Artykuły w czasopismach: „Lightning strike to aircraft”

1

Yoshikawa, Eiichi, i 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, nr 8 (sierpień 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, i 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, nr 1 (1.11.2021): 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, nr 8 (1.06.2016): 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 i Daniel Kajánek. "Assessment of Aircraft Coating Resistance to Lighting Strikes and Long-Term Environmental Impact". Aerospace 10, nr 3 (10.03.2023): 269. http://dx.doi.org/10.3390/aerospace10030269.

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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, i 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, nr 3 (5.06.2023): 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, i Jean-Patrick Moreau. "Aircraft-triggered lightning - Processes following strike initiationthat affect aircraft". Journal of Aircraft 29, nr 4 (lipiec 1992): 575–80. http://dx.doi.org/10.2514/3.46204.

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Bohne, Alan R., i Albert C. Chmela. "Storm structure during aircraft lightning strike events". Journal of Geophysical Research 91, nr D12 (1986): 13291. http://dx.doi.org/10.1029/jd091id12p13291.

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

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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 i P. Testé. "Development of a low voltage railgun in the context of a swept lightning stroke on an aircraft". Review of Scientific Instruments 93, nr 8 (1.08.2022): 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, i Andrzej Katunin. "Numerical analysis of electrically conductive fillers of composites for aircraft lightning strike protection". Aircraft Engineering and Aerospace Technology 92, nr 10 (23.07.2020): 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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Ostermann, Markus, Juergen Schodl, Peter A. Lieberzeit, Pierluigi Bilotto i Markus Valtiner. "Lightning Strike Protection: Current Challenges and Future Possibilities". Materials 16, nr 4 (20.02.2023): 1743. http://dx.doi.org/10.3390/ma16041743.

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An airplane is statistically struck by lightning every year. The need for lightweight aircraft to reduce the production of carbon dioxide has significantly reduced the presence of metals in favour of composites, resulting in lower lightning strike protection efficiency. In this perspective, we critically review the state of technologies in lightning strike protection solutions based on carbon materials, graphene, and MXenes. Furthermore, we comment on possible future research directions in the field.

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Das, Sayantan, i Udaya Kumar. "Modeling of Bi-Polar Leader Inception and Propagation from Flying Aircraft Prior to a Lightning Strike". Atmosphere 13, nr 6 (9.06.2022): 943. http://dx.doi.org/10.3390/atmos13060943.

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Lightning is one of the major environmental threats to aircraft. The lightning strikes during flying are mostly attributed to aircraft-triggered lightning. The first step toward designing suitable protective measures against lightning is identifying the attachment locations. For this purpose, oversimplified approaches are currently employed, which do not represent the associated discharge phenomena. Therefore, in this work, a suitable model is developed for simulating the inception and propagation of bi-polar leader discharge from the aircraft. Modeling of leader discharges requires field computation around the aircraft, which is carried out employing the Surface Charge Simulation Method (SCSM) combined with sub-modeling, which ensures the best accuracy of field computations near nosecone, wingtips, etc. A DC10 aircraft model is considered for the simulation. Simulations are performed for different pairs of leader inception points on aircraft using the developed model. Subsequently, corresponding ambient fields required for stable bi-polar discharge from aircraft are determined. These values are in the range of measured ambient fields reported in the literature. In summary, the present work has come up with a suitable model for simulating the bi-polar leader inception and propagation from the flying aircraft. Using the same, a detailed quantitative description of the discharge phenomena from the aircraft is provided.

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Squires, K., i S. Businger. "The Morphology of Eyewall Lightning Outbreaks in Two Category 5 Hurricanes*". Monthly Weather Review 136, nr 5 (1.05.2008): 1706–26. http://dx.doi.org/10.1175/2007mwr2150.1.

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Abstract Data from the Long-Range Lightning Detection Network (LLDN), the Tropical Rainfall Measuring Mission (TRMM) satellite, and reconnaissance aircraft are used to analyze the morphology of lightning outbreaks in the eyewalls of Hurricanes Rita and Katrina, two of the strongest storms in the Atlantic hurricane record. Each hurricane produced eyewall lightning outbreaks during the period of most rapid intensification, during eyewall replacement cycles, and during the time period that encompassed the maximum intensity for each storm. Within the effective range of the aircraft radar, maxima in eyewall strike density were collocated with maxima in radar reflectivity. High lightning strike rates were also consistently associated with TRMM low brightness temperatures and large precipitation ice concentration (PIC) values. The strike density ratio between the eyewall region and the outer rainband region was 6:1 for Hurricane Rita and 1:1 for Hurricane Katrina. This result is in contrast to those of previous remote lightning studies, which found that outer rainbands dominated the lightning distribution. The differences are shown to be at least in part the result of the more limited range of the National Lightning Detection Network (NLDN) data used in the earlier studies. Finally, implications of the results for the use of LLDN lightning data to remotely examine changes in hurricane intensity and structural evolution are discussed.

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Wang, Yongwei, Deng Zhou, Gang Yan i Zhuangjie Wang. "Experimental and Numerical Study on Residual Strength of Honeycomb Sandwich Composite Structure after Lightning Strike". Aerospace 9, nr 3 (14.03.2022): 158. http://dx.doi.org/10.3390/aerospace9030158.

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Honeycomb sandwich composite structures are widely used in various aircraft structures due to their unique performance. However, honeycomb sandwich composite structures are prone to lightning damage that threatens the structure safety. Therefore, it is necessary to assess the residual mechanical properties of honeycomb sandwich composite structures after a lightning strike. In this study, simulated lightning strike tests were first conducted for honeycomb sandwich panels with and without carbon nanotube film (CNTF) to obtain different damage scenarios and study the protection effect of CNTF. Then, the residual compressive strength of the panels with lightning strike damage was predicted using a progressive damage analysis method and verified with the experimental results. It was found that the numerical prediction results agree with the experimental results. The size and extent of lightning damage have an important effect on the compression damage mode of honeycomb sandwich panel with closed edges.

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Broc, Alain, Philippe Lalande, Emmanuel Montreuil, Jean-Patrick Moreau, Alain Delannoy, Anders Larsson i Pierre Laroche. "A lightning swept stroke model: A valuable tool to investigate the lightning strike to aircraft". Aerospace Science and Technology 10, nr 8 (grudzień 2006): 700–708. http://dx.doi.org/10.1016/j.ast.2005.10.008.

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Ranjith, Ravichandran, Rho Shin Myong i Sangwook Lee. "Computational Investigation of Lightning Strike Effects on Aircraft Components". International Journal of Aeronautical and Space Sciences 15, nr 1 (30.03.2014): 44–53. http://dx.doi.org/10.5139/ijass.2014.15.1.44.

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Guo, Dan Dan, Dong Lin Su, Xiao Ying Zhao, Li Peng Deng i You Feng Chen. "Electromagnetic Compatibility Analysis of Carbon Fiber Cabin Struck by Lightning in the Aircraft". Advanced Materials Research 383-390 (listopad 2011): 7509–14. http://dx.doi.org/10.4028/www.scientific.net/amr.383-390.7509.

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Aircraft is more light than usual because of using the material of carbon fiber, which can make aircraft lighter than metal materials. But the shielding effectiveness of carbon fiber is worse than metal materials. First, This paper explains the direct effect and the indirect effect which aircraft suffer of the lightning strike. And then this paper analysis and imitates the carbon fiber cabin struck by lightning. And then, at two circumstance of indirect effect, this paper gives the result of electric field, magnetic field and surface current. Finally, this paper gives some advice for defending outside the carbon fiber cabin and electromagnetic compatibility (EMC) inside the carbon fiber cabin.

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Wang, Fusheng, Xiangteng Ma, Yao Zhang i Senqing Jia. "Lightning Damage Testing of Aircraft Composite-Reinforced Panels and Its Metal Protection Structures". Applied Sciences 8, nr 10 (1.10.2018): 1791. http://dx.doi.org/10.3390/app8101791.

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In order to investigate the lightning damage behavior of an aircraft carbon fiber/epoxy composite-reinforced panel and its protection structures, four types of panels were selected to carry out a lightning experiment. Panels were without protection, with a full-sprayed aluminum coating, a local-sprayed aluminum coating, and a full-embedded copper mesh filling, respectively. Their surface and internal damage was detected via ultrasonic C-scanning. Results showed delamination damage for the protected and unprotected specimens due to substantial lightning Joule heat, thermal shock, and internal explosion. The aluminum coatings and the copper mesh had good shielding performance against anti-lightning strike damage. The protection method with a full-sprayed aluminum coating is more effective compared with the other two methods. This study is valuable to investigate the protection effectiveness of metal covers when aircraft composite structures are struck by lightning.

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Sun, Jinru, Xueling Yao, Wenjun Xu, Jingliang Chen i Yi Wu. "Evaluation method for lightning damage of carbon fiber reinforced polymers subjected to multiple lightning strikes with different combinations of current components". Journal of Composite Materials 54, nr 1 (29.06.2019): 111–25. http://dx.doi.org/10.1177/0021998319860562.

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The aircraft lightning environment consists of four lightning current components with different parameters, which are known as lightning components A, B, C and D. The lightning damage of aeronautic carbon fiber reinforced polymer laminates subjected to multiple continuous sequential lightning current components with different timing combinations was experimentally evaluated. The experimental results indicated that the carbon fiber reinforced polymer laminates suffered serious lightning damage, including carbon fiber fracture, resin pyrolysis and delamination. Through an analysis of the lightning damage properties of carbon fiber reinforced polymers, the influential factors and evaluation methods of the lightning damage in carbon fiber reinforced polymer laminates were studied. Because the lightning damage evaluation method under a single lightning impulse was found to be inapplicable for the multiple continuous lightning strikes, a multi-factor evaluation method was proposed. In the multiple continuous lightning strike test, the damage depth was found to be closely related to lightning components A, B and D and could be estimated based on the amplitudes and rise rates of the applied lightning components. Increases in the damaged area after a lightning strike were driven by lightning component C due to its substantial thermal effects. The damaged area was evaluated on the basis of the parameters of the electrical action integral and the transfer charge. The research on the evaluation methods for carbon fiber reinforced polymer laminate lightning damage presented herein may provide experimental support and a theoretical basis for studying the lightning effect mechanism and optimizing material formulations, manufacturing processes and structural designs to achieve performance improvements for carbon fiber reinforced polymer laminates in the future.

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Featherston, C. A., Mark J. Eaton, S. L. Evans, Karen M. Holford, Rhys Pullin i Matthew Cole. "Development of a Methodology to Assess Mechanical Impulse Effects Resulting from Lightning Attachment to Lightweight Aircraft Structures". Applied Mechanics and Materials 24-25 (czerwiec 2010): 129–34. http://dx.doi.org/10.4028/www.scientific.net/amm.24-25.129.

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The effect of lightning attachment to structures and vehicles is a cause of major concern to a number of different industries, in particular the aerospace industry, where the consequences of such an event can be catastrophic. In 1963, a Boeing 707 was brought down in Maryland killing 81 people on board, triggering the improvement of lightning protection standards. However, commercial jets are still struck on average once every 10,000 hours of flight time and between 1963 and 1989 forty lightning related accidents were recorded within the U.S.A alone. The rapid increase in the use of composite materials in aircraft design and the consequent increase in complexity when determining the effects of a lightning strike, has led to new challenges in aircraft protection and the requirement for improved understanding and standardisation.

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Kim, Jong-Jun, Sang-Tae Baek, Dong-Geon Song i Rho-Shin Myong. "Computational Simulation of Lightning Strike on Aircraft and Design of Lightning Protection System". Journal of the Korean Society for Aeronautical & Space Sciences 44, nr 12 (1.12.2016): 1071–86. http://dx.doi.org/10.5139/jksas.2016.44.12.1071.

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Thirukumaran, Sanmugasundaram, Paul Ratnamahilan Polycarp Hoole, Harikrishnan Ramiah, Jeevan Kanesan, Kandasamy Pirapaharan i Samuel Ratnajeevan Herbert Hoole. "A new electric dipole model for lightning-aircraft electrodynamics". COMPEL: The International Journal for Computation and Mathematics in Electrical and Electronic Engineering 33, nr 1/2 (20.12.2013): 540–55. http://dx.doi.org/10.1108/compel-12-2012-0385.

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Purpose – As commercial and military aircraft continue to be subject to direct lightning flashes, there is a great need to characterize correctly the electrical currents and electric potential fluctuations on an aircraft to determine alternative design approaches to minimizing the severity of the lightning-aircraft dynamics. Moreover, with the increased severity of thunderstorms due to global warming, the need arises even more to predict and quantify electrical characteristics of the lightning-aircraft electrodynamics, which is normally not measurable, using a reliable electric model of the aircraft. Such a model is advanced here. The paper aims to discuss these issues. Design/methodology/approach – The case considered in this paper is that of an aircraft directly attached to an earth flash lightning channel. The paper develops a new approach to modelling the aircraft using electric dipoles. The model has the power to represent sharp edges such as wings, tail ends and radome for any aircraft with different dimensions by using a number of different sized dipoles. The distributed transmission line model (TLM) of the lightning return stroke incorporating the distributed aircraft model is used to determine aircraft electrical elements and finally the electric current induced on the aircraft body due to lightning's interaction with the aircraft. The model is validated by the waveform method and experimental results. Findings – The dipole model proposed is a very powerful tool for minute representation of the different shapes of aircraft frame and to determine the best geometrical shape and fuselage material to reduce electric stress. This charge simulation method costs less computer storage and faster computing time. Originality/value – The paper for the first time presents a computer-based simulation tool that allows scientists and engineers to study the dynamics of voltage and current along the aircraft surface when the aircraft is attached to a cloud to ground lightning channel.

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Williams, Abigail. "Lightning Strikes". Aerospace Testing International 2022, nr 3 (wrzesień 2022): 34–40. http://dx.doi.org/10.12968/s1478-2774(23)50302-1.

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Gizatullin, Z. M., R. M. Gizatullin i M. G. Nuriev. "Technique of physical modeling of lightning strike effects on aircraft". Russian Aeronautics (Iz VUZ) 59, nr 2 (kwiecień 2016): 157–60. http://dx.doi.org/10.3103/s106879981602001x.

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Guerra-Garcia, Carmen, Ngoc Cuong Nguyen, Jaime Peraire i Manuel Martinez-Sanchez. "Charge Control Strategy for Aircraft-Triggered Lightning Strike Risk Reduction". AIAA Journal 56, nr 5 (maj 2018): 1988–2002. http://dx.doi.org/10.2514/1.j056406.

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Rufail, Leandro, i Jean-Jacques Laurin. "Composite Aircraft Lightning Strike Protection Damage Evaluation Using Microwave Microscopy". IEEE Transactions on Instrumentation and Measurement 69, nr 6 (czerwiec 2020): 3804–11. http://dx.doi.org/10.1109/tim.2019.2941039.

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Jang, Jae-Kyeong, Jong-Min Hyun, Dae-Sung Son i Jung-Ryul Lee. "Nondestructive and electromagnetic evaluations of stealth structures damaged by lightning strike". Journal of Intelligent Material Systems and Structures 30, nr 17 (12.07.2019): 2567–74. http://dx.doi.org/10.1177/1045389x19862366.

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Stealth technology is very important for the survival of military aircraft. A stealth aircraft structure has both electromagnetic and mechanical functions. Lightning can cause failure on both the points. In this study, we claim that the stealth structure should be evaluated nondestructively and electromagnetically, and we propose a method for full-field evaluations of both the functions. First, a radar absorbing structure was designed and fabricated with stealth capability in the X-band. The radar absorbing structure consisted of a carbon nanotube layer (glass/epoxy dispersed with multiwalled carbon nanotubes), a spacer layer (glass/epoxy) and a perfect electrical conductor layer. A lightning test was performed using an impulse current generator according to standard regulations. Then, nondestructive damage and electromagnetic performance evaluations were performed using a pulse-echo laser ultrasonic propagation imager and a scanning free-space measurement system, respectively. The results showed that neither structural damage nor changes in the electromagnetic properties were observed during the two evaluations. In general, the composites were severely damaged by lightning. However, it turned out that the radar absorbing structure with the carbon nanotube layer could prevent serious damage to stealth function as well as material damage owing to the high conductivity of the carbon nanotubes dispersed in its surface layer.

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Rakov, Vladimir A. "Mathematical Modeling of Energy Distribution in Entering a Beam into the Workpiece Material in the Course of Electron Beam Welding". Elektrichestvo 6, nr 6 (2021): 4–11. http://dx.doi.org/10.24160/0013-5380-2021-6-4-11.

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Lightning can be defined as a transient, high-current (typically tens of kA) electric discharge in air whose length is measured in km. As for any discharge in air, lightning channel is composed of ionized gas, that is, of plasma, whose peak temperature is typically 30,000 K, about five times higher than the temperature of the surface of the Sun. The global lightning flash rate is some tens to a hundred km per second. Lightning initiates many forest fires, and over 30% of all electric power line failures are lightning related. Each commercial aircraft is struck by lightning on average once a year. A lightning strike to an unprotected object or system can be catastrophic. In the first part [1] of the article, an overview of thunderclouds and their charge structure was given, and different types of lightning were described. The existing hypotheses of lightning initiation in thunderclouds were reviewed. In the second part of the article, current and electromagnetic signatures of lightning are characterized and the techniques to measure lightning electric and magnetic fields are discussed

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Katunin, Andrzej, Katarzyna Krukiewicz, Roman Turczyn, Przemysław Sul i Marcin Bilewicz. "Electrically conductive carbon fibre-reinforced composite for aircraft lightning strike protection". IOP Conference Series: Materials Science and Engineering 201 (maj 2017): 012008. http://dx.doi.org/10.1088/1757-899x/201/1/012008.

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Raimondo, Marialuigia, Liberata Guadagno, Vito Speranza, Leila Bonnaud, Philippe Dubois i Khalid Lafdi. "Multifunctional graphene/POSS epoxy resin tailored for aircraft lightning strike protection". Composites Part B: Engineering 140 (maj 2018): 44–56. http://dx.doi.org/10.1016/j.compositesb.2017.12.015.

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Katunin, A., K. Krukiewicz, A. Herega i G. Catalanotti. "Concept of a Conducting Composite Material for Lightning Strike Protection". Advances in Materials Science 16, nr 2 (1.06.2016): 32–46. http://dx.doi.org/10.1515/adms-2016-0007.

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Abstract The paper focuses on development of a multifunctional material which allows conducting of electrical current and simultaneously holds mechanical properties of a polymeric composite. Such material could be applied for exterior fuselage elements of an aircraft in order to minimize damage occurring during lightning strikes. The concept introduced in this paper is presented from the points of view of various scientific disciplines including materials science, chemistry, structural physics and mechanical engineering with a discussion on results achieved to-date and further plans of research.

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Buguet, Magalie, Philippe Lalande, Pierre Laroche, Patrice Blanchet, Aurélie Bouchard i Arnaud Chazottes. "Thundercloud Electrostatic Field Measurements during the Inflight EXAEDRE Campaign and during Lightning Strike to the Aircraft". Atmosphere 12, nr 12 (8.12.2021): 1645. http://dx.doi.org/10.3390/atmos12121645.

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The AMPERA (Atmospheric Measurement of Potential and ElectRic field on Aircraft) electric field network was integrated on the Falcon 20 (F20) of SAFIRE (the French facility for airborne research) in the framework of EXAEDRE (EXploiting new Atmospheric Electricity Data for Research and the Environment) project. From September 2018, an in-flight campaign was performed over Corsica (France) to investigate the electrical activity in thunderstorms. During this campaign, eight scientific flights were done inside or in the vicinity of a thunderstorm. The purpose of this paper is to present the AMPERA system and the atmospheric electrostatic field recorded during the flights, and particularly during the pass inside electrified clouds, in which the aircraft was struck by lightning. The highest value of atmospheric electrostatic field recorded during these flights was around 79 kV·m−1 at 8400 m of altitude. A normalization of these fields is done by computing the reduced atmospheric electrostatic field to take into account the altitude effect (ratio between the atmospheric electrostatic field and the air density). Most of the significant values of reduced atmospheric electrostatic field magnitude retrieved during this campaign occur between around 5.5 and 9.5 km and are included between 50 and 100 kV·m−1. The highest value measured of the reduced atmospheric electrostatic field is 194 kV·m−1 during the lightning strike of the F20. The merging of these results with data from former campaigns suggests that there is a threshold (depending of the aircraft size) for the striking of an aircraft.

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de Toro Espejel, J. Fernandez, i Zahra Sharif Khodaei. "Lightning Strike Simulation in Composite Structures". Key Engineering Materials 754 (wrzesień 2017): 181–84. http://dx.doi.org/10.4028/www.scientific.net/kem.754.181.

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Lighting strike is one of the critical threats to the safety of composite aircrafts during flight. This work reports on numerical simulation of lightning strike in composite structures. Different modelling techniques using the commercial software ABAQUS, together with damage models are studied to find the most appropriate one in comparison to experimental results. Once the numerical model is validated, the effect of insertion of carbon nanotubes (CNTs) and metallic mesh in the composite is investigated. It is concluded that inserting CNTs in the top layer of the composite can improve its lightning strike protection noticeably.

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I Lekas, Theodore. "Computation of locations of possible stepped leader attachment points on an aircraft flying under thunderstorm conditions". Aeronautics and Aerospace Open Access Journal 6, nr 1 (24.01.2022): 1–5. http://dx.doi.org/10.15406/aaoaj.2022.06.00134.

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In case of flight in a thunderstorm region, a lightning strike on the aircraft might occur. For better lightning protection, the locations of points on the aircraft skin where a stepped leader can be attached should be delimited. In this paper, the areas of the skin of an aircraft where a stepped leader might be attached are defined through an approach based on the fact that electrostatics and potential flow theory have the same mathematical background. This is done by computing the distribution of the electrostatic field on the metallic parts of the skin of the aircraft due to the ambient electric field. In any area of the skin, where the electric field resulting from the combination of the ambient electric field and the local electric field can ionize the air, attachment points of a stepped leader might exist. The advantage of this approach is a decreased computational time and computer memory needed, as compared to a full Computational Physics approach. The areas of the skin of a generic airliner delimited through this approach, at least qualitatively, are in agreement with photos taken under real thunderstorm conditions.

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Huang, Ying, Dan Sun i Danielle S. Soban. "Assessing the Novel Aircraft Lightning Strike Protection Technology Using Technology Impact Forecasting". Journal of Aircraft 57, nr 5 (wrzesień 2020): 914–21. http://dx.doi.org/10.2514/1.c035875.

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Fisher, Joseph, Paul R. Hoole, Kandasamy Pirapaharan i Samuel H. Hoole. "Pre-Lightning Strikes and Aircraft Electrostatics". MATEC Web of Conferences 87 (2017): 05002. http://dx.doi.org/10.1051/matecconf/20178705002.

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Karch, Christian, Fridolin Heidler i Christian Paul. "Protection of Aircraft Radomes against Direct Lightning Strikes—An Overview". Atmosphere 12, nr 9 (4.09.2021): 1141. http://dx.doi.org/10.3390/atmos12091141.

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The aim of this contribution is to design and test the lightning protection of an aircraft radome exposed to direct lightning strikes. The influencing parameters are investigated on different radome wall samples equipped with solid and segmented diverter strips. The effectiveness of the lightning interception and protection measures is tested with different high-voltage waveforms and representative high-current pulses. The tests show that reliable radome lightning protection can be achieved by an optimized arrangement of solid and segmented diverter strips, even if the aircraft radome has a huge size, with dimensions up to several meters.

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Imran, Kazi A., i Kunigal N. Shivakumar. "Graphene-modified carbon/epoxy nanocomposites: Electrical, thermal and mechanical properties". Journal of Composite Materials 53, nr 1 (6.06.2018): 93–106. http://dx.doi.org/10.1177/0021998318780468.

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A primary limitation of fiber-reinforced polymer composites in aircraft applications is susceptibility to lightning because of poor electrical, thermal and electromagnetic properties. The current methods to mitigate the lightning strike in aircraft have added weight and reduced the performance. Previous graphene-modified epon 828 epoxy matrix study showed that three-roll dispersion is effective, repeatable and potentially scalable to disperse graphene in to epoxy to increase the electrical conductivity. Percolation threshold of graphene was found to be about 1.0 wt.% that enhanced electrical conductivity of epon 828 epoxy matrix from 4.3 × 10−15 to 2.6 × 10−6 S/m, thermal conductivity doubled and fracture toughness increased by one-third. In the present study, the same graphene/epon 828 is reinforced by carbon fabric by hand lay-up followed by compression molding. The resulting composite laminate was tested for electrical, thermal and mechanical properties and results of this nanocomposite laminates were compared with base composite laminate.

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Pandey, Akhileshwar, Ashutosh K. Upadhyay i K. K. Shukla. "Numerical studies on damage of carbon/epoxy composites exposed to lightning strike". International Journal of Engineering, Science and Technology 13, nr 1 (9.07.2021): 112–18. http://dx.doi.org/10.4314/ijest.v13i1.17s.

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Lighter carbon fiber/epoxy composites are replacing metals in wind turbines blades, aircraft structures, marine structures, automotive skins & other applications. Lightning strike damage is a real threat to these materials during service life. Along with experimental studies, their damage predictions by numerical methods are being attempted by various researchers. The numerical simulation of this damage by coupled thermal–electric (transient) analysis and thermal transient analysis is presented in this article. In this study, damage predictions based on thermal profiles are carried out, and suitable validations with earlier published work are discussed.

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Rakov, Vladimir A. "Lightning, the Science. Part 1: Modern View". Elektrichestvo 5, nr 5 (2021): 4–16. http://dx.doi.org/10.24160/0013-5380-2021-5-4-16.

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Lightning can be defined as a transient, high-current (typically tens of kA) electric discharge in air whose length is measured in km. As for any discharge in air, lightning channel is composed of ionized gas, that is, of plasma, whose peak temperature is typically 30,000 K, about five times higher than the temperature of the surface of the Sun. Lightning was present on Earth long before human life evolved and it may even have played a crucial role in the evolution of life on our planet. The global lightning flash rate is some tens to a hundred km per second. Each year, some 25 million cloud-to-ground lightning discharges occur in the United States, and this number is expected to increase by about 50% due to global warming over the 21st century. Lightning initiates many forest fires, and over 30% of all electric power line failures are lightning related. Each commercial aircraft is struck by lightning on average once a year. A lightning strike to an unprotected object or system can be catastrophic. In the first part of the article, an overview of thunderclouds and their charge structure is given, basic lightning terminology is introduced, and different types of lightning (including the so-called rocket-triggered lightning) are described. For the most common negative cloud-to-ground lightning, main lightning processes are identified and the existing hypotheses of lightning initiation in thunderclouds are reviewed.

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Matthews, J. J. "Role 2 Afloat support to the QUEEN ELIZABETH (QE) Class – an update from WESTLANT 18". Journal of The Royal Naval Medical Service 105, nr 2 (2019): 103–7. http://dx.doi.org/10.1136/jrnms-105-103.

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AbstractWESTLANT 18 saw a Role 2 Afloat (R2A) team deploy on HMS QUEEN ELIZABETH (QNLZ) to support the First of Class Flying Trials for the F-35 Lightning 2 aircraft. This team established the R2A capability onboard QNLZ and began the process of developing R2A support to Carrier Strike Group (CSG) operations. The deployment was a great success and many lessons were identified. The experience from this deployment is summarised and the current R2A support to CSG is described.

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Reid, G. W. "Mechanical Damage to Aircraft Structures from Lightning Strikes". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 207, nr 1 (styczeń 1993): 1–14. http://dx.doi.org/10.1243/pime_proc_1993_207_240_02.

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The various types of current waveforms associated with lightning discharges are discussed together with their relevance to different areas of the aircraft structures. The physical damage that could be sustained by aircraft material due to lightning strikes, in particular the damage to composite material especially carbon fibre, is described. This damage is primarily due to the very fast heating and impulsive forces which lightning currents can produce. Minimum cross-sectional areas required to carry these currents safely are discussed as well as the effect of moisture content and loading the samples during test for the case of carbon fibre composite material. Details of the effects of arc attachment to various composite materials and also metal with the degree and type of damage that can be produced are reviewed.

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Sazhenkov, Nickolai, i Aleksei Sazhenkov. "LIGHTNING PROTECTION COATINGS OF AIRCRAFT ENGINES POLYMER COMPOSITE NACELLES. PART 1. ANALYSIS OF THE EXISTING TYPES OF LIGHTNING PROTECTION". Perm National Research Polytechnic University Aerospace Engineering Bulletin, nr 67 (2021): 43–55. http://dx.doi.org/10.15593/2224-9982/2021.67.05.

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The overview of the existing and upcoming types of aircraft engines polymeric composite nacelles lightning protection is presented. It is demonstrated that at present the most widely-used technologies of polymer composites lightning protection in the world and domestic aviation industry consist in using metal foils and meshes. However, the relative weight of the lightning protection comprised of metal foils and meshes (including adhesive and erosion layers) may result in a significant weight gain up to 0.7–0.9 kg per each square meter of the polymer composite nacelle surface. Additionally, the principal disadvantage of metal meshes is high percentage of the open area (80–90 %) leading to decreased engine EMI protection in the event of exposure to electromagnetic impulse from the lightning strike or L/HIRF. Currently, intensive scientific studies are performed in the field of aviation equipment lightning protection in different universities, institutes and companies, mainly in the USA, Europe, Russia and Japan. The potential lightning protection problem solution addressed by the large number of scientific papers is use of coatings made of heatproof polymer composites and polymer binders modified by carbon nanoparticles to develop a better material conductivity. However, this technology is characterized by high costs, low repairability, etc. Various spraying methods are studied. It has been found out that for the lightning protection of the advanced types of nacelles the highly competitive engineering solution is the one that ensures a cardinally low relative weight and high reliability, manufacturability, high EMI protection L/HIRF, low engine life cycle costs including easy in-service repair.

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Zhulikov, S. S., S. I. Khrenov, Yu S. Turchaninova, G. V. Kopaev i D. V. Golubev. "Test Procedure for Aircraft Fuel Systems in the Case of a Lightning Strike". Russian Electrical Engineering 93, nr 8 (sierpień 2022): 498–501. http://dx.doi.org/10.3103/s1068371222080120.

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INOMATA, Soshi, Yoshiyasu HIRANO, Toshio OGASAWARA i Shintaro KAMIYAMA. "Dynamic Load Estimation Caused by Simulated Lightning Strike Testing on Aircraft Structural Materials". Proceedings of the Materials and processing conference 2020.28 (2020): 107. http://dx.doi.org/10.1299/jsmemp.2020.28.107.

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ZHULIKOV, S. S., S. I. KHRENOV, Yu S. TURCHANINOVA, G. V. KOPAEV i D. V. GOLUBEV. "To the methodology of testing the fuel systems of aircraft under lightning strike". Elektrotekhnika, nr 8 (2022): 7–11. http://dx.doi.org/10.53891/00135860_2022_8_7.

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Bikkina, Siva Chakra Avinash, i Pappu V. Y. Jayasree. "Investigation of Electromagnetic Shielding for Wire Mesh Composite for Aircraft against Lightning Strike". International Journal of Electrical and Electronics Research 11, nr 2 (30.05.2023): 353–58. http://dx.doi.org/10.37391/ijeer.110216.

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Nowadays, fly-wire is only used for flying-related things. All plane controls depend on electronics, but they also must deal with high-intensity radiated fields. This equipment might need an electromagnetic shield to protect it from outside electromagnetic pollution. The current work aims to develop a mesh around the operating equipment to protect and make it work better. AL6061 was used to create a shield with a metal matrix composite. Here three combinations of Metal Matrix Composite (MMCs) were considered to protect from the high-intensity radiated fields. These MMCs are AL6061+10%Al_2 O_3+5% FA (MMC-1), AL6061+15% Al_2 O_3+5% FA (MMC-2), and AL6061+20% Al_2 O_3+5% FA (MMC-3) made the process of shielding more effective at different percentages. Explements are Measures that take the electrical characteristics, and they are by Shielding Effectiveness (SE) of different concentrations of fly ash and Al_2 O_3.SE of 50 dB is achieved; hence these MMCs can be used in aircraft and other applications as a shield.

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Wang, Yan De, Cheng Gao, Fei Guo i Yan Xin Li. "The Study of Inner EM Environment in the Helicopter under the Influence of Lightning Strikes". Advanced Materials Research 912-914 (kwiecień 2014): 860–64. http://dx.doi.org/10.4028/www.scientific.net/amr.912-914.860.

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Numeric simulation of the whole aircraft is conducted in the CST MICROSTRIPES workshop which is based on the theory of TLM. The current waveform is defined according to the standard of SAEARP5412. The EM environment inside the helicopter is analyzed when the lightning strikes on the middle of the helicopter vertically. The lightning current moves along the aircraft to the back, then travels to the middle along the line. Simulation analysis demonstrates that the method can effectively simulate the indirect lightning effect, and shows the EM environment characteristic inside the helicopter.

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Hoole, P. R. P., S. Thirukumaran, Harikrishnan Ramiah, Jeevan Kanesan i S. R. H. Hoole. "Ground to Cloud Lightning Flash Currents and Electric Fields: Interaction with Aircraft and Production of Ionosphere Sprites". Journal of Computational Engineering 2014 (3.08.2014): 1–5. http://dx.doi.org/10.1155/2014/869452.

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This paper presents for the first time a case for the importance of ground to cloud (upward leader) lightning flash parameters for safety testing of direct aircraft-lightning interaction and protection of wind turbines, as well as the importance of radiated electric fields for indirect lightning-aircraft interaction and generation of electric discharges called sprites and halos in the ionosphere. By using an electric circuit model of the transverse magnetic waves along the return stroke channel, electric currents at ground level as well as cloud level are determined for both the cloud to ground lightning flash and the ground to cloud lightning flash. We show that when an aircraft triggers lightning, the electric currents will be much more severe in current magnitude, rate of rise of currents, and frequency spectrum than otherwise and are more severe than the parameters observed for the usual and well monitored (and measured) cloud to ground (downward leader) flashes. The rate of rise of currents and the frequency spectrum of the ground to cloud lightning flash are also given here. The electric fields radiated by the lightning flashes that would appear in the ionosphere are presented for both the earth flash and the ground to cloud flash.

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Piccone, Ashley. "Simulating lightning strikes to improve aircraft safety". Scilight 2022, nr 1 (7.01.2022): 011111. http://dx.doi.org/10.1063/10.0009253.

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