Готові списки джерел за темами / Lightning strike to aircraft

Добірка наукової літератури з теми "Lightning strike to aircraft"

Автор: Grafiati
Опубліковано: 6 вересня 2023

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Статті в журналах з теми "Lightning strike to aircraft"

1

Yoshikawa, Eiichi, and Tomoo Ushio. "Tactical Decision-Making Support Information for Aircraft Lightning Avoidance: Feasibility Study in Area of Winter Lightning." Bulletin of the American Meteorological Society 100, no. 8 (August 2019): 1443–52. http://dx.doi.org/10.1175/bams-d-18-0078.1.

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AbstractDid you know that aircraft can cause lightning? Researchers began investigating aircraft-triggered lightning after several cases were observed of aircraft receiving lightning strikes from lightning-inactive clouds. The phenomenon of aircraft-triggered lightning was subsequently confirmed by a UHF radar, and today, it is known that most aircraft lightning strikes are aircraft triggered. However, aviation weather support for aircraft lightning avoidance has not been well developed. This is probably because aircraft lightning strikes have been somewhat avoided by using other information such as thunderstorm nowcasting, and have hardly ever caused serious accidents. In fact, today’s aircraft are designed, manufactured, and certified so as not to be seriously affected by lightning. In actual aircraft operations, however, lightning strikes can still cause minor damage to an aircraft’s body and instruments and result in time and expense being incurred by airlines to check for and repair any damage. Moreover, such checks and repairs can sometimes lead to the delay or cancellation of following services. Aircraft lightning strike is therefore recognized as an important issue in aviation weather. The Japan Aerospace Exploration Agency and Tokyo Metropolitan University carried out a feasibility study on providing tactical support information for aircraft lightning avoidance. In this study, weather and flight data were collected from actual cases of aircraft lightning strikes, and their analysis yielded information on trends regarding the relationship between aircraft lightning strikes and weather conditions. A prototype tactical support system was then developed based on the analyzed trends, and its evaluation showed that it could be used to avoid potentially 60%–80% of current aircraft lightning strikes.
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Bikkina, Siva Chakra Avinash, and P. V. Y. Jayasree. "Analysis of Electromagnetic Reflection Loss for Mesh Structure with A16061 MMC for Aerospace Applications." IOP Conference Series: Materials Science and Engineering 1206, no. 1 (November 1, 2021): 012021. http://dx.doi.org/10.1088/1757-899x/1206/1/012021.

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Abstract One of the major problems facing by the aircraft was a lightning strike. To overcome this problem, fiber-reinforced materials have been used. The fiber-reinforced materials have less conductivity. These fiber-reinforced materials can’t eliminate the lightning strike effect. For that purpose, the metal matrix composite materials significantly impacted the aircraft’s internal circuits and physical components from the lightning strike effect. To meet industries dynamic and ever-increasing demands, Al6061 metal matrix composite reinforced with fly ash must be utilized to build the aircraft to offer HIRF. The material thickness should be kept low as possible then it can be used to cover the plane’s surface. To prevent lightning strikes, it might be used to protect electronic components from a concentrated high-intensity radiated field, primarily in Aeroplan configuration. The electromagnetic characteristics of composites are measured using the X-band for normal incidence. The electromagnetic reflection properties of AL6061 reinforced with fly ash are studied in this study for mesh structure. Mat lab Software was used to calculate the maximum reflection loss of 33.88dB for 15% fly ash and 85 percent AL6061 at X-band.
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Katunin, Andrzej. "Lightning Strike Protection of Aircraft Composite Structures: Analysis and Comparative Study." Fatigue of Aircraft Structures 2016, no. 8 (June 1, 2016): 49–54. http://dx.doi.org/10.1515/fas-2016-0002.

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AbstractLightning strikes are a serious problem during operation of aircraft due to the increasing applicability of polymeric composites in aircraft structures and the weak electrical conducting properties of such structures. In composite structures, lightning strikes may cause extended damage sites which require to be appropriately maintained and repaired leading to increased operational costs. In order to overcome this problem various lightning strike protection solutions have been developed. Some of them are based on the immersion of metallic elements and particles while others use novel solutions such as intrinsically conductive polymers or other types of highly conductive particles including carbon nanotubes and graphene. The concept of fully organic electrically conductive composites based on intrinsically conductive polymers is currently being developed at the Silesian University of Technology. The results obtained in numerous tests, including concerning electrical conductivity and the capability to carry on high-magnitude electrical charges as well as certain operating properties need to be compared with existing solutions in lightning strike protection of aircraft. The following study presents the properties of the material developed for lightning strike protection and a comparative study with other solutions.
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Pecho, Pavol, Patrik Veľký, Martin Bugaj, and Daniel Kajánek. "Assessment of Aircraft Coating Resistance to Lighting Strikes and Long-Term Environmental Impact." Aerospace 10, no. 3 (March 10, 2023): 269. http://dx.doi.org/10.3390/aerospace10030269.

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Анотація:
During an aircraft’s flight through the atmosphere, the aircraft structure interacts with the surrounding environment. One of the potential hazards that can occur is a lightning strike to the structure covering. Subsequent damage to the aircraft covering may cause safety risks, so it must be removed. This paper describes a method of producing an electrical discharge that simulates the effect of lightning on metallic and non-metallic types of aircraft coverings upon which various types of paint coatings are applied. The electrical discharge hits the coating samples and, based on the material and type of paint used, causes damage. The coatings were later tested in a salt chamber according to STN ISO 9227:2017, and were photodocumented at various time intervals and subsequently analysed. The salt chamber test exposes the material to adverse conditions, which, in relation to the damaged coating, cause corrosion of the material, which depends on the extent of the damage and the type of material. The paper concludes that metallic aircraft coating samples allow less damage to aircraft coverings after a lightning strike, which is linked with less required maintenance associated with financial and time costs.
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Woo, Hee-chae, and Yong-Tae Kim. "Protection Design and Lightning Zone Analysis for Unmanned Aerial Vehicle with Composite Wings." Journal of the Korea Institute of Military Science and Technology 26, no. 3 (June 5, 2023): 302–12. http://dx.doi.org/10.9766/kimst.2023.26.3.302.

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This paper describes the analysis of lightning strike zoning, the indirect lightning data simulation and the protection design for lightning indirect effects of equipment by lightning strike for unmanned aircraft consisting of composite wings. Through the analysis of lightning strike zoning according to the external shape of unmanned aerial vehicles, the structure areas that should be protected during lightning strike is derived, and the protection requirements of lightning indirect effects for flight critical equipments and equipment that must be operated upon lightning strike was derived. Lightning protection levels according to the location of mounting equipment and surrounding structure materials for each equipment was derived, and the protection design of the unmanned aerial vehicle with composite structures was also proposed from direct effect of lightning. Later, the lightning protection technology will be verified by the ground test of lightning direct and indirect effects.
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Mazur, Vladislav, and Jean-Patrick Moreau. "Aircraft-triggered lightning - Processes following strike initiationthat affect aircraft." Journal of Aircraft 29, no. 4 (July 1992): 575–80. http://dx.doi.org/10.2514/3.46204.

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Bohne, Alan R., and Albert C. Chmela. "Storm structure during aircraft lightning strike events." Journal of Geophysical Research 91, no. D12 (1986): 13291. http://dx.doi.org/10.1029/jd091id12p13291.

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8

Liu, Zhi Qiang, Zhu Feng Yue, Fu Sheng Wang, and Yao Yao Ji. "Optimizations of Flame Spraying Aluminum Thickness and Laminate Plies for Composite Lightning Protection." Advanced Materials Research 915-916 (April 2014): 698–703. http://dx.doi.org/10.4028/www.scientific.net/amr.915-916.698.

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Анотація:
Anti-lightning strike protection for composite structures is catching great attention to design optimum lightning protection solution. Based on lightning direct effect, optimizations of flame spraying aluminum thickness and composite laminate plies were conducted by combining electrical-thermal analysis procedure and corresponding optimization programs. Optimized thickness was acquired for flame spraying aluminum layer. Meanwhile, non-uniform thick plies and optimized stacking angles were given for anti-lightning strike composite laminate. Comparisons were conducted to investigate changes of lightning direct effects on composite laminates fore and after optimization. Synergetic protections of flame spraying aluminum and laminate plies design were listed. The conclusions can be used as suggestions for lightning strike protection of advanced aircraft.
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Andraud, V., R. Sousa Martins, C. Zaepffel, R. Landfried, and P. Testé. "Development of a low voltage railgun in the context of a swept lightning stroke on an aircraft." Review of Scientific Instruments 93, no. 8 (August 1, 2022): 084705. http://dx.doi.org/10.1063/5.0085925.

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When aircraft are struck by lightning, the aircraft’s structural fuselage and components are stressed by electrical and thermo-mechanical constraints, which imposes a need for reliable experimental test benches to design accurate and enhanced lightning protection. In order to reproduce the in-flight conditions of an aircraft in a laboratory, the aim of this work is to design and implement launch equipment able to propel aeronautical test samples at speeds characteristic of an aircraft— from 10 m/s for ultra-light gliders to 100 m/s for airliners—before striking it with an electric arc within the laboratory dimensions of several meters. After a comparison of several propulsion techniques, the selected solution is an augmented electromagnetic railgun launcher. Since it requires the injection of a high current to be efficient and a low voltage operative point for safety considerations, specific and original electric generator and rail structures have been designed and experimentally implemented. Particular attention has been paid to the experimental problems encountered and mainly the sliding contact, since almost no literature references are available for railgun equipment at this level of performance. Then, based on different experimental implementations, a dynamic and ballistic model of the projectile has been developed to evaluate and characterize friction forces with the aim of predicting launcher performances with different inputs. This serves to control the speed of the material test sample during the lightning strike. Finally, the railgun equipment has been coupled to a lightning generator to reproduce the lightning strike of an aircraft respecting in-flight conditions.
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Lesiuk, Igor, and Andrzej Katunin. "Numerical analysis of electrically conductive fillers of composites for aircraft lightning strike protection." Aircraft Engineering and Aerospace Technology 92, no. 10 (July 23, 2020): 1441–50. http://dx.doi.org/10.1108/aeat-01-2020-0003.

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Purpose This paper aims to present a numerical analysis and comparison of two types of conductive fillers of polymeric composites subjected to lightning strikes. Design/methodology/approach Two types of conductive fillers were considered in the developed numerical models of electrically conductive composites: carbon nanotubes and polyaniline. For these fillers, the representative volume elements were developed to consider distribution of the particles that ensures percolation and homogenization of the materials within the Eshelby-based semi-analytical mean-field homogenization approach. The performed numerical analyses allowed determination of effective volume fractions of conducting particles, resistivity and conductivity tensors, and finally the current density for the simulated materials subjected to lightning strike. Findings The obtained results allowed for comparison of electrical conductivity of two simulated materials. It was observed that besides fair results obtained in the previous studies for intrinsically conducting polymers as fillers of composites dedicated for lightning strike protection, the composites filled with carbon nanotubes reveal much better conductivity. Practical implications The presented simulation results can be considered as initial information for further experimental tests on electrical conductivity of such materials. Originality/value The originality of the paper lies in the proposed design and simulation procedures of conductive composites as well as the comparison of selected composites dedicated for lightning strike protection as the most intensively developed materials for this purpose.
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Більше джерел

Дисертації з теми "Lightning strike to aircraft"

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Mouratidis, Theodore. "Aircraft charging using ion emission for lightning strike mitigation : an experimental study." Thesis, Massachusetts Institute of Technology, 2019. https://hdl.handle.net/1721.1/122708.

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Анотація:
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2019
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 96-97).
Lighting strikes are a problem for aircraft flying in large external electric fields. In most cases, the strike is triggered by the aircraft; as it flies through an electric field, it becomes polarized, and on areas with small radius of curvature, the electric field is magnified. This can result in bidirectional leaders which extend from opposite polarity aircraft extremities. These can connect to oppositely charged regions in a cloud or the ground, resulting in a lightning strike. Current methods to avoid lightning are limited to avoiding thunderstorm regions, as recommended by weather radar or conversations between pilots and the ground. Methods to treat the symptom of a strike have been relatively successful; a mesh placed under the skin of the aircraft can distribute the current and heat of the localized strike. However, there are currently no active measures to prevent the strike from happening.
The Boeing Lightning Strike team at MIT has recently proposed an active system that exploits the physics of how a lightning arc is triggered from an aircraft in flight based on net charge control of the vehicle. The objective of this thesis is to prove the feasibility of controlling the net charge of an aircraft in flight by using ion emission from its surface. Different strategies to control the net charge of a flying isolated body were explored and analyzed. The first strategy tested was based on using charge emission from an electrospray source. A passive flow and forced flow configuration were tested, however it was shown that there were numerous difficulties associated with running the electrosprays in atmospheric pressure. To overcome the limitations of the electrospray source, a second strategy was tested based on a controlled corona discharge, which is known to have increasing current emission with increasing wind speed.
The first experiment was setup in the Wright Brothers Wind Tunnel; sharp tips were used to generate a corona discharge and a metallic sphere was used to simulate the aircraft. Significant electrical potential saturation was observed on the sphere, and it is likely this was due to the filamentary streamer corona regime which produces both positive and negative ions. Thus a new experiment was designed; a thin wire was used to generate a glow corona, which produces predominantly positive ions, and this was attached using GlO (a fiberglass composite material) to a metallically coated airfoil. Charging of much higher magnitudes was observed, indicating the glow corona regime is critically important in optimizing the potential of the airfoil. Charge control of an airfoil (Chord 0.2 m, Span 1 m) at 40 m/s was demonstrated to a level of -42 kV.
For an object of a given characteristic size, a certain amount of charge is required to satisfy the optimal charge condition, where negative and positive leader strikes are both equally likely or unlikely. The achieved potential of -42 kV is the order of magnitude required for this size airfoil based on the theoretical estimates, and these tests also showed a trend of linear potential variation with wind speed.
"Boeing Company for financially supporting my Research Assistantship"
by Theodore Mouratidis.
S.M.
S.M. Massachusetts Institute of Technology, Department of Aeronautics and Astronautics
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2

Zhang, Bangwei. "Manufacturing, characterization, and modeling of graphene-based nanocomposites for aircraft structural and lightning strike applications." Diss., Wichita State University, 2012. http://hdl.handle.net/10057/5591.

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Research and development of graphene and graphene-based materials have been attracting significant interest since they were invented. This dissertation mainly focused on the graphene-based materials: (a) a fundamental understanding of nanosize functionalized graphene inclusions in resin and fiber systems, (b) the development of graphene based hierarchical nanocomposites incorporated with thin layers of graphene papers, and carbon and glass fibers, and (c) the mathematical modeling of a process that can be useful for aircraft and wind turbine applications. Dispersion, wet layup, and vacuum-assisted resin transfer molding (VARTM) processes were used in the fabrication process, and then mechanical, thermal, electrical, and electromagnetic interference (EMI) properties of the materials were characterized using various techniques. Results of experiments conducted at different concentrations, thicknesses, pressures, and types of reinforcement materials show that the graphene-based fiber composites provided substantially better physical properties than other conventional carbon and glass-fiber-reinforced composites because of the extraordinary physical properties of graphene nanoflakes, rate of dispersion, and stronger covalent bonding between the resin and the reinforcement systems. MESOTEX (MEchanical Simulation of TEXtile) was utilized to predict the bulk-scale elastic modulus of the graphene-based fiber-reinforced composites. Graphene nanoflakes are assumed to be randomly and homogenously distributed in Epon 862 epoxy resin. Halpin-Tsai theories/equations were first used to simulate the tensile modulus of two phase graphene-based polymeric nanocomposites; however, today’s nanocomposite materials have three-phase structures. MESOTEX modeling results on variable laminate composite geometries confirmed that this modeling had a good prediction on a three-phase nanocomposite system and the test results indicated the existence of agglomeration effects on the properties of nanocomposites.
Thesis (Ph.D.)--Wichita State University, College of Engineering, Dept. of Mechanical Engineering
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Ashok, Kumar Sachin Sharma. "Incorporation of graphene thin films into the carbon fiber reinforced composite via 3d composite concept against the lightning strikes on composite aircraft." Thesis, Wichita State University, 2012. http://hdl.handle.net/10057/5592.

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Research and development of graphene and graphene based materials have been increasing significantly since they were invented. This report presents the development of a highly conductive graphene thin film (GTF) to reduce the damage of lightning effects on composite aircrafts. Furthermore, there are three new developments that are presented in this research: (a) the development of a highly conductive functionalized nanosize GTF, (b) a new approach of incorporating the GTF into the carbon fiber reinforced composite panel, and (c) a new development of 3D stitching concept were introduced specifically using polyester threads instead of fiber yarns that can be useful for the applications of aircraft protections against the effects of lightning strike. In addition, graphene was chemically functionalized and oxidized to form GTF. The highest electrical conductivity measured on the GTF was approximately 1800 S/cm. Furthermore, the GTF was then incorporated into the carbon fiber reinforced composite. Delamination was observed between the GTF and the composite. To investigate this issue, the composite was mechanically tested and there was a 40% decrease in tensile strength compared to the baseline. Therefore, 3D stitching concept was then introduced to reduce the delamination. Four stitch configurations having different stitch length, thread to thread thickness, thread tension, and thread thickness respectively were used in this study. 3D stitching was initially done on six sheets of unidirectional prepreg, MTM45-1 without the incorporation of GTF. Furthermore, mechanical testing was carried out and the stitch configuration that delivered the most appropriate result was then further used on twelve sheets of unidirectional prepreg, 5320. Here, three samples which was the baseline, 5320 with and without the incorporation of GTF respectively were prepared and mechanically tested, and the strength values were observed.
Thesis (M.S.)--Wichita State University, College of Engineering, Dept. of Mechanical Engineering
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4

Wan, Ahmad Wan Fatinhamamah. "Modelling of lightning strike on an earth ground conductor." Thesis, University of Nottingham, 2007. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.438449.

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5

Lee, Steve H. K. "Route optimization model for strike aircraft." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1995. http://handle.dtic.mil/100.2/ADA306230.

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Mastrolembo, Giuseppe. "Understanding and optimising parameters for lightning strike testing of CFRP materials." Thesis, Cardiff University, 2017. http://orca.cf.ac.uk/113125/.

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In this thesis experimental tests and numerical simulations were carried out on the effects of the grounding system on CFRP test samples for the aerospace industry. The grounding system was assessed as one of the parts that can contribute to increasing the cost effectiveness of the sample and the relative test campaign. A numerical investigation was performed to understand the current distribution within anisotropic CFRP laminates. The influence of the grounding system and the interlaminar impedance on the current distribution were studied using parametric simulations and the results were compared. It was found that the side grounding system produces the best performance between the arrangements investigated. It allows for the best current spreading within the sample and for the lowest voltage drop between the injection and grounding points. Furthermore, it allows for the manufacturing of more cost effective test samples. However, a real implementation of the side grounding system introduces the contact pressure variable between the sample and the grounding electrode which influences the contact resistance. To implement the side grounding system, a test rig was designed and manufactured. This made it possible to control the compression force. A low current DC test campaign was carried out on five test samples with the same number of grounding systems. It was found that the contact resistance for the three side grounding systems is dependent on the compression force applied between the grounding electrode and the side of the sample. The influence was more pronounced for the sample without any metal coating on the side in contact with the electrode. Furthermore, the resistances measured for the two side grounding systems with metalized sides were comparable with the resistances measured for the fastener grounding systems. It was found in the literature that the variation of contact resistance due to compression force, for the side grounding cases, is related to variations in the topography of the surfaces in contact, specifically, the variations in the real contact area. Therefore, an investigation on the effects of the compression force on the surfaces in contact was carried out. It was found that the increase in compression force contributes to the decrease in the roughness mean; the increase in the material ratio curve which is a parameter related to the load bearing area; and the modification of the distribution of the height of the surfaces with the appearance of a negative tail. Further to the low current tests and the characterization of the surfaces of the side grounding samples a high current test campaign was performed. Through the use of typical lightning current waveforms, the thermal and electrical limits of the five grounding systems were investigated. The side grounding systems were tested at the maximum compression force to improve the contact area between the sample and the return electrode and therefore, decrease the risk of the sparking phenomena. The side grounding system paired with the sample with the metal sputtered side showed the best performance in terms of sustaining the highest current peak without appreciably increasing the risk of sparking phenomena at the contact interface between the sample and the IV return electrode. Conversely, the sample without any metal coating on its side showed the poorest performance, showing the sparking phenomena at the lowest current peak. The results of the thermal investigation were used for a visual validation of the numerical model created in the first part of the thesis. A comparison between a numerical model and an analytical model was performed. The dynamics of the temperature when a carbon fibres tow is subjected to a lightning current and thus to Joule effects were studied. The analytical model had the advantage of offering a simpler solution compared to the numerical model and a limited amount of data to input into the problem. The two models were found to produce similar results for the first transient of the temperature. However, the analytical model did not take into account the heat dissipation effects of the carbon fibres in the surrounding environment therefore, after the first transient the analytical model was found not to be as accurate as the numerical model.
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Ericsson, Max. "Simulating Bird Strike on Aircraft Composite Wing Leading Edge." Thesis, KTH, Hållfasthetslära (Inst.), 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-103783.

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In this master thesis project the possibility to model the response of a wing when subjected to bird strike using finite elements is analyzed. Since this transient event lasts only a few milliseconds the used solution method is explicit time integration. The wing is manufactured using carbon fiber laminate. Carbon fiber laminates have orthotropic material properties with different stiffness in different directions. Accordingly, there are damage mechanisms not considered when using metal that have to be modeled when using composites. One of these damage mechanisms is delamination which occurs when cured layers inside a component become separated. To simulate this phenomenon, multiple layers of shell elements with contact in between are used as a representation of the interface where a component is likely to delaminate. By comparing experimental and simulated results the model of delamination is verified and the influence of different parameters on the results is investigated. Furthermore, studies show that modeling delamination layers in each possible layer of a composite stack is not optimal due to the fact that the global stiffness of the laminate is decreased as more layers are modeled. However, multiple layers are needed in order to mitigate the spreading of delamination and obtain realistic delaminated zones. As the laminates are comprised of carbon fiber and epoxy sheets it is of importance to include damage mechanisms inside each individual sheet. Accordingly, a composite material model built into the software is used which considers tensile and compressive stress in fiber and epoxy. The strength limits are then set according to experimental test data. The bird is modeled using a mesh free technique called Smooth Particle Hydrodynamics using a material model with properties similar to a fluid. The internal pressure of the bird model is linked to the change in volume with an Equation of State. By examining the bird models behavior compared to experimental results it is determined to have a realistic impact on structures. A model of the leading edge is then subjected to bird strike according to European standards. The wing skin is penetrated indicating that reinforcements might be needed in order to protect valuable components inside the wing structure such as the fuel tank. However, the results are not completely accurate due to the fact that there is little experimental data available regarding soft body penetration of composite laminates. As a consequence, the simulation cannot be confirmed against real experimental results and further investigations are required in order to have confidence in modeling such events. Furthermore, the delamination due to the bird strike essentially spreads across the whole model. Since only one layer of delamination is included the spread is most likely overestimated.
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8

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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Анотація:
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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9

Callahan, Jeremy. "Metrics of METOC forecast performance and operational impacts on carrier strike operations." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2006. http://library.nps.navy.mil/uhtbin/hyperion/06Sep%5FCallahan.pdf.

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Thesis (M.S. in Meteorology and Physical Oceanography)--Naval Postgraduate School, September 2006.
Thesis Advisor(s): Tom Murphree, Rebecca Stone. "September 2006." Includes bibliographical references (p. 61-62). Also available in print.
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Tedrow, Christine Atkins. "Bird Strike Risk Assessment for United States Air Force Airfields and Aircraft." Thesis, Virginia Tech, 1998. http://hdl.handle.net/10919/40926.

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Analysis of strike data is critical to determine the true economic costs of bird strikes, determine the magnitude of safety issues, and develop preventive measures. Analysis of USAF bird-strike data identified trends and indicated suggested relationships among factors contributing to damaging strikes. From FY 1988 through FY 1997, the annual mean was 2,668 bird strikes with peaks evident in fall and spring. Daylight and dusk were hazardous for bird strikes. More bird strikes occurred during airfield operations - aircraft are at low altitudes and soaring birds are more numerous. Aircraft speed, phase of flight, taxonomic group, bird mass and aircraft group were the strongest predictors of damaging bird strikes. Bird strike rates were calculated for USAF aircraft and selected USAF airfields. Bomber aircraft had the highest strike rate; these aircraft frequently fly long missions at low altitudes where they are likely to encounter birds. Logistic regression analyses estimated odds of occurrence for damaging bird strikes during airfield operations. General statistics, odds for a damaging airfield strike, and airfield strike rates, were used to identify USAF airfields with higher bird strike risks. Howard AFB, Panama, had a higher number and rate of bird strikes, and greater odds for a damaging bird strike than other airfields analyzed. This study allows recommendations for improving reporting of bird strikes and data management. Results will enable USAF to better estimate bird strike risks aircraft, better focus research on preventing bird strikes, and assess the effectiveness of bird management programs.
Master of Science
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Книги з теми "Lightning strike to aircraft"

1

R, Bohne Alan. Storm precipitation and wind structure during aircraft strike lightning events. Hanscom AFB, MA: Atmospheric Sciences Division, Air Force Geophysics Laboratory, 1985.

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Bohne, Alan R. Storm precipitation and wind structure during aircraft strike lightning events. Hanscom AFB, MA: Atmospheric Sciences Division, Air Force Geophysics Laboratory, 1985.

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3

Strike aircraft. Toronto: Bantam Books, 1988.

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4

Why does lightning strike? London: Dorling Kindersley, 1996.

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5

Copyright Paperback Collection (Library of Congress), ed. Recon force: Lightning strike. New York, NY: Kensington Pub. Corp., 2003.

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6

Paine, Lauran. Lightning Strike: A western duo. Waterville, Me: Five Star, 2012.

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7

Chancellorsville 1863: Jackson's lightning strike. Westport, Conn: Praeger, 2004.

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8

Center, Langley Research, ed. 1983 direct strike lightning data. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

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9

K, Carney Harold, and Langley Research Center, eds. 1984 direct strike lightning data. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1986.

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10

Young-Stone, Michele. The handbook for lightning strike survivors. Waterville, Me: Wheeler Pub., 2010.

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Частини книг з теми "Lightning strike to aircraft"

1

Soykasap, Omer, Sukru Karakaya, Yelda Akcin, and Mehmet Colakoglu. "Finite Element Modelling of CNT-Doped CFRP Plates for Lightning Strike Damage." In Smart Intelligent Aircraft Structures (SARISTU), 825–37. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_44.

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2

Davis, James W., Dana Forman, La Scienya M. Jackson, James W. Davis, Javier Garau, David N. O’Dwyer, Elisa Vedes, et al. "Lightning Strike." In Encyclopedia of Intensive Care Medicine, 1331. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-00418-6_1830.

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Miller, Christopher W. "Getting Lightning to Strike." In The PDMA Handbook of New Product Development, 135–53. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2013. http://dx.doi.org/10.1002/9781118466421.ch8.

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4

Holstege, Christopher P. "Lightning Strike Induced Skin Changes." In Visual Diagnosis in Emergency and Critical Care Medicine, 74. Oxford, UK: Wiley-Blackwell, 2011. http://dx.doi.org/10.1002/9781444397994.ch110.

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Hooijmeijer, P. A. "Burn-through and lightning strike." In Fibre Metal Laminates, 399–408. Dordrecht: Springer Netherlands, 2001. http://dx.doi.org/10.1007/978-94-010-0995-9_26.

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6

Jiang, Haiyan, and Zhuoran Liu. "Lightning Rod in Power Transmission Line against the Strike of Detour Lightning." In Communications in Computer and Information Science, 210–13. Berlin, Heidelberg: Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-25002-6_29.

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7

Hartnett, David, and Colin G. Kaide. "Lightning Strike: Thunderbolts and Lightning, Very, Very Frightening…The Cosmic DC Countershock." In Case Studies in Emergency Medicine, 329–39. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-22445-5_33.

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Fisher, Joseph, Paul R. P. Hoole, Kandasamy Pirapaharan, and Samuel R. H. Hoole. "Lightning Electrodynamics: Electric Power Systems and Aircraft." In Lightning Engineering: Physics, Computer-based Test-bed, Protection of Ground and Airborne Systems, 233–88. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-94728-6_7.

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Smetankina, Natalia, Igor Kravchenko, Vyacheslav Merculov, Dmitry Ivchenko, and Alyona Malykhina. "Modelling of Bird Strike on an Aircraft Glazing." In Integrated Computer Technologies in Mechanical Engineering, 289–97. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-37618-5_25.

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10

Kasemir, H. W. "Airborne Warning Systems for Natural and Aircraft-Initiated Lightning." In Heinz-Wolfram Kasemir: His Collected Works, 663–84. Washington, D. C.: American Geophysical Union, 2013. http://dx.doi.org/10.1002/9781118704813.ch52.

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Тези доповідей конференцій з теми "Lightning strike to aircraft"

1

Massa, Travis. "Post Lightning Strike Inspection." In Vertical Flight Society 75th Annual Forum & Technology Display. The Vertical Flight Society, 2019. http://dx.doi.org/10.4050/f-0075-2019-14663.

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Inspecting an aircraft after a known or suspected lightning strike can be a tedious and subjective task. While aircraft technical manuals do provide conditional inspections following a lightning strike, these inspections tend to be broad in their approach and based solely on the presence of visual damage. This paper discusses the simple technique of tracing the lightning path through the aircraft by the use of an analog magnetometer to identify ferromagnetic parts that have been magnetized by the substantial electrical current of a lightning strike. While this technique is not novel, it is not often published as an inspection technique. Knowing the approximate path of the lightning can assist aircrews and maintainers in the identification of suspect parts that may require further inspection, repair and/or replacement thereby increasing safety and ensuring continued airworthiness of the aircraft.
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Evans, Simon, Ivan Revel, Matthew Cole, and Richard Mills. "Lightning strike protection of aircraft structural joints." In 2014 International Conference on Lightning Protection (ICLP). IEEE, 2014. http://dx.doi.org/10.1109/iclp.2014.6973447.

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Bollavaram, Praveen K., Muhammad M. Rahman, and R. Asmatulu. "Lightning Strike Protection and EMI Shielding of Fiber Reinforced Composite Using Gold and Silver Nanofilms." In ASME 2018 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/imece2018-88639.

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Carbon fiber reinforced composites are very much imperative to future-generation aircraft structures. However, lightning strike protection (LSP) and electromagnetic interference (EMI) are main concerns. Carbon fibers have very good mechanical properties with the best strength-to-weight ratio, but they are very poor conductors of electricity. These fibers must be reinvented to increase the surface conductance to provide high electrical conductivity to the aircraft structure. The present study deals with preparing composite sandwich structures of carbon fibers used for commercial nacelle applications subject to lightning strike effects with different metallic nanofilm of gold (Au) and silver (Ag) measuring approximately 100 nm. These metallic nanofibers were co-cured on the top layers of composite panels during vacuum curing process. In our laboratory, lightning strike results for a composite sandwich structure using nanofilms were obtained to observe lightning strike damage and structural tolerance necessary to observe the damage tolerance capability. Resistance of composite panels with metallic nanofilm under various strains was studied. It was found that resistance of the metallic nanofilm increased under strain. The voltage was found to be low; hence, an increase in current would help to reduce the damage on composite panels due to lightning strikes, and the same theory would be applicable to EMI. No EMI was absorbed or reflected in the nanofilm using the P-static test. When lightning strikes were applied to composite coupons, the resulting damage from the currents was reduced on those with metallic nanofilms.
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MANOMAISANTIPHAP, SIWAT, and TOMOHIRO YOKOZEK YOKOZEKI. "EFFECTS OF NUMBER OF PLIES ON LIGHTNING STRIKE PROTECTION OF ELECTRICALLY CONDUCTIVE LAYER-WISE HYBRID LAMINATES." In Thirty-sixth Technical Conference. Destech Publications, Inc., 2021. http://dx.doi.org/10.12783/asc36/35908.

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With the development of composite technologies, aircraft become lighter and more fuel efficiency. The composite aircraft, however, become susceptible to lightning strike. Developing lightning strike protection (LSP) system need to couple with composite technologies. The authors present a concept of LSP using layer-wise hybrid laminates (CF/Hybrid) in this study. The aim of the study is to validate the effectiveness of layer-wise hybrid laminates structure for lightning strike application by using conventional epoxy-resin CFRP for main structure and electrically conductive layer as a cover layer. The composite laminates include two different types of resin in each layer: conductive polyaniline-based matrix (CF/PANI) and conventional epoxy resin (CF/epoxy). CF/PANI layers varied from 1, 2, and 4 layers with corresponding 7, 6, and 4 layers of CF/epoxy to find out the least effective number of CF/PANI that can prevent lightning strike damage. The specimens were characterized for their mechanical properties and underwent simulated lightning strike test to realize their effectiveness. The result of simulated lightning strike has shown that a layer of conductive CF/PANI can help to avoid catastrophic damage on CF/epoxy. With a greater number of CF/PANI, the less detectable damage in CF/PANI layer became. In the case of CF/Hybrid with 4 layers of CF/PANI shows 70% residual bending strength after the lightning strike. With the aid of nondestructive inspection tools, i.e., thermography and ultrasonic test, the mechanism of damage on the composite panels were observed and analyzed. From this study, CF/Hybrid with 4 layers shows the optimal properties for lightning strike protection.
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BOUSHAB, DOUNIA, KHARI HARRISON, ANIKET MOTE, THOMAS E. LACY, JR., and CHARLES U. PITTMAN, JR. "EXPERIMENTAL STUDY OF LIGHTNING DAMAGE RESISTANCE OF UNPROTECTED AND PROTECTED STITCHED WARP-KNIT CARBON-EPOXY COMPOSITES." In Thirty-sixth Technical Conference. Destech Publications, Inc., 2021. http://dx.doi.org/10.12783/asc36/35743.

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In-flight lightning strike damage to aircraft composite structures may compromise aircraft airworthiness. Hence, it is crucial to incorporate adequate protection systems to mitigate the lightning current. Most lightning strike protection (LSP) techniques involve bonding a metallic conductive layer to the cured laminate exterior. In this study, a novel LSP integration technique was used to develop unitized panels with three different protection layers: pitch carbon fiber paper (PCFP), graphene paper (GP), and copper mesh (CM). Each LSP layer was overlaid on through-the-thickness VectranHT stitched warp-knit multiaxial dry carbon fabric stacks, resin-infused, and oven-cured. A series of lightning strike tests to protected and unprotected stitched carbonepoxy laminates were conducted at a nominal peak current of 150 kA. Visual inspection was used to investigate each panel’s lightning damage resistance, understand the damage mechanisms, and evaluate the surface morphology at the strike locations. The size and severity of the damaged area depended on several factors: the outermost ply fiber direction, the strike location relative to VectranHT and polyester knitting treads, the lightning peak current, and the conductivity of the protection layers. The CM and GP protection layers effectively dissipated the lightning current in-plane and showed no damage to the underlying composite. The degree of lightning damage on an unprotected laminate was significantly lower than for a similar panel with PCFP protection. The presence of VectranHT structural stitches and polyester warp-knitting threads profoundly reduced the size and severity of lightning damage. These threads appeared to promote close contact between adjacent carbon fiber tows, resulting in better in-plane and through-thickness electrical/thermal conductivities and reduced lightning damage.
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Pridham, Barry, Dieter Jaeger, and Manfred Schreiner. "Integral Lightning Strike Protection of CFC Fuel Tanks on Aircraft." In International Conference on Lightning and Static Electricity. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2001. http://dx.doi.org/10.4271/2001-01-2912.

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Odam, Pamela J. "UK Military Aircraft Lightning Strike Reporting Over the Last 50 Years." In International Conference on Lightning and Static Electricity. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2001. http://dx.doi.org/10.4271/2001-01-2887.

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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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Artemiev, Igor V., Rustam R. Gaynutdinov, and Sergey F. Chermoshentsev. "Aircraft Control System Immunity Study at the Direct Lightning Strike." In 2018 19th International Conference of Young Specialists on Micro/Nanotechnologies and Electron Devices (EDM). IEEE, 2018. http://dx.doi.org/10.1109/edm.2018.8435064.

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Gozluklu, Burak, Gulsen Oncul, and Ugur Koseoglu. "Design Concept of a CFRP External Trailing Edge for Ailerons." In ASME 2013 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/imece2013-66066.

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The most recent civil aircraft dominantly use composite structures such as in the ailerons. However, airworthiness authorities raise concerns about lightning strike damage and repairability if the aileron is made of composite material. Today, aerodynamic profiles of aircraft wings become more complex and challenging for designers who need adequate space to fit conventional “torque box” designs inside the wing surfaces. The aero-surfaces may become too shallow and curved in the trailing edge side of the wing which is highly exposed to edge impact and lightning strike damages. This paper presents a new design concept for Carbon Fiber Reinforced Plastic (CFRP) External Trailing Edge (CETE) structure for the trailing edge of the ailerons. CETE is attached to the main aileron torque box where the main load carrying composite spar, ribs and panels are located. The design objective of the CETE combines various important features such as better strength characteristics against lightning strike and edge impact, and easier repairability with a lighter aileron. This paper also discusses recurring and non-recurring costs and monetary benefits of the new design concept. The CETE concept is as simple as creating a secondary torque box on the trailing edge side of the aileron with two C-section parts; inner and outer parts of CETE. The inner part of CETE provides a secondary spar to the aileron to sustain the main torque box force flows and support the trailing edge panels. The main structural feature of CETE is to form a low loaded zone by its outer part which is located at the outermost region of the trailing edge where mechanical edge impact and lightning strike damages are frequently encountered. It is revealed during the lightning strike tests that, the resulting damages can be catastrophic and located at the trailing edge line where the metallic strips are located. In case of lightning strike damage on the CETE, the aileron is able to carry loads since the flows in the main torque box is minimally disturbed as the inner part of CETE is still intact while the outer part is damaged. Similarly, the damage after edge impact is trapped at the outer section of the CETE where the loads are minimized by CETE design. In case of a larger damage, CETE can be replaced easily instead of replacing the whole aileron which is cost effective in long term although the initial costs seem higher than the conventional designs.
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Звіти організацій з теми "Lightning strike to aircraft"

1

Gruden, James M., Lawrence C. Walko, Daniel L. Schweickart, John C. Horwath, and Gary L. Webb. Analysis of Simulated Aircraft Lightning Strikes and Their Electromagnetic Effects. Fort Belvoir, VA: Defense Technical Information Center, February 2001. http://dx.doi.org/10.21236/ada387342.

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Bond, C. D., F. J. Campbell, and D. P. Smith. Lightning Strike Tests of Composite Connectors. Fort Belvoir, VA: Defense Technical Information Center, June 1992. http://dx.doi.org/10.21236/ada252281.

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NOBLE, STEPHEN. LIGHTNING STRIKE PREDICTION AT THE SAVANNAH RIVER SITE. Office of Scientific and Technical Information (OSTI), July 2022. http://dx.doi.org/10.2172/1878527.

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Marrs, Frank. National Lightning Detection Network: Summary of Strike Peak Currents. Office of Scientific and Technical Information (OSTI), March 2021. http://dx.doi.org/10.2172/1771070.

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Dinallo, M. S., and R. J. Fisher. Voltages across assembly joints due to direct-strike lightning currents. Office of Scientific and Technical Information (OSTI), August 1994. http://dx.doi.org/10.2172/10190346.

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Uman, M., V. Rakov, J. Elisme, D. Jordan, C. Biagi, and J. Hill. Update Direct-Strike Lightning Environment for Stockpile-to-Target Sequence. Office of Scientific and Technical Information (OSTI), October 2008. http://dx.doi.org/10.2172/945839.

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Fisher, R. J., and M. A. Uman. Recommended baseline direct-strike lightning environment for stockpile-to-target sequences. Office of Scientific and Technical Information (OSTI), May 1989. http://dx.doi.org/10.2172/6245291.

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Bogdan, Christopher. F-35 Joint Strike Fighter Aircraft (F-35). Fort Belvoir, VA: Defense Technical Information Center, November 2015. http://dx.doi.org/10.21236/ad1019428.

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Uman, Martin A., V. A. Rakov, J. O. Elisme, D. M. Jordan, C. J. Biaji, and J. D. Hill. Update Direct-Strike Lightning Environment for Stockpile-to-Target Sequence (Second Revision). Office of Scientific and Technical Information (OSTI), October 2010. http://dx.doi.org/10.2172/1124903.

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SECRETARY OF THE AIR FORCE WASHINGTON DC. U.S. Air Force Long-Range Strike Aircraft White Paper. Fort Belvoir, VA: Defense Technical Information Center, November 2001. http://dx.doi.org/10.21236/ada433970.

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