Relevant bibliographies by topics / Composite aircraft structure

Academic literature on the topic 'Composite aircraft structure'

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Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Composite aircraft structure"

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Broer, Agnes A. R., Rinze Benedictus, and Dimitrios Zarouchas. "The Need for Multi-Sensor Data Fusion in Structural Health Monitoring of Composite Aircraft Structures." Aerospace 9, no. 4 (March 30, 2022): 183. http://dx.doi.org/10.3390/aerospace9040183.

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With the increased use of composites in aircraft, many new successful contributions to the advancement of the structural health monitoring (SHM) field for composite aerospace structures have been achieved. Yet its application is still not often seen in operational conditions in the aircraft industry, mostly due to a gap between research focus and application, which constraints the shift towards improved aircraft maintenance strategies such as condition-based maintenance (CBM). In this work, we identify and highlight two key facets involved in the maturing of the SHM field for composite aircraft structures: (1) the aircraft maintenance engineer who requires a holistic damage assessment for the aircraft’s structural health management, and (2) the upscaling of the SHM application to realistic composite aircraft structures under in-service conditions. Multi-sensor data fusion concepts can aid in addressing these aspects and we formulate its benefits, opportunities, and challenges. Additionally, for demonstration purposes, we show a conceptual design study for a fusion-based SHM system for multi-level damage monitoring of a representative composite aircraft wing structure. In this manner, we present how multi-sensor data fusion concepts can be of benefit to the community in advancing the field of SHM for composite aircraft structures towards an operational CBM application in the aircraft industry.
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Utami, Mala, Jonathan Ernest Sirait, Beny Budhi Septyanto, Aries Sudiarso, and I. Nengah Putra Apriyanto. "Laminar Composite Materials for Unmanned Aircraft Wings." Defense and Security Studies 3 (December 21, 2022): 106–12. http://dx.doi.org/10.37868/dss.v3.id211.

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Unmanned Aerial Vehicles (UAVs) have high popularity, especially in the military field, but are now also being applied to the private and public sectors. One of the UAV components that require high material technology is the wing. The latest material technology developed as a material for unmanned aircraft wings is a composite material that has high strength and lightweight. This research aims to identify composite materials that can be used for unmanned aircraft wing structures. The method used in this research is a qualitative method with a literature study approach. The results of this theoretical study show that some of the latest composite materials that have been developed into materials for unmanned aircraft wings are Laminar Composites with a sandwich structure. Laminar and sandwich composites consist of various constituent materials such as Balsa wood fiber-glass and polyester resin, microparticles, Carbon Fibre Reinforced Polymer, polymer matrix composites reinforced with continuous fibers, Polymer matrix composites, E-glass/Epoxy, Kevlar/Epoxy, Carbon/Epoxy, woven fabrics, acrylonitrile butadiene styrene-carbon (ABS) laminated with carbon fiber reinforced polymer (CFRP) and uniaxial prepreg fabrics. Laminar and sandwich composite materials are a reference for developing unmanned aircraft wing structures that have resistant strength and lightweight.
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Li, Fenglei, Shengnian Zhang, and Wanxiang Cheng. "Application and Optimization of Wing Structure Design of DF-2 Light Sports Aircraft Based on Composite Material Characteristics." Journal of Nanomaterials 2022 (June 21, 2022): 1–10. http://dx.doi.org/10.1155/2022/6967016.

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Compared with ordinary metal structures, advanced composite materials have the characteristics of high strength, high rigidity, and light weight. The use of composite materials in aircraft structures is currently a hot research topic. This research mainly discusses the optimization design of the composite wing structure of the DF-2 light sports aircraft. This article takes the DF-2 light sports aircraft planned to be produced by the company as the source. Based on its overall design basis, aerodynamic requirements, and the original wing structure design, according to the composite material aircraft structure design theory and method, the aircraft wing structure is carried out. Composite materials are materials with new properties that are composed of two or more materials with different properties at the macroscale by physical and chemical methods. Composite materials can be divided into functional composite materials and structural composite materials according to the nature of the application. Functional composites are materials with special functions, such as conductive composites, ablative materials, and frictional composites. At present, the main research is on structural composite materials, which are composed of two components: matrix material and reinforcing material. The new structural scheme design and structural strength analysis are designed to meet the structural strength requirements of the wing and the lightest weight. In this paper, according to the force transmission characteristics of different structural types of the wing, the characteristics of the load transmission are analyzed, and the shape parameters and load parameters of the wing structure design are used as initial conditions, and the quantitative analysis model of the wing structure is constructed according to the requirements of strength, stiffness, and stability. Through rapid mathematical modeling and analysis of the wing structure, the weight and efficiency of different configurations can be evaluated. Through the quantitative analysis model of the wing, the wing structure type can be quickly determined according to the wing parameters in the preliminary design, which makes the basis for the selection of the wing structure type. After optimization, the weight of the wing structure decreased from 0.966 kg to 0.803 kg, a decrease of 16.87%. The designability of composite materials is one of its major characteristics. By optimizing the layup angle, layup sequence, and dropout area, the performance indicators of the structure are finally improved. This research will promote the further development of the aerospace field.
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Ganjeh, Babak, and Mohd Roshdi Hassan. "Cost-Efficient Composite Processing Techniques for Aerospace Applications – A Review." Applied Mechanics and Materials 325-326 (June 2013): 1465–70. http://dx.doi.org/10.4028/www.scientific.net/amm.325-326.1465.

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Composite materials have been used in aircraft components since the early beginning of aircraft industry establishment.Undenaible advantages of composites in mechanical properties and light weight in comparison with conventional metal alloys make them desirable alternative for fabrication of different aircraft components. However, quality concerns and high costs of processing tackle the extensive usage of composites in aircraft structure, until the past decade, introducing new generation of composite processing techniques, needless of traditional autoclave processing and capable of fabricating aerospace-grade quality composite parts more time and cost efficiently. In this paper concise review over recent cost-efficient composite processing technologies with proven practicality in commercial aircraft applications, is presented.
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Du, Ya Xiong, Shu Li, and Kai Guo. "Strength Analysis for Composite Windshield of Commercial Aircraft." Advanced Materials Research 1030-1032 (September 2014): 1010–13. http://dx.doi.org/10.4028/www.scientific.net/amr.1030-1032.1010.

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With the development of advanced composites technology, composites instead of traditional aluminum alloy, will be widely used to build full-size aircraft windshield structure in the aviation field. The finite element model of commercial aircraft composite windshield is established in the environment of Msc.Patran / Nastran. And based on Tasi-Wu failure criterion, the strength of windshield structure under typical load pressure is predicted and analyzed during failure processes. It shows that composite windshield can work better through rational design according to the analysis result.
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Armstrong, Keith. "Civil Aircraft Composite Structure Repair Technology." Materials Technology 14, no. 4 (January 1999): 198–210. http://dx.doi.org/10.1080/10667857.1999.11752840.

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Grant, Carroll. "Automated processes for composite aircraft structure." Industrial Robot: An International Journal 33, no. 2 (March 2006): 117–21. http://dx.doi.org/10.1108/01439910610651428.

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Lee, WJ, BH Seo, SC Hong, MS Won, and JR Lee. "Real world application of angular scan pulse-echo ultrasonic propagation imager for damage tolerance evaluation of full-scale composite fuselage." Structural Health Monitoring 18, no. 5-6 (February 24, 2019): 1943–52. http://dx.doi.org/10.1177/1475921719831370.

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Composite structures are assertively used for new airframe designs and manufacturing in military aircrafts because of superior strength-to-weight ratios and fatigue resistance. Because the composites have different fatigue failure characteristics compared with metals, it is necessary to develop different approaches for the composite fatigue design and testing. In this study, we propose an in situ damage evaluation technology with high spatial resolution during full-scale fatigue testing of composite aircraft structures. For real composite structure development considering composite fatigue characteristics, full-scale fatigue and damage tolerance tests of the composite fuselage structure were conducted to evaluate the structural characteristics. In the meantime, the laser ultrasonic nondestructive inspection method, called an angular scan pulse-echo ultrasonic propagation imager, which is fully noncontact, real-time, and portable to position it in between the complex test rigs, is used to observe in situ damage growth of the composite. Finally, the verification procedure assisted by the angular scan pulse-echo ultrasonic propagation imager assures no growth of the initial impact damages after lifetime operation and proves the damage tolerance capability of the developed composite fuselage structure.
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Chernov, Andrey, Ivan Kondakov, and Yury Mirgorodskiy. "Experimental Study of Impact-Protective Elements for Unidirectional Ribs of Lattice Composite Aircraft Structures." MATEC Web of Conferences 304 (2019): 01016. http://dx.doi.org/10.1051/matecconf/201930401016.

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Lattice structures based on unidirectional composite ribs is currently one of the most promising directions of research aiming to create lightweight and reliable structure of future aircrafts [1]. Hybrid structure concepts based on lattice layouts have been developed for a number of conventional and non-conventional civil aircraft configurations, giving up to 15-20% weight saving as compared to conventional composite structures based on laminated skin and stiffeners [2]. One of the most critical problems of load-bearing lattice composite structures is very high sensitivity to impact loads, which is even more crucial than for the laminated composite structures. At the same time, topology of lattice grid makes it possible to create reliable protective system for the ribs, which can be effective in terms of weight expenses.
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Zhang, Jia Rui, Zhen Yu Feng, and Tian Chun Zou. "Certification for Effect of Environment on Composite Properties." Advanced Materials Research 284-286 (July 2011): 396–400. http://dx.doi.org/10.4028/www.scientific.net/amr.284-286.396.

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The environment which can have a great effect on the composite aircraft structure performances must be considered during the design and certification process. In this paper, the extreme temperature and humidity span of the worst environment conditions in aircraft structure design and certification are investigated, and some test methods involving environment influences are also discussed. The studying results can be used in design and certification for environment influences of composite aircraft structures.
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Dissertations / Theses on the topic "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.

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L’utilisation des matériaux composites dans l’industrie aéronautique s’étant largement étendue, ledimensionnement de ces structures et de leur protection vis-à-vis de la foudre est devenu un enjeu majeur. Ilest important de pouvoir développer des outils prédictifs permettant d’obtenir une conception de structurerépondant aux critères de certification avec des temps et coûts de conception maitrisés. L’interaction de lafoudre avec une structure composite est un phénomène multiphysique complexe, avec une difficulté ajoutéepar la présence d’une protection métallique en surface et d’une couche de peinture. Dans ce contexte, cetteétude a visé à développer la compréhension par rapport aux forces générées par la foudre et d’en évaluer sesconséquences quant à l’endommagement du composite. Dans cet objectif, le phénomène a d’abord étédécomposé pour en étudier ses différentes parties et définir l’impact des interactions. Dans un premier temps,l’arc libre a été comparé au pied d’arc en interaction avec différents substrats permettant de définir un modèlede vaporisation de la protection foudre. Dans un second temps, la surpression générée par l’explosion de laprotection en surface lors de la vaporisation a été évaluée pour définir des profils de pression spatio-temporels.Dans un troisième temps, une caractérisation mécanique de la peinture a été développée afin de quantifier soneffet de confinement sur l’explosion de surface. A chaque étape, une théorie a été développée et analysée viades modèles numériques et des essais. Enfin, ces trois différentes briques ont été rassemblées dans un modèlemécanique simulant l’impact foudre sur une structure composite afin d’en prédire l’endommagement. De plus,une loi utilisateur a été développée pour appliquer ce chargement complexe ainsi qu’une loid’endommagement. Ces modèles sont comparés aux résultats d’essai foudre en laboratoire afin d’endéterminer les limites de validité et leur capacité à prédire l'endommagement
As 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
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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.

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This project explores the classical wing structure of an commercial aircraft for an all carbon fiber reinforced polymer unmanned aerial vehicle(UAV). It is part of a collaborative work consisting of several groups researching different parts of the aircraft. The objective of this report is to present the design of the inner wing structure for a greener, more efficient scaled 2:1 version of the Skywalker X8. In order to make the aircraft as efficient as possible, the structure needs to be lightweight. The loads were first approximated using XFLR5 and a first design made. The design was then tested using finite element analysis (FEA) in the programme Ansys Static Structural. The material that was tested was carbon fiber/epoxy prepreg. The final design of the wing weighs 3.815 kg, and consists of one spar and a skin thickness of 1 mm. The weight of the whole aircraft, including the propulsion system and a sharklet at both wingtips researched by other groups, is 20.262 kg. The lift-to-drag ratio was also calculated, and the most efficient angle of attack was concluded to be around 2-3°.
Detta 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°.
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Mahdi, Stephane. "The performance of bonded repairs to composite structures." Thesis, Imperial College London, 2001. http://hdl.handle.net/10044/1/7815.

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Bail, 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.

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Thesis (M.S.)--University of Akron, Dept. of Civil Engineering, 2007.
"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.
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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.

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Liu, 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.

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The pressure retaining door is obviously a sensible part of an aircraft, and the design criteria is much more critical than for the fuselage, so a problem caused by this critical criteria is the heavy weight of the door structure because it should be strong enough to withstand loads and stiff enough to meet the sealing requirements. In spite of the pressure retaining door being so important, it is difficult to find design references. So, in this thesis, the pressure retaining door is investigated first, and then a typical structure of a type A door is selected as the study case using both metallic and composite material, in order to generate a standard method for door structure design, and to identify the key factors which can affect the structure weight. The study indicates that the structure weight of a type A door can be kept in a range for different combinations of beams and stringers, and the composite door structure can be 20% lighter than the metallic door while the stiffness of the two doors remains similar. It is found that the skin contributes much more weight to the door structure than other components and the skin thickness is affected by the short edge of the skin panel divided by beams and stringers. The results also found that it is much more serious when the end stop fails than when the middle stops fail. Therefore, it appears that the composite door is a good material as an alternative to aluminium. Also the method of door structure design is reasonable for the composite door, although it would be better to consider the stiffness of beams while in the theory design period. Besides IRP, the Group Design Project (GDP) is another important part of the MSc study; it lasts nearly half a year and we complete the Fly-wing concept design. The main contribution of the author to the GDP is the arrangement of doors, and also includes the family issues, cabin layout arrangement and a 3D model construct, which can be seen in APPENDIX B. According to the GDP work, I will have broadened my professional knowledge and will have an overall view of aircraft design.
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Crump, 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/.

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In the current, environmentally-aware, climate aircraft designers are under increasing pressure to produce fuel efficient vehicles. Weight reduction is an important method for increasing fuel efficiency. Fibre reinforced polymer (FRP) composites are known to offer weight savings over traditional metallic components, due to their excellent stiffness and strength to weight ratios. However, the major limiting factor for the use of aerospace quality composites is the manufacturing cost. The costs incurred in the conventional process of prepreg cured in an autoclave are well documented. The research in this thesis is concerned with reducing the cost of manufacturing aircraft standard carbon fibre composite sandwich panels, whilst maintaining mechanical performance. The overall aim of the EngD is to provide a unified approach for assessing the performance of carbon fibre sandwich secondary structure that are manufactured using several different techniques. Cost and performance criteria are defined so that an optimal panel can be produced. The work has been motivated by the industrial sponsor, GE Aviation Systems. Five combinations of raw material and processing techniques, manufacturing options (MOs) were considered in incremental steps from the baseline of unidirectional prepreg cured in an autoclave to the noncrimp fabric (NCF) infiltrated using resin film infusion (RFI) and cured in a conventional oven. For cost and performance analysis a generic panel has been designed that is representative of secondary wing structure on commercial passenger aircraft. The cost was estimated by monitoring the manufacture of generic panels using each MO, whilst the performance was measured by both mechanical characterisation tests and by full scale tests on a custom designed rig. The rig applies a pressure load using a water cushion and allows optical access to the surface of the panel enabling the use of optical techniques, i.e. thermoelastic stress analysis (TSA) and digital image correlation (DIC). Feasibility tests on TSA and DIC demonstrated their use on the materials considered in this thesis, and were used to validate finite element (FE) models. The RFI out-of-autoclave process was found to reduce generic panel manufacture time by almost 30%, and the material cost was reduced by almost 40%. The mechanical characterisation tests suggested the ‘new’ process could produce laminates with a similar fibre volume fraction to that of the original process and similar in and out-of-plane mechanical properties. The in-plane stiffness was slightly reduced by 7 %, but the strength showed an increase of 12%. Full scale tests on the generic panels using point out-of-plane deflection measurements and full field TSA demonstrated the panel produced using the ‘new’ process has adequate performance. Moreover the full-field tests indicated an improvement in performance. Further work is required to optimise the design of the panel for weight, in particular the weight of the raw material, and investigating methods for modelling the NCF for certification.
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Satterwhite, Matthew Ryan. "Development and Validation of Fluid-Structure Interaction in Aircraft Crashworthiness Studies." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/51559.

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Current Federal Aviation Regulations require costly and time consuming crashworthiness testing to certify aircraft. These tests are only capable of a limited assessment of progressive damage and all crash configurations and scenarios cannot be physically evaluated. Advancements in technology have led to accurate and effective developments in numerical modeling that have the possibility of replacing these rigorous physical experiments. Through finite element analysis, an in-depth investigation of an aircraft equipped with a fabricated composite undercarriage was evaluated during water ditching. The severe impact of aircraft ditching is dynamic and nonlinear in nature; the goal of this work to develop a methodology that not only captures the structural response of the aircraft, but also the fluidic behavior of the water. Fundamental studies were first conducted on a well-researched fluid-solid interaction problem, the water entry of a wedge. Typical modeling strategies did not capture the desired detail of the event. An advanced meshing scheme combining meshed and meshless Lagrangian techniques was developed and multiple wedge angles were tested and compared to analytic and qualitative results. The meshing technique proved valid, as the difficult to model phenomena of splashing was captured and the maximum impact force was within five percent of analytical calculations for the 20° and 30° deadrise wedge. Physical small scale aircraft ditching experiments were then performed with an innovative testing platform capable of producing varied aircraft approach configurations. The model was outfitted with an instrumented composite undercarriage to record data throughout the impact while a high-speed camera recorded the event. Numerical simulations of the model aircraft were then compared to experimental results with a strong correlation. This methodology was then ultimately tested on a deformable model of a fuselage section of a full-size aircraft.
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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.

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Carbon composite reinforcement fabrics aimed at flight critical aircraft structure application were designed and the capability of the process used to manufacture them examined. Studies of the LIBA multiaxial non-crimp fabric manufacturing process focused on the effect of changes to four manufacturing parameters using an experimental design process to design the fabrics and analyse the results. The composite properties measured included microstructural features of the fibre tows and resin distribution, and mechanical performance both in-plane and their damage resistance and tolerance characteristics. Nine pairs of Toray T300 carbon based LIBA multiaxial non-crimp fabrics were manufactured and converted to composite laminates. Processing was accomplished using the interleaved Resin Film Infusion processing route with commercial Fiberdux 914 matrix resin. All the fabrics were of the same reinforcement type, consisting of 816 g/m2 of fibre; 376 g/m2 oriented along the fabric length (0°) and 220 g/m2 oriented in each of the ±45° directions. Differences between the nine pairs of fabrics were restricted to the settings of four manufacturing parameters; stitch course (needle penetrations/cm); stitch tension, 00 tension and 0° coverage (amount of constraint on the 0° material provided by the stitch). Three settings were used for each of the parameters; each representing the upper and lower limits, and standard setting. Microstructural characterisation of the laminates indicated large differences in both resin distribution and levels of 0° fibre crimp caused by the changes in manufacturing parameter settings. In-plane and damage resistance and tolerance tests on their composites allowed relationships between manufacturing settings, microstructure and engineering properties to be deduced. It was found that selected in-plane properties could be increased by as much as 17% relative to standard production materials, although a wide range of influence was observed. For damage resistance and tolerance characteristics, reductions in impact damage area (C-scan) of between 13-50% are expected across a range of energies. Manufacturing settings to maximise the impact force for delamination initiation were found to minimise the impact damage areas. Similarly the same settings maximised both the Mode I propagation strain energy release rate and the Compression After Impact strength of the materials. It was found that polyester knitting yarn was largely responsible for the control of the damage resistance and tolerance characteristics together with the mean size of the resin areas and layers within the composite. The manufacturing/microstructure/property relationships identified provide those wishing to exploit these materials with design guidelines to tailor fabric structure and performance characteristics for the intended application. Above all else the results highlight the need for precision in specifying and controlling the manufacturing process in order to repeatably produce the desired performance. Further work on the same materials could be used to provide a link to processing characteristics such as permeability for liquid resin moulding processes and ability to conform to complex curved surfaces.
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Xu, 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.

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This thesis presents a research project and results of design and optimization of a composite wing structure for a large aircraft in flying wing configuration. The design process started from conceptual design and preliminary design, which includes initial sizing and stressing followed by numerical modelling and analysis of the wing structure. The research was then focused on the minimum weight optimization of the /composite wing structure /subject to multiple design /constraints. The modelling, analysis and optimization process has been performed by using the NASTRAN code. The methodology and technique not only make the modelling in high accuracy, but also keep the whole process within one commercial package for practical application. The example aircraft, called FW-11, is a 250-seat commercial airliner of flying wing configuration designed through our MSc students Group Design Project (GDP) in Cranfield University. Started from conceptual design in the GDP, a high-aspect-ratio and large sweepback angle flying wing configuration has been adopted. During the GDP, the author was responsible for the structural layout design and material selection. Composite material has been chosen as the preferable material for both the inner and outer wing components. Based on the derivation of structural design data in the conceptual phase, the author continued with the preliminary design of the outer wing airframe and then focused on the optimization of the composite wing structure. Cont/d.
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Books on the topic "Composite aircraft structure"

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Chamis, C. C. Structural tailoring of select fiber composite structures. [Washington, D.C.]: NASA, 1990.

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Leite Cavalcanti, Welchy, Kai Brune, Michael Noeske, Konstantinos Tserpes, Wiesław M. Ostachowicz, and Mareike Schlag, eds. Adhesive Bonding of Aircraft Composite Structures. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-319-92810-4.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Repair of Aircraft Structures Involving Composite Materials. S.l: s.n, 1986.

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Dastin, Samuel J. Aircraft composite materials and structures: Seminar notes. Lancaster, PA: Technomic Publishing Co., 1986.

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Smith, Peter J. Damage tolerant composite wing panels for transport aircraft. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

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Renaud, Guillaume. Advanced optimal design concepts for composite material aircraft repair. [Downsview, Ont.]: University of Toronto, Institute for Aerospace Studies, 2003.

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Poon, C. A review of crashworthiness of composite aircraft structures. Ottawa: National Aeronautical Establishment, 1990.

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Development, Advisory Group for Aerospace Research and. The repair of aircraft structures involving composite materials. Neuilly-sur-Seine: Agard, 1986.

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Development, North Atlantic Treaty Organization Advisory Group for Aerospace Research and. Composite repair of military aircraft structures: Papers presented at the 79th Meeting of the AGARD Structures and Materials Panel, held in Seville, Spain 3-5 October 1994. Neuilly sur Seine, France: AGARD, 1995.

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Glossop, N. D. W. Optical fibre damage detection for an aircraft composite leading edge. [S.l.]: [s.n.], 1990.

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Book chapters on the topic "Composite aircraft structure"

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Barut, Silvere. "Sensitive Coating Solutions to Lower BVID Threshold on Composite Structure." In Smart Intelligent Aircraft Structures (SARISTU), 745–51. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_37.

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Saleem, M., Nishant Kumar Raj, Shreshth Gupta, and Yogesh Kumar. "Design and Analysis of Aluminium Matrix Composite Aircraft Wing Structure." In Lecture Notes in Mechanical Engineering, 53–60. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-6619-6_6.

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Tran, B., P. G. Ifju, M. M. Mennu, A. Brenes, and S. Shbalko. "Applying Macro Fiber Composite Patches to Morph Complex Aircraft Structure." In Mechanics of Composite, Hybrid and Multifunctional Materials , Volume 6, 99–106. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-59868-6_15.

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Venkatesh, S., S. C. Lakshminarayana, and Byji Varughese. "Integrity Evaluation of Feature Level Test Specimen of an Aircraft Primary Composite Structure." In Advances in Structural Integrity, 93–101. Singapore: Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-7197-3_8.

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Su, Weiguo, Lan Zou, Zhitao Mu, and Xudong Li. "Stress Analysis of Cracked Metallic Aircraft Structure Adhesively Repaired with Composite Patch." In Lecture Notes in Electrical Engineering, 369–77. Berlin, Heidelberg: Springer Berlin Heidelberg, 2014. http://dx.doi.org/10.1007/978-3-642-54233-6_41.

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Havar, Tamas, and Eckart Stuible. "Design and Testing of Advanced Composite Load Introduction Structure for Aircraft High Lift Devices." In ICAF 2009, Bridging the Gap between Theory and Operational Practice, 365–74. Dordrecht: Springer Netherlands, 2009. http://dx.doi.org/10.1007/978-90-481-2746-7_21.

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Choquet, Marc, René Héon, Christian Padioleau, Paul Bouchard, Christian Néron, and Jean-Pierre Monchalin. "Laser-Ultrasonic Inspection of the Composite Structure of an Aircraft in a Maintenance Hangar." In Review of Progress in Quantitative Nondestructive Evaluation, 545–52. Boston, MA: Springer US, 1995. http://dx.doi.org/10.1007/978-1-4615-1987-4_66.

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Kelly, Don W., Murray L. Scott, and Rodney S. Thomson. "Composite Aircraft Structures." In Modeling Complex Engineering Structures, 247–74. Reston, VA: American Society of Civil Engineers, 2007. http://dx.doi.org/10.1061/9780784408506.ch09.

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Gatewood, B. E. "Composite materials." In Virtual Principles in Aircraft Structures, 582–610. Dordrecht: Springer Netherlands, 1989. http://dx.doi.org/10.1007/978-94-009-1165-9_16.

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Harinarayana, Kota. "Design Approach to Composites in Fighter Aircraft: Current status." In Composite Structures, 1–19. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-662-11345-5_1.

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Conference papers on the topic "Composite aircraft structure"

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COT, LEA, SHUVAJIT MUKHERJEE, MISAEL MELGAR, and RANJAN GANGULI. "Aircraft Composite Structure Preventive Maintenance." In Structural Health Monitoring 2015. Destech Publications, 2015. http://dx.doi.org/10.12783/shm2015/282.

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Jonas, Paul, and Tom Aldag. "Certification of Bonded Composite Structure." In General Aviation Aircraft Meeting and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1987. http://dx.doi.org/10.4271/871022.

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Pugazhenthi, V., S. Gopalakannan, and R. Rajappan. "Finite Element Analysis of Composite Shell Structure of Aircraft Wing Using Composite Structure." In 2018 IEEE International Conference on System, Computation, Automation and Networking (ICSCAN). IEEE, 2018. http://dx.doi.org/10.1109/icscan.2018.8541192.

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Liu, X., and S. Mahadevan. "Failure probability of a composite aircraft wing structure." In 39th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-2048.

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Brunson, S., and M. Rais-Rohani. "A thin tailored composite wing box for a civil tiltrotor transport aircraft." In 37th Structure, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-1378.

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Soderquist, Joseph R. "Design/Certification Considerations in Civil Composite Aircraft Structure." In Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1987. http://dx.doi.org/10.4271/871846.

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Millwater, H., K. Griffin, D. Wieland, A. West, H. Smith, M. Holly, and R. Holzwarth. "Probabilistic analysis of an advanced fighter/attack aircraft composite wing structure." In 41st Structures, Structural Dynamics, and Materials Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-1567.

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BROWN, WILLIAM, and DARYL TIMMERMAN. "Benefits of composite structure for the tandem wing Advanced Technology Tactical Transport." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3167.

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Engelstad, Stephen P., Jason Action, Stephen B. Clay, Richard Holzwarth, Richard W. Dalgarno, and Don Robbins. "Assessment of Composite Damage Growth Tools for Aircraft Structure - Part I." In 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1876.

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Engelstad, Stephen P., and Stephen Clay. "Assessment of Composite Damage Growth Tools for Aircraft Structure Part II." In 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-0725.

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Reports on the topic "Composite aircraft structure"

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Hosur, Mahesh V., Shaik Jeelani, Uday K. Vaidya, and Sylvanus Nwosu. Survivability of Affordable Aircraft Composite Structures. Volume 2: High Strain Rate Characterization of Affordable Woven Carbon/Epoxy Composites. Fort Belvoir, VA: Defense Technical Information Center, April 2003. http://dx.doi.org/10.21236/ada421599.

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Hosur, Mahesh V., Shaik Jeelani, Uday K. Vaidya, Sylvanus Nwosu, and Ajit D. Kelkar. Survivability of Affordable Aircraft Composite Structures. Volume 1: Overview and Ballistic Impact Testing of Affordable Woven Carbon/Epoxy Composites. Fort Belvoir, VA: Defense Technical Information Center, April 2003. http://dx.doi.org/10.21236/ada421600.

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Hosur, Mahesh V., Shaik Jeelani, Uday K. Vaidya, and Ajit D. Kelkar. Survivability of Affordable Aircraft Composite Structures. Volume 3: Characterization of Affordable Woven Carbon/Epoxy Composites Under Low-Velocity Impact Loading. Fort Belvoir, VA: Defense Technical Information Center, April 2003. http://dx.doi.org/10.21236/ada421601.

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Roach, Dennis, and Thomas Rice. A Quantitative Assessment of Advanced NDI Techniques for Detecting Flaws in Composite Laminate Aircraft Structures. Office of Scientific and Technical Information (OSTI), August 2014. http://dx.doi.org/10.2172/1762097.

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Roach, D., and P. Walkington. Full-Scale Structural and NDI Validation Tests of Bonded Composite Doublers for Commercial Aircraft Applications. Office of Scientific and Technical Information (OSTI), February 1999. http://dx.doi.org/10.2172/4368.

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Matt, Howard M. Structural Diagnostics of CFRP Composite Aircraft Components by Ultrasonic Guided Waves and Built-In Piezoelectric Transducers. Office of Scientific and Technical Information (OSTI), January 2006. http://dx.doi.org/10.2172/899976.

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