Shashank Pant, Richard Degenhardt, and Anil Prathuru. "Defect Types." In Structural Health Monitoring Damage Detection Systems for Aerospace, 15–72. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-72192-3_3.

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AbstractThis chapter provides an overview of the common types of defects found in various structural materials and joints in aircraft. Materials manufacturing methods (including large-scale production) have been established in the aircraft industry. However, as will be seen in this chapter, manufacturing defects and defects during in-service conditions are very common across all material types. The structural material types include metals, composites, coatings, adhesively bonded and stir-welded joints. This chapter describes the defect types as a baseline for the description of their detection with the methods of Chap. 10.1007/978-3-030-72192-3_5 to 10.1007/978-3-030-72192-3_8. Based on the understanding of the defect types, there is great expectation for a technical breakthrough for the application of structural health monitoring (SHM) damage detection systems, where continuous monitoring and assessment with high throughput and yield will produce the desired structural integrity.
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Ueda, Y., H. Kuroki, T. Murooka, A. Tanaka, K. Miyazawa, I. Okumura, Y. Shigenari, K. Oikawa, and H. Morita. "Damage Tolerance Demonstration of Flange Joint for Aircraft Engine Composite Fan Case." In ICAF 2011 Structural Integrity: Influence of Efficiency and Green Imperatives, 207–18. Dordrecht: Springer Netherlands, 2011. http://dx.doi.org/10.1007/978-94-007-1664-3_17.

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CHALKLEY, P., C. WANG, and A. BAKER. "Fatigue Testing of Generic Bonded Joints." In Advances in the Bonded Composite Repair of Metallic Aircraft Structure, 103–26. Elsevier, 2002. http://dx.doi.org/10.1016/b978-008042699-0/50007-3.

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Molent, Lorrie, and Rhys Jones. "The F111C Wing Pivot Fitting Repair and its Implications for the Design/Assessment of Bonded Joints and Composite Repairs." In Aircraft Sustainment and Repair, 511–43. Elsevier, 2018. http://dx.doi.org/10.1016/b978-0-08-100540-8.00010-8.

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Melhem, George Nadim. "Aerospace Fasteners: Use in Structural Applications." In Encyclopedia of Aluminum and Its Alloys. Boca Raton: CRC Press, 2019. http://dx.doi.org/10.1201/9781351045636-140000240.

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Aircraft components need to be selected and manufactured to adequately combat the environment, temperature, loading, compatibility, and so on. When structural materials such as aluminum alloys or fiber-reinforced polymer composites need to be joined in aircraft, the selection of fasteners, bolts, rivets, adhesives, and other methods need to be quantitatively assessed in order that the correct design for the component and joining method is identified. There is a variety of fasteners, bolts, and rivets, made using a variety of materials. Aluminum rivets are often used to join aluminum components in an aircraft. Rivets do not perform well under tension loading, but perform better in shear, thus limiting the application specifically for these purposes. Bolts are designed to clamp material together, and even though the bolt may be adequate to support a particular structure and load requirement, consideration must also be given to the modulus of elasticity and stiffness of the components that are being clamped together. Therefore, an understanding of each of the materials being clamped or joined together is necessary. Bolts manufactured from steel, for instance, have coatings applied in order to help protect them from corrosion. The use of composites translates to a reduced number of rivets and fasteners to be used. Drilling of holes into composites to insert fasteners poses many challenges because the fibers are damaged, a region of high stress concentration may be formed, and the hole is a site for the ingress of water or moisture. The insertion of aluminum fasteners or the contact of aluminum components with carbon fibers creates galvanic corrosion due to the large difference in electrical potential. Titanium alloy (Ti-6Al-4V) is a typical fastener where there is composite joining due to its better compatibility (elimination of galvanic corrosion) and increased strength properties. Substitution of rivets and fasteners for welding is also on the increase in aircraft because laser beam welding (LBW) and friction stir welding both reduce cracking, porosity, and better properties achieved due to deeper penetration, and reduce the heat-affected zone which would typically be undesirable with conventional arc welding such as metal inert gas and tungsten inert gas welding. The shear and compressive stresses are increased, and fatigue cracking, weight, and cost are also reduced as a result of LBW, including the elimination of stresses and corrosion associated with rivets and the elimination of adhesives. Dissimilar metals such as the 7000 series and the 2000 series can be joined with a filler metal compatible to both metals to mitigate galvanic corrosion.
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Conference papers on the topic "Composite aircraft joints"

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Evans, S. J. "Fasteners: addressing the problem of sparking composite joints." In IET Seminar on Lightning Protection for Aircraft Components. Institution of Engineering and Technology, 2013. http://dx.doi.org/10.1049/ic.2013.0175.

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PLAKA, EVGENIA, BRETT BEDNARCYK, and MARIANNA MAIARÙ. "DESIGN OF ADHESIVELY BONDED COMPOSITE JOINTS USING A RAPID DESIGN TOOL." In Proceedings for the American Society for Composites-Thirty Seventh Technical Conference. Destech Publications, Inc., 2022. http://dx.doi.org/10.12783/asc37/36492.

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The optimization of composite structural joints is an iterative process and a multiscale problem. High fidelity finite element modeling of joints with 3D woven and laminated materials can become computationally expensive. The aim of this paper is to present the applicability of a reliable analysis process for the optimization of the composite Y-joint (curved Pi-joint), to be used in an aircraft fuselage, using a commercial rapid joint design tool analysis optimization software. The rapid joint design tool was investigated as a substitute and/or complement to a finite element analysis software. A composite Pi-joint and a composite Y-joint were evaluated using the rapid joint design tool. Furthermore, two main preliminary parametric studies were performed to better understand the capability of the tool in predicting the failure load trends in the Y-joint. The parameters investigated were the joint curvature and the laminated skin thickness. Failure loads are found using interactive stress-based criteria. Lastly, the Y-joint modeled using the rapid tool was validated against experimental results with an agreement of less than 10% of the experimental value reported.
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Bazˇant, Zdeneˇk P., Jia-Liang Le, Ferhun C. Caner, and Qiang Yu. "Size Effect on Strength of Bi-Material Joints of Steel With Fiber-Polymer Composite." In ASME 2008 International Mechanical Engineering Congress and Exposition. ASMEDC, 2008. http://dx.doi.org/10.1115/imece2008-69229.

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Metal-composite joints between steel ribs and advanced fiber-polymer composites are an effective structural system for hybrid ship hulls. Similar joints are of interest for fuel-efficient aircraft. The current designs of such joints are generally based on the strength criterion, which ignores fracture mechanics. Aimed at an efficient and reliable design, this study investigates the size effect on the strength of these joints theoretically, numerically and experimentally. The analytical formulation of the size effect is asymptotically anchored at the large-size limit in linear elastic fracture mechanics (LEFM). The bi-material corner of the joint is shown to have a singular stress field with complex singularity. The strength of the joint is determined by the energy criterion for the macrocrack initiation at the corner, from which the large-size asymptote of the size effect law has been derived. A general approximate size effect law, spanning all sizes and various joint angles, is further derived via asymptotic matching. Numerical analysis with cohesive fracture model is used to design the experiments. Experimental studies involve the testing of geometrically similar hybrid joint specimens with the size ratio of 1 : 4 : 12. The analytical, numerical and experimental studies all indicate that the strength of bimaterial metal-composite joints is subjected to a strong size effect.
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Mahmoud, Hassan A., Mostafa Shazly, Yehia Bahei-El-Din, and Emad El-Kashif. "Analysis of Composite Bolted Connection Joints Under Out of Plane Loading." In ASME 2020 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/imece2020-23303.

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Abstract The use of composite joints has been increased in recent years in structural applications such as aircraft, civil engineering structure, ship structure, wind energy sector, and automotive industry. In this paper, the behaviour of composite bolted connection joints under out of plane loading is investigated. A parametric study was conducted to study the joint stiffness variation with various geometric parameters, which include the edge distance, bolt diameter, plate width, and the laminate stacking sequence. The experimental work was conducted on GFRP tension clips (L-angle) joint specimens manufactured by the vacuum infusion technique. In the present work, two types of laminates were used, unidirectional laminates [0°]5 with an areal density of 1050 gm/m2, triaxial laminates [−45°/+45°/0°]5 with an areal density of 1200 g/m2. A 3D finite element (FE) model was developed to study the effect of joint parameters on its stiffness. Finite element models were constructed, and the experimental results were used to validate the finite element models. The analysis concluded that the failure load increases when the edge distance to bolt diameter ratio (E/D) increases and the triaxial stacking sequence is better than unidirectional. The (E/D) ratio, the (W/D) ratio and stacking sequence were found to be very significant parameters.
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Carr, Daniel, David Clark, Chris Stone, Manu Haddad, Simon Evans, Matthew Jenkins, and Matthew Cole. "Optical Techniques For the Analysis of Outgassing of Composite Aircraft Joints Under Lightning." In 2018 34th International Conference on Lightning Protection (ICLP). IEEE, 2018. http://dx.doi.org/10.1109/iclp.2018.8503423.

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Yeh, P. C., P. Y. Chang, J. M. Yang, and D. Kordonowy. "The Effect of Damage on the Bonding Strength of Hybrid T-Joint Structures." In ASME 2012 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/imece2012-85924.

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Adhesively co-bonded and co-cured structural joints are attractive for aircraft applications due to the potential reduction in weight and part count as compared to traditional mechanical joints. In this research, a damage tolerant structure using co-bonded hybrid T-joints was designed and manufactured for structural application on a remotely piloted aircraft. The T-joint structure was constructed from GLAss fiber REinforced aluminum laminates (GLARE) 4-2/1 skin, carbon fiber composite web, and three-dimensional woven glass fiber fabric Pi-preform in a co-bonded/co-cured process. The goal of this research is to demonstrate the damage tolerance, structural capability, and ancillary benefits of the co-bonded T-joint. In order to evaluate the structural design and investigate the strength of manufactured T-joint, experiments such as pull-out tests were performed. Additionally, the T-joint was manufactured and tested with defects inserted intentionally within the co-bonded interface between the GLARE and Pi-preform at two locations: a) underneath the vertical woven carbon composite web, and b) along the edge of the glass fiber Pi-preform and the GLARE flange. Pull-out tests showed the effect of intentionally inserted defects on the strength of the co-bonded T-joint structure. The benefit of co-bonded joints featuring damage tolerant skins and high strength composite webs has been demonstrated.
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LIN, WENHUA, YEQING WANG, SPENCER LAMPKIN, SRIHARI GANESH PRASAD, OLESYA ZHUPANSKA, and BARRY DAVIDSON. "BOND STRENGTH DEGRADATION OF ADHESIVE- BONDED CFRP COMPOSITE LAP JOINTS AFTER LIGHTNING STRIKE." In Thirty-sixth Technical Conference. Destech Publications, Inc., 2021. http://dx.doi.org/10.12783/asc36/35742.

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Adhesive bonding to join fiber reinforced polymer matrix composites holds great promise to replace conventional mechanical attachment techniques for joining composite components. Understanding the behavior of these adhesive joints when subjected to various environmental loads, such as lightning strike, represents an important concern in the safe design of adhesively bonded composite aircraft and spacecraft structures. In the current work, simulated lightning strike tests are performed at four elevated discharge impulse current levels (71.4, 100.2, 141, and 217.8 kA) to evaluate the effects of lightning strike on the mechanical behavior of single lap joints. After documentation of the visually observed lightning strike induced damage, single lap shear tests are conducted to determine the residual bond strength. Post-test visual observation and cross-sectional microscopy are conducted to document the failure modes of the adhesive region. Although the current work was performed on a limited number of specimens, it identified important trends and directions for future more comprehensive studies on lightning strike effects in adhesively bonded composites. It is found that the lightning strike induced damage (extent of the surface vaporization area and the delamination depth) increases as the lightning current increases. The stiffness of the adhesive joints and shear bond strength did not show a clear correlation with the lightning current levels, which could be due to many competing factors, including the temperature rise caused by the lightning strike and the surface conditions of the adherends prior to bonding. The failure modes of the adhesive regions for all specimens demonstrate a mixed mode of adhesive and cohesive failure, which may be due to inconsistent surface characteristics of the adherends before bonding. The energy absorbed during the lap shear tests generally increases as the lightning current increases.
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Bogdanovich, Alexander E., and Sergei P. Yushanov. "Failure Prediction of Bonded Joints of Composite Engineering Structures." In ASME 1998 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/imece1998-1199.

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Abstract First part of the paper presents brief review of fracture mechanics applications to progressive failure prediction in adhesive bonded joints under mechanical loading end environmental effects (temperature and moisture) typical for the aircraft and civil engineering structures. Existing concepts of critical energy release rates and critical stress intensity factors for fracture modes I and II are evaluated in the context of failure and durability of adhesive bonded joints. The challenging problem of reliable experimental fracture toughness characterization of bonded laminated composites is emphasized. Second part of the paper presents novel development of 3-D variational analysis aimed at predicting crack propagation in adhesive composite bonded joints exposed to mechanical loading combined with variable temperature and moisture. A general 3-D variational thermo-hygro-mechanical approach is developed, based on the principle of minimum total potential energy. A brick-type composite mosaic model is allowing to incorporate the material property variation in all three coordinate directions. The displacement field in each of the bricks is approximated in terms of triple series with Bernstein basis functions of an arbitrary degree used in all the coordinate directions. In the case of no pre-existing cracks, all of the bricks are perfectly bonded through the displacement continuity conditions. If there is a 2-D surface crack perpendicular to one of the coordinate axes (the crack can be arbitrarily located inside the structure, including any part of the interfaces or bondlines), then the respective displacement continuity conditions are released along the corresponding surface area. A progressive failure analysis approach is then developed using the energy release rates evaluated for various possible scenarios of a cohesive, adhesive or interlaminar crack propagation. Several cracks of the same type or different types can be analyzed simultaneously. Numerical examples illustrate application of the developed analysis approach to double-lap adhesive bonded joints with cross-ply laminated composite adherends under some typical thermomechanical loading cases. The moisture effect is incorporated through the time-dependent critical energy release rates for Modes I and II. Several pre-existing cracks are introduced (separately or conjointly), and their propagation is followed using the computed strain energy release rates around the crack tip. Importantly, each of the distinct failure modes (adhesive, cohesive or interlaminar) is characterized by its specific critical strain energy release rate sensitive to the penetrating moisture. Numerical results and their comparison with available experimental data show that the developed analysis approach is capable of predicting the paths of dominating failure modes in adhesively bonded laminated composite joints.
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Grimes, Glenn C. "Building Block Approach for Composite Aircraft Structure Prototypes: Allowables and Building Block Testing for DOD/NASA Vehicles." In ASME 1998 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/imece1998-0387.

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Abstract Composite material allowables development required for prototype aircraft is discussed along with the related building block test effort necessary for such structure development. Allowables requirements are included as part of building block structural test requirements that are related to aircraft structure part criticality classifications. Then, each part of the building block is related to the test/evaluation/analysis categories that need to be interrogated to study the risk involved. For allowables, the categories are preliminary and “design-to” values related to physical defect minimum requirements in each classification. For the building block structures development test effort categories, the procedure used is progressive scale up of the size and complexity of the test program parts: from single to multiple load paths to joints and shapes. In summary, the relationship of the quality assurance requirements to those required for design allowables for flat panels to those required for intermediate structural components to those required for full size structure are discussed. Quality assurance requirement categories are discussed for each structural classification, size, and complexity of parts to be built. The building block structures test development effort satisfies the goals of: 1. Preliminary and “design-to” material allowables development, 2. Appropriate conceptual structural development, 3. Structural proof of concept and related analytical methods development, 4. Structural verification testing for analytical methods correlation, and 5. Structural integrity testing and FEM validations. Once these goals are achieved the user has acceptable risk and cost effective prototype composite aircraft structure that has the necessary integrity and reliability needed for the specific prototype aircraft being developed.
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Lee, David E., and H. Thomas Hahn. "Virtual Assembly Production Analysis of Composite Aircraft Structures." In ASME 1995 15th International Computers in Engineering Conference and the ASME 1995 9th Annual Engineering Database Symposium collocated with the ASME 1995 Design Engineering Technical Conferences. American Society of Mechanical Engineers, 1995. http://dx.doi.org/10.1115/cie1995-0815.

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Abstract Concurrent with the use of tailored materials for specific applications has been the understanding that a product’s design has a significant and measurable effect on manufacturing process cycle times and unit production costs. In order to reliably manufacture and assemble aircraft structures fabricated from composite materials on a cost-effective basis, an environment for virtual assembly production analysis is being developed. Within this environment, members of an aircraft’s integrated product development team can rapidly assess the impact of design decisions on individual assembly operations and overall aircraft assembly in a virtual manufacturing context. Effects related to joint design and component matings are measured based on force and process conditions as well as the types of tooling required for final assembly. By evaluating assembly production impacts early during product design, the costly design-manufacture-redesign cycle is redefined and recast based on the realities of manufacturing process constraints.
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