Journal articles on the topic 'Composite aircraft structure'
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Broer, Agnes A. R., Rinze Benedictus, and Dimitrios Zarouchas. "The Need for Multi-Sensor Data Fusion in Structural Health Monitoring of Composite Aircraft Structures." Aerospace 9, no. 4 (March 30, 2022): 183. http://dx.doi.org/10.3390/aerospace9040183.
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With the increased use of composites in aircraft, many new successful contributions to the advancement of the structural health monitoring (SHM) field for composite aerospace structures have been achieved. Yet its application is still not often seen in operational conditions in the aircraft industry, mostly due to a gap between research focus and application, which constraints the shift towards improved aircraft maintenance strategies such as condition-based maintenance (CBM). In this work, we identify and highlight two key facets involved in the maturing of the SHM field for composite aircraft structures: (1) the aircraft maintenance engineer who requires a holistic damage assessment for the aircraft’s structural health management, and (2) the upscaling of the SHM application to realistic composite aircraft structures under in-service conditions. Multi-sensor data fusion concepts can aid in addressing these aspects and we formulate its benefits, opportunities, and challenges. Additionally, for demonstration purposes, we show a conceptual design study for a fusion-based SHM system for multi-level damage monitoring of a representative composite aircraft wing structure. In this manner, we present how multi-sensor data fusion concepts can be of benefit to the community in advancing the field of SHM for composite aircraft structures towards an operational CBM application in the aircraft industry.
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Utami, Mala, Jonathan Ernest Sirait, Beny Budhi Septyanto, Aries Sudiarso, and I. Nengah Putra Apriyanto. "Laminar Composite Materials for Unmanned Aircraft Wings." Defense and Security Studies 3 (December 21, 2022): 106–12. http://dx.doi.org/10.37868/dss.v3.id211.
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Unmanned Aerial Vehicles (UAVs) have high popularity, especially in the military field, but are now also being applied to the private and public sectors. One of the UAV components that require high material technology is the wing. The latest material technology developed as a material for unmanned aircraft wings is a composite material that has high strength and lightweight. This research aims to identify composite materials that can be used for unmanned aircraft wing structures. The method used in this research is a qualitative method with a literature study approach. The results of this theoretical study show that some of the latest composite materials that have been developed into materials for unmanned aircraft wings are Laminar Composites with a sandwich structure. Laminar and sandwich composites consist of various constituent materials such as Balsa wood fiber-glass and polyester resin, microparticles, Carbon Fibre Reinforced Polymer, polymer matrix composites reinforced with continuous fibers, Polymer matrix composites, E-glass/Epoxy, Kevlar/Epoxy, Carbon/Epoxy, woven fabrics, acrylonitrile butadiene styrene-carbon (ABS) laminated with carbon fiber reinforced polymer (CFRP) and uniaxial prepreg fabrics. Laminar and sandwich composite materials are a reference for developing unmanned aircraft wing structures that have resistant strength and lightweight.
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Li, Fenglei, Shengnian Zhang, and Wanxiang Cheng. "Application and Optimization of Wing Structure Design of DF-2 Light Sports Aircraft Based on Composite Material Characteristics." Journal of Nanomaterials 2022 (June 21, 2022): 1–10. http://dx.doi.org/10.1155/2022/6967016.
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Compared with ordinary metal structures, advanced composite materials have the characteristics of high strength, high rigidity, and light weight. The use of composite materials in aircraft structures is currently a hot research topic. This research mainly discusses the optimization design of the composite wing structure of the DF-2 light sports aircraft. This article takes the DF-2 light sports aircraft planned to be produced by the company as the source. Based on its overall design basis, aerodynamic requirements, and the original wing structure design, according to the composite material aircraft structure design theory and method, the aircraft wing structure is carried out. Composite materials are materials with new properties that are composed of two or more materials with different properties at the macroscale by physical and chemical methods. Composite materials can be divided into functional composite materials and structural composite materials according to the nature of the application. Functional composites are materials with special functions, such as conductive composites, ablative materials, and frictional composites. At present, the main research is on structural composite materials, which are composed of two components: matrix material and reinforcing material. The new structural scheme design and structural strength analysis are designed to meet the structural strength requirements of the wing and the lightest weight. In this paper, according to the force transmission characteristics of different structural types of the wing, the characteristics of the load transmission are analyzed, and the shape parameters and load parameters of the wing structure design are used as initial conditions, and the quantitative analysis model of the wing structure is constructed according to the requirements of strength, stiffness, and stability. Through rapid mathematical modeling and analysis of the wing structure, the weight and efficiency of different configurations can be evaluated. Through the quantitative analysis model of the wing, the wing structure type can be quickly determined according to the wing parameters in the preliminary design, which makes the basis for the selection of the wing structure type. After optimization, the weight of the wing structure decreased from 0.966 kg to 0.803 kg, a decrease of 16.87%. The designability of composite materials is one of its major characteristics. By optimizing the layup angle, layup sequence, and dropout area, the performance indicators of the structure are finally improved. This research will promote the further development of the aerospace field.
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Ganjeh, Babak, and Mohd Roshdi Hassan. "Cost-Efficient Composite Processing Techniques for Aerospace Applications – A Review." Applied Mechanics and Materials 325-326 (June 2013): 1465–70. http://dx.doi.org/10.4028/www.scientific.net/amm.325-326.1465.
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Composite materials have been used in aircraft components since the early beginning of aircraft industry establishment.Undenaible advantages of composites in mechanical properties and light weight in comparison with conventional metal alloys make them desirable alternative for fabrication of different aircraft components. However, quality concerns and high costs of processing tackle the extensive usage of composites in aircraft structure, until the past decade, introducing new generation of composite processing techniques, needless of traditional autoclave processing and capable of fabricating aerospace-grade quality composite parts more time and cost efficiently. In this paper concise review over recent cost-efficient composite processing technologies with proven practicality in commercial aircraft applications, is presented.
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Du, Ya Xiong, Shu Li, and Kai Guo. "Strength Analysis for Composite Windshield of Commercial Aircraft." Advanced Materials Research 1030-1032 (September 2014): 1010–13. http://dx.doi.org/10.4028/www.scientific.net/amr.1030-1032.1010.
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With the development of advanced composites technology, composites instead of traditional aluminum alloy, will be widely used to build full-size aircraft windshield structure in the aviation field. The finite element model of commercial aircraft composite windshield is established in the environment of Msc.Patran / Nastran. And based on Tasi-Wu failure criterion, the strength of windshield structure under typical load pressure is predicted and analyzed during failure processes. It shows that composite windshield can work better through rational design according to the analysis result.
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Armstrong, Keith. "Civil Aircraft Composite Structure Repair Technology." Materials Technology 14, no. 4 (January 1999): 198–210. http://dx.doi.org/10.1080/10667857.1999.11752840.
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Grant, Carroll. "Automated processes for composite aircraft structure." Industrial Robot: An International Journal 33, no. 2 (March 2006): 117–21. http://dx.doi.org/10.1108/01439910610651428.
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Lee, WJ, BH Seo, SC Hong, MS Won, and JR Lee. "Real world application of angular scan pulse-echo ultrasonic propagation imager for damage tolerance evaluation of full-scale composite fuselage." Structural Health Monitoring 18, no. 5-6 (February 24, 2019): 1943–52. http://dx.doi.org/10.1177/1475921719831370.
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Composite structures are assertively used for new airframe designs and manufacturing in military aircrafts because of superior strength-to-weight ratios and fatigue resistance. Because the composites have different fatigue failure characteristics compared with metals, it is necessary to develop different approaches for the composite fatigue design and testing. In this study, we propose an in situ damage evaluation technology with high spatial resolution during full-scale fatigue testing of composite aircraft structures. For real composite structure development considering composite fatigue characteristics, full-scale fatigue and damage tolerance tests of the composite fuselage structure were conducted to evaluate the structural characteristics. In the meantime, the laser ultrasonic nondestructive inspection method, called an angular scan pulse-echo ultrasonic propagation imager, which is fully noncontact, real-time, and portable to position it in between the complex test rigs, is used to observe in situ damage growth of the composite. Finally, the verification procedure assisted by the angular scan pulse-echo ultrasonic propagation imager assures no growth of the initial impact damages after lifetime operation and proves the damage tolerance capability of the developed composite fuselage structure.
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Chernov, Andrey, Ivan Kondakov, and Yury Mirgorodskiy. "Experimental Study of Impact-Protective Elements for Unidirectional Ribs of Lattice Composite Aircraft Structures." MATEC Web of Conferences 304 (2019): 01016. http://dx.doi.org/10.1051/matecconf/201930401016.
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Lattice structures based on unidirectional composite ribs is currently one of the most promising directions of research aiming to create lightweight and reliable structure of future aircrafts [1]. Hybrid structure concepts based on lattice layouts have been developed for a number of conventional and non-conventional civil aircraft configurations, giving up to 15-20% weight saving as compared to conventional composite structures based on laminated skin and stiffeners [2]. One of the most critical problems of load-bearing lattice composite structures is very high sensitivity to impact loads, which is even more crucial than for the laminated composite structures. At the same time, topology of lattice grid makes it possible to create reliable protective system for the ribs, which can be effective in terms of weight expenses.
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Zhang, Jia Rui, Zhen Yu Feng, and Tian Chun Zou. "Certification for Effect of Environment on Composite Properties." Advanced Materials Research 284-286 (July 2011): 396–400. http://dx.doi.org/10.4028/www.scientific.net/amr.284-286.396.
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The environment which can have a great effect on the composite aircraft structure performances must be considered during the design and certification process. In this paper, the extreme temperature and humidity span of the worst environment conditions in aircraft structure design and certification are investigated, and some test methods involving environment influences are also discussed. The studying results can be used in design and certification for environment influences of composite aircraft structures.
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Dai, Jing Tao, Pei Zhong Zhao, Hong Bo Su, Hao Dong Liu, Yu Bo Wang, and Shi Kang Dong. "Optimal Design of Composite Material Maintenance Structure for Aircraft Based on ANSYS Workbench." Key Engineering Materials 871 (January 2021): 216–21. http://dx.doi.org/10.4028/www.scientific.net/kem.871.216.
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Composite material is widely used to maintain damaged structures of aircraft. The 3D finite element model of composite cement maintenance for aircraft is established by finite element method software ANSYS Workbench. The structural characteristics and usage status of the composite cement maintenance model is analyzed, and then the optimal structural parameters of the composite patch are obtained, including the length, width and thickness. The results show that the composite cement maintenance method could effectively restore the rigidity, and improve the strength of the structure. Furthermore, the optimal design for composite patch ensures safety of aircraft, economics of maintenance, and operability of repair methods.
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Srilakshmi, R., and R. Sanjay kumar. "Numerical analysis of sandwich panels under high-velocity impact." IOP Conference Series: Materials Science and Engineering 1248, no. 1 (July 1, 2022): 012104. http://dx.doi.org/10.1088/1757-899x/1248/1/012104.
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Abstract Composites are gaining importance in aircraft structures, due to their high specific strength, stiffness, and low weight. There are different types of composites used in aircraft structures out of which carbon fiber reinforced polymer (CFRP) serves best in the aircraft industry. Half of the weight of the Boeing 787 is made of CFRP and other composites that reduced the weight of the aircraft by 20% as compared to the conventional design with aluminum alloy. Similar to CFRP the recent trend focused on the usage of sandwich structures in aircraft design. Sandwich structure is a composite material made of the lightweight thick core placed between the thin face sheets made of CFRP or Glass fiber reinforced polymer. During service, aircraft panels are subjected to severe structural, aerodynamics loads, and impact loads. These loads cause severe damage to the structure that affects the residual strength. The impact is the more susceptible damage in composite panels. In this paper, a numerical impact analysis of the sandwich panel is carried out. There are different parameters that influence the impact strength of sandwich panels are face sheet material, core material, and thickness of the core. In this paper, finite element-based parametric analysis is carried out by varying face sheet materials such as CFRP, GFRP, Al alloy, Ti alloy, and core materials (such as honeycomb structure and PVC foam). Further, in this work, the combined MADM method using TOPSIS and AHP is applied to find out the optimal face sheet material for the sandwich panel. The attribute data for applying the MADM method is obtained from finite element analysis (FEA).
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Maier, Raluca. "Study on Increasing Performances of Hybrid Composite Through Pull Out Compression Test Assessement." Materiale Plastice 57, no. 1 (April 17, 2020): 329–35. http://dx.doi.org/10.37358/mp.20.1.5325.
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The exhaustive use of light advanced polymer composites into the development of the future high-efficiency long-range commercial aircrafts (primary) structures for increasing strength while decreasing weight for lower fuel consumption and less pollution has attracted great attention in the last decade. In this context, solutions for the integration and joining composites into the aircraft structures metallic sub-assemblies or components, while providing the necessary strength to sustain heavily loaded joints, are urgently required. The paper comes to meet an area of interest for many researchers and large integrators and manufacturers, by presenting several type of metallic join geometrical designs, along with metallic joint part integration solutions into a composite structure directly during production. Performances evaluation of the developed metallic join geometrical designs was performed in static regime by means of �pull-out� compressive tests. The paper focuses on the strength of the hybrid metallic/advanced polymer composites joints. It was concluded that an efficient design of the metallic joint and a proper transition from hybrid to the composite structure can lead to proper integration solutions while assuring safety requirements.
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Chen, Wen Jun, Jing Song Chen, Wen Bo Cheng, and Lu Chun Zhao. "Status Quo of Research on Impact Damage of Composites in Aircraft." Key Engineering Materials 719 (November 2016): 33–40. http://dx.doi.org/10.4028/www.scientific.net/kem.719.33.
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The application of composites in aircraft was introduced. And compare composites with metal materials. The conclusions referring to the impact test on composite laminates and impact damage characteristics of composite laminates, were summarized by referring to a large number of literature. This investigation shows: composite material is more suitable for the preparation of the overall structure; the research of impact damage test on composites mainly concentrated in the layer order; layer direction and low-energy impact test; and there are clear division and judgment method of four kinds of damage body by studying characteristics of impact damage.Keyword: aircraft; composites; impact damage
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Gao, Yu, Nan Li, and Bin Liu. "A Study for Damage Mode of Composite Aircraft Structure with Advanced Composite Materials." Advanced Materials Research 583 (October 2012): 100–104. http://dx.doi.org/10.4028/www.scientific.net/amr.583.100.
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More and more advanced composite materials are used in mainly supporting structure of civil aviation; its airworthiness safety should be the focus of the research. Damage assessment is the key step in the general composite repair procedure. In this paper, the ANSYS calculating method is validated on the basis of classic laminate theory which could be used to calculate composite strength. In one case, it is applied to simulation and modeling of the B767 landing gear door. The case shows that composite damage mode such as low velocity impact damage, curing and fatigue could be evaluated with finite element method, the result of evaluation is provided as a means to composite damage assessment. Thereafter, the finite element method can be used for structural health monitoring to advanced composites.
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Setlak, Lucjan, Rafał Kowalik, and Tomasz Lusiak. "Practical Use of Composite Materials Used in Military Aircraft." Materials 14, no. 17 (August 25, 2021): 4812. http://dx.doi.org/10.3390/ma14174812.
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The article presents a comparative characterization of the structural materials (composites and metals) used in modern aviation structures, focusing on the airframe structure of the most modern aircraft (Airbus A-380, Boeing B-787, and JSF F-35). Selected design and operational problems were analysed, with particular emphasis on composites and light metals (aluminium). For this purpose, the Shore’s method was used for the analysis of the obtained strength results and the programming environment (ANSYS, SolidWorks) required to simulate the GLARE 3 2/1-04 composite. The focus was on highlighting the differences in the construction and modelling of these materials resulting from their various structures (isotropy and anisotropy), e.g., by analyzing the mechanics of metal destruction and comparing it with the composite material. In terms of solving the problems of finite element analysis FEM, tests have been carried out on two samples made of an aluminium alloy and a fiberglass composite. The focus was on highlighting the differences in the construction and modelling of these materials resulting from their various structures (isotropy and anisotropy), e.g., by analyzing the mechanics of metal destruction and comparing it with the composite material. On the basis of the obtained results, the preferred variant was selected, in terms of displacements, stresses, and deformations. In the final part of the work, based on the conducted literature analysis and the conducted research (analysis, simulations, and tests), significant observations and final conclusions, reflected in practical applications, were formulated.
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Li, Ying Guang, C. Y. Fu, D. S. Li, and S. M. Wan. "The Composite Tool Design Technologies of Aircraft Composite Parts in Autoclave Forming." Advanced Materials Research 426 (January 2012): 330–34. http://dx.doi.org/10.4028/www.scientific.net/amr.426.330.
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Aiming at the problems of composites of anisotropic, poor in dimensional and uneven temperature field in the designing of composite tool in autoclave, the techniques of designing the composite tool of aircraft components were constructed, involving in the following aspects: Taking advantage of design flexibility of composites, the thermal expansion coefficient between the moulding board and composite components matched. By analyzing the cure process curve of fiber-reinforced composites, the result that the crisis point without stress between component and tool, which the shape of composite component decided was concluded. By the temperature field analysis, and contrasted with the experimental results, the maximum difference was 4.95°C，after analysis, optimized the structure of the tool, obtaining the relatively uniform temperature field of the board.
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Hartini, Dwi, Buyung Junaidin, and Habibi Habibi. "STRENGTH ANALYSIS OF CARGO-X UAV WING STRUCTURE USING SANDWICH COMPOSITE MATERIALS." Vortex 3, no. 1 (January 15, 2022): 1. http://dx.doi.org/10.28989/vortex.v3i1.1153.
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The Cargo-X UAV aircraft is a UAV aircraft designed to carry medicines, packages and blood bags in areas that require fast and efficient handling. One of the important components of the Cargo-X UAV aircraft is the wing, so the strength of the wing structure must be seriously considered to ensure safety during flight under unexpected conditions. The purpose of this study was to analyze the wing structure of the UAV Cargo-X aircraft made of sandwich composite material to determine the level of safety of the wing structure. The loading of the wing structure uses the load due to the lift. The wing structure modeling uses CATIA software, while the analysis uses PATRAN/NASTRAN software. From the analysis results, the skin and spar wing structures are safe against loading, while the core section is not safe against loading.
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Popov, A. V., V. Yu Voloshina, K. A. Zhuravsky, and M. A. Labina. "Acoustic Emission Method of Diagnostics of Structures Made of Composite Materials Based on Invariants." Advanced Engineering Research 22, no. 4 (January 9, 2004): 331–37. http://dx.doi.org/10.23947/2687-1653-2022-22-4-331-337.
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Introduction. Composite materials are the main way to reduce the weight of the aircraft structure and improve its flight performance. Methods of non-destructive testing enable to assess the technical condition of composite materials, as well as to determine stress concentrators in them to make a decision on the further operation of this control object. The paper presents an analysis of the use of composite materials in the aircraft design and ways to improve their flight performance through the application of composites. An acoustic-emission method for assessing crack resistance based on invariants was described. The study aimed at increasing the accuracy and efficiency of assessing the crack resistance of aircraft structures made of composite materials through the use of the acoustic emission method of non-destructive testing. Materials and Methods. The nomenclature of composite materials used in aircraft was given, and their physical and mechanical properties were compared. The acoustic emission method of non-destructive testing of composite materials based on invariant ratios was used. Results. A method for assessing the crack resistance of primary structural elements based on the invariants of acoustic emission processes, and a program apparatus complex based on it has been developed. Discussion and Conclusions. The results obtained can be used to determine the strength characteristics of composite materials by the acoustic emission method of non-destructive testing to assess the technical condition of primary structural elements in mechanical engineering, shipbuilding, and aircraft construction. The paper is recommended to researchers involved in the development of aircraft.
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Li, Hong Peng, Shu Li, and Fang Lue Huang. "Impact Resistance Research of Composite Laminate Structure." Advanced Materials Research 712-715 (June 2013): 1045–49. http://dx.doi.org/10.4028/www.scientific.net/amr.712-715.1045.
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The composite material has been widely used in aircraft structures. But this kind of material has some shortage such as poor impact resistance, low residual compressive strength, which have a negative influence on the performance of aircraft structures. In this paper, simulations of low-velocity impact and compression process of composite laminates with AL ply and different core material has been done. The simulation results show that softer core materials and AL ply with certain thickness can improve the residual compressive strength
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Perret, Adrien, Sébastien Mistou, Louis Etienne Denaud, Thierry Mollé, Claudia Veyrac, and Moussa Karama. "Numerical Modelling of a Composite Fuselage Manufactured by Liquid Resin Infusion." Applied Mechanics and Materials 62 (June 2011): 49–56. http://dx.doi.org/10.4028/www.scientific.net/amm.62.49.
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FUSCOMP (FUSelage COMPosite) is a Research & Development program which has received the label from the Aerospace Valley competitiveness cluster. It will lead to a test of a composite fuselage demonstrator manufactured by the Liquid Resin Infusion (LRI) process. LRI is based on the moulding of high performance composite parts by infusing liquid resin on dry fibers instead of prepreg fabrics. The study of this proof of concept is based on the TBM 850 airframe, a pressurized business turboprop aircraft currently produced by DAHER-SOCATA. Technical achievements will concern numerical methods and finite elements analysis to be used for the modelling of this aircraft composite fuselage structure. Actual industrial projects face composite integrated structure issues as a number of structures (stiffeners,...) are more and more integrated onto the skins of aircraft fuselage. Indeed the main benefit of LRI is to reduce assembly steps which lead to cycle time gain and thus cost reduction. In particular, infusing components and sub-components at the same time avoids riveting parts altogether. However it is necessary to validate the dimensioning of the studied composite structure.
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Guo, Jianchao, Yongbo Zhang, and Ke Chen. "Algorithm for Compression Design Allowable Determination of Composite Laminates with Initial Delaminations." Machines 9, no. 12 (November 24, 2021): 307. http://dx.doi.org/10.3390/machines9120307.
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With the increasing demands for detailed design of composite aircraft structures, the method of covering all damages with low design allowables cannot meet the current requirements for aircraft structure design. Herein, this paper proposes a novel algorithm for design allowable determination of composite laminates by combining the damage distribution with damage factor model of design allowable, so as to provide different structures with more accurate design allowables based on their initial damages. For the composite laminates with initial delaminations, a model describing the effect of delamination size and depth position on the compression design allowable is developed and the compression design allowable of different aircraft structures are individually determined by employing abundant initial delamination statistics. Compared with the design allowable offered by the single-point method, the design allowable based on the initial damage can be increased by at least 5% to 20%, greatly improving the economic benefits of the aircraft structures and providing an important support for the damage tolerance design of the composite structures.
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Sleesongsom, Suwin, Sumit Kumar, and Sujin Bureerat. "Multi-Objective Reliability-Based Partial Topology Optimization of a Composite Aircraft Wing." Symmetry 15, no. 2 (January 21, 2023): 305. http://dx.doi.org/10.3390/sym15020305.
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Reliability-based partial topology optimization (RBPTO) is a new approach for aircraft structural design; however, it brings computational complexity and makes aeroelasticity analysis quite challenging. Therefore, the present study proposed the multi-objective reliability-based partial topology optimization of a composite aircraft wing using a fuzzy-based metaheuristic (MRBPTOFBMH) approach. The objective is to obtain an optimal layout including partial topology and sizing of the aircraft wing structure. Here, an optimal aeroelastic structure is designed by taking into account the uncertain nature of material properties and the permitted transverse displacement. To increase computational efficiency in the design process, a non-probabilistic approach called a possibilistic safety index-based design optimization (PSIBDO) with fuzzy uncertainties is proposed to quantify the uncertainties due to aeroelastic and structural constraints. Various optimum partial topological shapes and sizing of aircraft wing structures with various PSI values in the range of [0.001, 1.0] have been obtained in a single optimization run. These outcomes, including deterministic and reliable optimal aircraft wing structures, demonstrate the high effectiveness of the proposed MRBPTOFBMH technique to alleviate the complexity of unconventional aircraft wing structure design. The findings also reveal the ease in cooperation of the suggested technique with a high-performance multi-objective evolutionary algorithm (MOEA) and its application in real-world multi-objective design optimization (MODO) problems with the least computational requirements against the traditional method’s multiple runs. Furthermore, the proposed methodology can generate potential aircraft wing structures in a range of m = [89.38–127.84] kg, and flutter speed = [285.61–632.78] m/s, that adhere to all the constraints requirements.
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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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Petersen, Jan, Alexander Kube, Sebastian Geier, and Peter Wierach. "Structure-Integrated Thin-Film Supercapacitor as a Sensor." Sensors 22, no. 18 (September 13, 2022): 6932. http://dx.doi.org/10.3390/s22186932.
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Today, aircraft composite structures are generally over-dimensioned to avoid catastrophic failure by unseen damages. This leads to a higher system weight and therefore an unwanted increase in greenhouse gas emissions. To reduce this parasitic mass, load monitoring can play an important role in damage detection. Additionally, the weight and volume of future aircraft structures can also be reduced by energy storing and load carrying structures: so-called power composites. In this study a novel method of combining both approaches for maximum weight reduction is shown. This is achieved by using power composites as load monitoring sensors and energy suppliers. Therefore, supercapacitors are integrated into fiber reinforced polymers and are then used to investigate the mechanical load influence. By using four-point bending experiments and in situ electrochemical impedance spectroscopy, a strong relation between the mechanical load and the electrochemical system is found and analyzed using a model. For the first time, it is possible to detect small strain values down to 0.2% with a power composite. This strain is considerably lower than the conventional system load. The developed model and the impedance data indicate the possibility of using the composite as an energy storage as well as a strain sensor.
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Журибеда, М. Н. "ВИДИ МЕТРОЛОГІЧНИХ ХАРАКТЕРИСТИК І СКЛАДУ РОБІТ З ЇХ ВИЗНАЧЕННЯ НА ОСНОВНИХ СТАДІЯХ ІСНУВАННЯ КОМПОЗИТНИХ КОНСТРУКЦІЙ АГРЕГАТІВ ПОВІТРЯНИХ СУДЕН ТРАНСПОРТНОЇ КАТЕГОРІЇ." Open Information and Computer Integrated Technologies, no. 93 (November 19, 2021): 146–57. http://dx.doi.org/10.32620/oikit.2021.93.09.
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It is shown that the development of the concept of metrological support for the creation of composite structures of aircraft aggregates of the transport category and their support at all stages of the existence of an aircraft should be based on the formation of a complex criterion for the effectiveness of the use of polymer composite materials. It is noted that the effectiveness of a structure made of polymer composite materials is provided by various methods, methods and technical means of metrology. The structure of a complex of studies aimed at developing the concept of metrological support is discussed, the first point of which is to analyze the types of metrological characteristics and the scope of work to determine them at the main stages of the existence of composite structures of aircraft aggregates of the transport category. Based on the analysis of numerous publications on the problem of metrological support of the main stages of creating technical products, the main types of measurements of the metrological characteristics of composite structures of aircraft aggregates of the transport category have been established, and the composition of the nomenclature of works on metrological support of the main stages of the existence of these structures has been determined. 12 main types of measurements of parameters have been identified, on which the whole variety of production physical quantities and the description of the properties and characteristics of structures of aircraft aggregates made of polymer composite materials are based. The composition of the main works on the metrological support of the four stages of the existence of the aircraft is revealed: design, production, operation and disposal of composite structures formed into systems of sequential blocks for performing these works. It is shown that the tasks of metrological support at the facility manufacturers should be solved during the technological preparation of serial production and testing of the installation series of products, and also take into account the peculiarities of aircraft operation and disposal of composite structural elements in terms of work safety and economic efficiency of their results. An enlarged sequence has been established for organizing work on metrological support for measuring the properties of composite structures of aircraft aggregates at aviation enterprises. The results presented in the first approximation provide a solution to practically important aspects of the problem under discussion.
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Aung, Phyo Wai, Oleg Tatarnikov, and Naing Lin Aung. "Approach to optimization of composite aircraft wing structure." IOP Conference Series: Materials Science and Engineering 971 (December 1, 2020): 022058. http://dx.doi.org/10.1088/1757-899x/971/2/022058.
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JINNO, Masaaki. "Fabrication Process of Composite Materials for Aircraft Structure." Kobunshi 57, no. 9 (2008): 770. http://dx.doi.org/10.1295/kobunshi.57.770.
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El Tom, Joy Della, and Gareth A. Vio. "Novel Wing Box Design." Applied Mechanics and Materials 553 (May 2014): 243–48. http://dx.doi.org/10.4028/www.scientific.net/amm.553.243.
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Composite materials offer the possibility to tailor a structure to have the desired stiffness distribution. Current aircraft design is yet to fully utilise and exploit these capabilities to improve an aircraft’s performance. In this study, a typical wing box structure is optimised with the aim of achieving a set of target aeroelastic parameters, while minimizing the mass. Focus is given to the model parameterisation to reduce the number of optimisation variables. A number of design variables will be considered and conclusions are drawn based on performance gains. Keywords: Optimisation, Aeroelasticity, Composites, NURBS.
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Khames, Mohamed, Ahmed Embaby, and Abdelrahman Agha. "Comparison between the Use of Aluminum and Composites in the Design of a Wing-Spar of an Airplane." Materials Science Forum 953 (May 2019): 95–100. http://dx.doi.org/10.4028/www.scientific.net/msf.953.95.
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In this paper a comparison between the results of the stress analysis of wing spar of metallic and composite materials has been done in order to assess how the use of composites modifies the weight and strength of the structure. To perform this assessment, the Ansys tutorial program was used to check our results for metallic and composite materials. This test was made for different arrangements of composite material to reach the best design of the composite spar to use it in manufacturing airplanes. There is a large amount of analysis and validation performed at the certification to demonstrate the Airworthiness requirements of aircraft structure so that, the composites have been subject of permanent interest of various specialists at the previous years. This secures the safe operation of the airplane under standard operating environments and also load conditions that the aircraft is intended to operate through its design service life. It is a trial to prove that the composites have a lot of advantages in the manufacturing process.
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Fu, Xinwei, Jiafu Wang, and Yiru Ren. "Research on high-temperature resistant resin matrix composites of hypersonic aircraft structure." Journal of Physics: Conference Series 2228, no. 1 (March 1, 2022): 012014. http://dx.doi.org/10.1088/1742-6596/2228/1/012014.
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Abstract The aircraft structure would be suffered high temperature during the hypersonic flight. To solve the problem of high temperature resistance of hypersonic aircraft, the mechanical properties of different structural materials at different temperatures are studied. The tensile strength and tensile modulus of structural steel, aluminum alloy, titanium alloy, resin matrix composites and polyimide composites are analyzed, and the performance of the materials at high temperature is compared. The results show that the properties of typical materials will decrease with the increase of temperature. The high-temperature mechanical properties of structural steel and aluminum alloy are poor, and the titanium alloy can withstand higher temperature. Polyimide resin composites can work at higher temperature for a long time compared with epoxy resin and bismaleimide resin composites, and it has more obvious advantages than titanium alloy at 400 °C. Polyimide resin composite has great potential to replace traditional materials as load-bearing structural material of hypersonic aircraft.
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Lusiak, Tomasz, Andrej Novák, Michal Janovec, and Martin Bugaj. "Measuring and Testing Composite Materials Used in Aircraft Construction." Key Engineering Materials 904 (November 22, 2021): 161–66. http://dx.doi.org/10.4028/www.scientific.net/kem.904.161.
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This paper is focused on the use of special composite materials for the construction of aircraft components. It focuses on measuring and testing the strength of reinforced composite materials used in damaged aircraft parts repairs. To determine the layer required to repair a part of the aircraft, it is necessary to know the strength limit of the material and its parts. The article describes experimental measurements of manufactured composite samples that have been subjected to tensile stress. Aim of the performed tensile tests was to determine the maximum tensile stress that the composite materials are able to transmit until they are damaged. Measurement determining the maximum stress level is important to ensure the required safety of the aircraft structure on which the composite structure was repaired.
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LINDE, PETER. "VIRTUAL TESTING OF STIFFENED COMPOSITE PANELS AT AIRBUS." International Journal of Structural Stability and Dynamics 10, no. 04 (October 2010): 589–600. http://dx.doi.org/10.1142/s0219455410003634.
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The steady increase of composite parts in civil aircraft over the last three decades has recently been followed by a radical increase of weight percentage composites in the structure. In the most recent long range aircraft under development by both Boeing and Airbus, most major structure components, not only of the wings but also of the fuselage, now consist of composites. This necessitates an increased use of efficient structural simulation capabilities. One important aspect of this is the virtual testing of shear compression panels at Airbus, which will be presented here. Having served well for Glare during the A380 development, it is currently undergoing considerable development to extend its capacity to composites. Summarized under the designation "Simulation of Panels in AirCraft", (SIMULPAC), this platform is here introduced and described in terms of functioning and methodology. It has played a major role in the initial A350 developments: in the first designs, during virtual testing of the configuration of new components and for predictions of the first real shear compression panels.
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Makwana, Alpesh H., and A. A. Shaikh. "Performance assessment and optimization of hybrid composite patch repair of aircraft structure." Multidiscipline Modeling in Materials and Structures 16, no. 5 (March 9, 2020): 887–913. http://dx.doi.org/10.1108/mmms-03-2019-0052.
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PurposeIn this article, a novel hybrid composite patch consisting of unidirectional carbon fiber and glass fiber is considered for repair of the aircraft structure. The purpose of this paper is to assess the performance of hybrid composite patch repair of cracked structure and propose an optimized solution to a designer for selection of the appropriate level of a parameter to ensure effective repair solution.Design/methodology/approachElastic properties of the hybrid composites are estimated by micromechanical modeling. Performance of hybrid composite patch repair is evaluated by numerical analysis of stress intensity factor (SIF), shear stress, and peel stress. Design of experiment is used to determine responses for a different combination of design parameters. The second-order mathematical model is suggested for SIF and peel stress. Adequacy of the model is checked by ANOVA and used as a fitness function. Multiobjective optimization is carried out with a genetic algorithm to arrive at the optimal solution.FindingsThe hybrid composite patch has maintained equilibrium between the SIF reduction and rise of the peel stress. The repair efficiency and repair durability can be ensured by selection of an optimum value of volume fraction of glass fiber, applied stress, and adhesive thickness.Originality/valueThe composite patch with varying stiffness is realized by hybridization with different volume fraction of fibers. Analysis and identification of optimum parameter to reduce the SIF and peel stress for hybrid composite patch repair are presented in this article.
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Szymański, Rafał. "Quality Control Process of Manufactured Composite Structures." Transactions on Aerospace Research 2017, no. 1 (March 1, 2017): 95–103. http://dx.doi.org/10.2478/tar-2017-0009.
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Abstract The paper includes a description of the composite material used in the aviation industry. It presents the technological development of composites in terms of their use in the most important elements of the aircraft structures, such as a spar and aircraft wing sheathing, which are subjected to high loads during operation. The type of the material implemented for production was listed and the most commonly occurred incompatibilities during the carbon pre-impregnate manufacture and transport were described. The manufacture diagram of composite elements with a polymer matrix was presented and the quality control system carried out at each mentioned stage (material storage, defrosting, cutting of dies, structure forming, polymerisation) was discussed. The methods of non-destructive tests of carbon laminates in a polymer matrix were also listed, describing the most effective of them, i.e. a method of ultrasonic tests. The conclusions were drawn and the development possibilities of ultrasonic tests both in terms of quality improvement and reduction of time for detecting incompatibilities in composite structures were described.
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Pechenyuk, Valery, Yuri Popov, and Irina Moiseeva. "ASSESSMENT OF THE LOAD-BEARING CAPACITY OF A COMPOSITE AIRCRAFT STRUCTURE CONSISTING OF A METAL-POLYMER COMPOSITE MATERIAL AND A CLASSICAL METAL." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 67 (2021): 85–95. http://dx.doi.org/10.15593/2224-9982/2021.67.08.
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The requirements for modern models of aviation equipment are constantly increasing, as a result of which it is necessary to look for new ways to solve the assigned engineering tasks through the use of new materials, new principles of manufacturing and assembly, as well as through an extraordinary approach to the design of the design of modern aircraft products. In this paper, the engineering methodology of power calculation and design of composite aircraft structures combining metal-polymer composite materials and metal materials is considered. As a composite structure under study, a fragment of an aircraft wing panel is considered, including a stringer made of a traditional structural material (metal) and a metal-polymer composite material skin attached to it. Metal- polymer composite material is a layered material consisting of metal sheets and layers of polymer composite material. Previously, in [1], the characteristics of the stress-strain state (SSS) of a single metal-polymer composite material and each layer in its package were investigated. In this paper, analytical and graphical dependences of the stress state of the elements of a composite structure on their ultimate deformations are obtained. The parameters of the composite panel of the wing, working on tension, and their effect on the stress-strain state, safety margin and load-bearing capacity are investigated. The obtained graphical dependences can be used for a preliminary assessment of the strength of an element of a composite structure at the stage of working out the design concept of an aircraft airframe assembly using a metal-polymer material.
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PELIN, George, Cristina-Elisabeta PELIN, Adriana STEFAN, Alexandra PETRE, and Alina DRAGOMIRESCU. "Mechanical behavior of sandwich structure composites for helicopters." INCAS BULLETIN 12, no. 4 (December 4, 2020): 155–62. http://dx.doi.org/10.13111/2066-8201.2020.12.4.14.
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The visible part of the floors of a commercial aircraft has long been a standard issue for virtually every commercial aircraft, mainly due to the weight of the materials from which they were made. Floor parts must provide mechanical strength and dimensional stability, while keeping the weight of the aircraft as low as possible for maximum efficiency. The design of the 787 Dreamliner and the Airbus A380 aircraft brought new opportunities in the use of the sandwich composite structure, mainly due to their light weight and high strength-to-weight ratio. Thus, this paper investigates the mechanical behavior of sandwich composite panels composed of two sides of carbon fiber laminate and Nomex honeycomb core obtained in the autoclave and developed under the RoRCraft CompAct grant. The technical approaches of this work are mainly focused on the compression behavior and especially on the compression after impact behavior of the hybrid sandwich composite structure, for defining and obtaining an optimal structure for the floors. These mechanical tests are decisive for such materials and have been performed in accordance with international ASTM standards.
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Shan, Ning, and Guo Heng. "New Technology Research of Nondestructive Testing for Aero Aircraft Composite Materials." Advanced Materials Research 279 (July 2011): 142–46. http://dx.doi.org/10.4028/www.scientific.net/amr.279.142.
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Composite materials have many advantages such as big specific strength, high specific stiffness, good disrepair safety characteristic, large area molding conveniently and easy to forming complex shape. It becomes important structural materials of aero aircraft equipment necessarily and is used widely in aviation industry. Composite materials components of aero aircraft with complex and delicate structure chronically work in harsh environment. Early testing of its key component’s minute defects has been an urgent and necessary task. In this paper, its damage model and characteristic are analyzed and studied. Considering the limitation of composite materials structure’s detection methods at present, a number of existing problems are presented and development directions are pointed out. Laser ultrasound detection technique, continuous distribution sensing technique and optical fiber sensing technique are studied. The method of damage detection of aero aircraft’s composite materials components is put forward based on the organic combination of the three techniques. The results show that the system can be used to detect multi-ultrasound signals of large composite materials structure. Its structure is simple. It has small bulk and low cost. It is characterized by easy realization.
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Wang, Yitao, Teng Zhang, Yuting He, Jiyuan Ye, Hanzhe Zhang, and Xianghong Fan. "Analysis of Damage of Typical Composite/Metal Connecting Structure in Aircraft under the Influences of High-Velocity Fragments." Applied Sciences 12, no. 18 (September 15, 2022): 9268. http://dx.doi.org/10.3390/app12189268.
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A two-stage light gas gun was used to conduct a high-velocity impact test on the aircraft’s typical composite/metal connecting structure (CFRP/AL). The battle damage simulations used for the CFRP/AL connecting structure were carried out under different intersection conditions. Then, the damage morphology and mechanism of high-velocity prefabricated spherical fragments on typical structures, the dynamic process of hyper-velocity impact, and the formation of debris clouds on the secondary damage morphology of different component structures were investigated. Next, based on the X-ray computerized tomography (CT), the typical mode of different damage areas and evolution trends of CFRP under high-velocity impacts were explored. Finally, a simulation model was established for battle damages of typical structures by combining FEM methods, and structural components’ energy dissipation capabilities for fragments under different velocities were analyzed. The study results provide a reference and model support for the rapid repair of battle-damaged aircraft and aircraft survivability design.
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Lin, Long Xiang, Hao Lei Mou, Jian Ren, and Tian Chun Zou. "The Static Strength Reliability Analysis of Composite Aircraft Structures." Applied Mechanics and Materials 488-489 (January 2014): 1215–18. http://dx.doi.org/10.4028/www.scientific.net/amm.488-489.1215.
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The static strength design of aircraft structure is the most basic design principles. The basic applicable conditions of composite structures static strength reliability analysis using the current methods were mentioned in this paper, and compliance analysis of these basic conditions was carried out. In addition, further studies were also conducted to research the influence of the number of full-scale structural specimens and environmental factors on the composite structures static strength reliability.
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Santoso, Djarot Wahju, and Kris Hariyanto. "COMPARISON OF SANDWICH COMPOSITE WING STRUCTURE WITH BALSA WOOD (CASE STUDY OF UAV AIRCRAFT FIXED WING VTOL VX-2)." Vortex 3, no. 2 (July 1, 2022): 98. http://dx.doi.org/10.28989/vortex.v3i2.1236.
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UAV aircraft with a fixed wing configuration with multi-rotor are aircraft capable of vertical take-off and landing (VTOL). In designing the wing structure of aircraft, the weight factor and the strength of the wing structure are factors that need to be considered. The use of sandwich composite materials on UAV wings is expected to be able to meet the requirements of UAV aircraft, namely having a light weight, having high rigidity and strength. In this study, a comparative analysis the strength of the sandwich composite wing structure with the balsa wood wing of the UAV VTOL VX-2 aircraft was carried out. The steps taken are to model the composite wing structure of sandwiches and balsa wood using CATIA. Performing the process of structural analysis using ANSYS software. Both half-span models are subjected to lift and vertical take-off loads. From the analysis results, the sandwich composite wing (glass fiber skin with styrofoam core) is stronger than the balsa wood wing structure under vertical take off loads. While the VTOL rods, upper and lower spars of the balsa wood wing model are stronger than the sandwich structure under lift loads, but overall the sandwich wing structure is stronger than the balsa wood wing
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Khalid, Salman, Hee-Seong Kim, Heung Soo Kim, and Joo-Ho Choi. "Inspection Interval Optimization for Aircraft Composite Tail Wing Structure Using Numerical-Analysis-Based Approach." Mathematics 10, no. 20 (October 17, 2022): 3836. http://dx.doi.org/10.3390/math10203836.
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Recently, there has been a tremendous increase in the use of fiber-reinforced composite (FRCP) in the aviation and aerospace industries due to its superior properties of high strength, stiffness, and low weight. The most important feature of implementing composite materials in aviation is their behavior under dynamic loads and resistance to fatigue. To predict the life of composite structures and optimize the inspection interval, it is essential to predict the damage behavior of composites. In this study, a model of fatigue delamination damage of composite specimens was first constructed using a finite element analysis (FEA)-based approach. The FEA modeling was verified through comparison with experimental specimen data, and the verified FEA model was applied to the composite material aircraft tail wing structure. In this case, a Monte Carlo simulation (MCS) was performed by building a response surface model while considering the uncertainty of the mechanical parameters. Through this process, the risk as a function of flight time could be quantitatively evaluated, and the inspection interval was optimized by selecting the combination with the lowest number of repeated inspections that met the permitted risk criteria.
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Pratama, Fandi Syafri. "STRUCTURE POWER AIRCRAFT FUSELAGE 5774 TRAINER." Vortex 2, no. 2 (June 30, 2021): 82. http://dx.doi.org/10.28989/vortex.v2i2.1010.
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The analysis process using software aims to determine whether an object or material is suitable for use or not before carrying out the manufacturing process. To find out whether the material is strong or not when applied to the aircraft, an analysis is carried out using the ABAQUS CAE 6.14 software. This software will show the stress value that occurs in the sandwich composite structure when it receives the load experienced by the aircraft.
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Ricco, Juan Tamassia, Rogerio Frauendorf Faria Coimbra, and Guilherme Ferreira Gomes. "Multiobjective optimization of the LASER aircraft wing’s composite structural design." Aircraft Engineering and Aerospace Technology 93, no. 6 (June 17, 2021): 995–1010. http://dx.doi.org/10.1108/aeat-06-2020-0113.
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Purpose Aircraft wings, one of the most important parts of an aircraft, have seen changes in its topological and design arrangement of both the internal structures and external shape during the past decades. This study, a numerical, aims to minimize the weight of multilaminate composite aerospace structures using multiobjective optimization. Design/methodology/approach The methodology started with the determination of the requirements, both imposed by the certifying authority and those inherent to the light, aerobatic, simple, economic and robust (LASER) project. After defining the requirements, the loads that the aircraft would be subjected to during its operation were defined from the flight envelope considering finite element analysis. The design vector consists of material choice for each laminate of the structure (20 in total), ply number and lay-up sequence (respecting the manufacturing rules) and main spar position to obtain a lightweight and cheap structure, respecting the restrictions of stress, margins of safety, displacements and buckling. Findings The results obtained indicated a predominance of the use of carbon fiber. The predominant orientation found on the main spar flange was 0° with its location at 28% of the local chord, in the secondary and main web were ±45°, the skins also had the main orientation at ±45°. Originality/value The key innovations in this paper include the evaluation, development and optimization of a laminated composite structure applied to a LASER aircraft wings considering both structural performance and manufacturing costs in multiobjetive optimization. This paper is one of the most advanced investigations performed to composite LASER aircraft.
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Park, Hyun Bum, Chang Duk Kong, and Kyung Sun Lee. "Investigation on Damage Tolerance of Carbon/Epoxy Laminate for Aircraft Structural Design." Key Engineering Materials 488-489 (September 2011): 460–63. http://dx.doi.org/10.4028/www.scientific.net/kem.488-489.460.
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In Korea, the KC-100, which is a small scale piston propeller general aviation aircraft, has been developed to establish a domestic certificate infrastructure and system through the BASA(Bilateral Aviation Safety Agreement) program by KAI(Korea Aerospace Industries, Ltd.). This aircraft adopted the whole composite structure concept for an environmental friendly aircraft through low fuel consumption due to structure weight reduction. However the carbon/epoxy composite structure, which is mainly used for this aircraft, is very weak against foreign object damage. Therefore the purpose of the damage tolerance design philosophy is to ensure that the aircraft can operate safely for a period of time with damage present within the airframe. This study is to investigate the residual compressive strength of the carbon/epoxy UD and fabric laminate due to impact damages. Through investigation on compressive strength, design allowable of carbon/epoxy laminate is determined by the experiment to address design criteria of the composite structure.
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Horton, B., Y. Song, D. Jegley, F. Collier, and J. Bayandor. "Predictive analysis of stitched aerospace structures for advanced aircraft." Aeronautical Journal 124, no. 1271 (November 18, 2019): 44–54. http://dx.doi.org/10.1017/aer.2019.137.
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ABSTRACTIn recent years, the aviation industry has taken a leading role in the integration of composite structures to develop lighter and more fuel efficient aircraft. Among the leading concepts to achieve this goal is the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept. The focus of most PRSEUS studies has been on developing an hybrid wing body structure, with only a few discussing the application of PRSEUS to a tube-wing fuselage structure. Additionally, the majority of investigations for PRSEUS have focused on experimental validation of anticipated benefits rather than developing a methodology to capture the behavior of stitched structure analytically. This paper presents an overview of a numerical methodology capable of accurately describing PRSEUS’ construction and how it may be implemented in a barrel fuselage platform resorting to high-fidelity mesoscale modeling techniques. The methodology benefits from fresh user defined strategies developed in a commercially available finite element analysis environment. It further proposes a new approach for improving the ability to predict deformation in stitched composites, allowing for a better understanding of the intricate behavior and subtleties of stitched aerospace structures.
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Zhang, Xiao Qing, and Xuan Liu. "The Damage of Sandwich Composite Structure of Aircraft Radome under Debris-Strike." Applied Mechanics and Materials 63-64 (June 2011): 515–18. http://dx.doi.org/10.4028/www.scientific.net/amm.63-64.515.
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The low and medium speed impact damage of sandwich composite structure of aircraft radome shield under debris-strike during takeoff and landing along runway is examined by numerical simulations, using nonlinear dynamic finite element analysis software LS-DYNA. For different impact velocities, the dynamic responses of aircraft radome shield are obtained and the damage in composite panel is clearly demonstrated. The relations of impact energy, maximum impact force and the damage state are analyzed. The simulation results can provide some references for the design of aircraft radome.
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Romano, Maria Grazia, Michele Guida, Francesco Marulo, Michela Giugliano Auricchio, and Salvatore Russo. "Characterization of Adhesives Bonding in Aircraft Structures." Materials 13, no. 21 (October 28, 2020): 4816. http://dx.doi.org/10.3390/ma13214816.
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Structural adhesives play an important role in aerospace manufacturing, since they provide fewer points of stress concentration compared to faster joints. The importance of adhesives in aerospace is increasing significantly because composites are being adopted to reduce weight and manufacturing costs. Furthermore, adhesive joints are also studied to determine the crashworthiness of airframe structure, where the main task for the adhesive is not to dissipate the impact energy, but to keep joint integrity so that the impact energy can be consumed by plastic work. Starting from an extensive campaign of experimental tests, a finite element model and a methodology are implemented to develop an accurate adhesive model in a single lap shear configuration. A single lap joint finite element model is built by MSC Apex, defining two specimens of composite material connected to each other by means of an adhesive; by the Digimat multi-scale modeling solution, the composite material is treated; and finally, by MSC’s Marc, the adhesive material is characterized as a cohesive applying the Cohesive Zone Modeling theory. The objective was to determine an appropriate methodology to predict interlaminar crack growth in composite laminates, defining the mixed mode traction separation law variability in function of the cohesive energy (Gc), the ratio between the shear strength τ and the tensile strength σ (β1), and the critical opening displacement υc.
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Prakasa, Lado Rislya. "THE UTILIZATION OF BAMBOO WASTE AS A NEW ALTERNATIVE MATERIAL IN THE AIRCRAFT FUSELAGE INTERIOR PANEL STRUCTURE." Vortex 2, no. 1 (April 19, 2021): 30. http://dx.doi.org/10.28989/vortex.v2i1.932.
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In the aircraft manufacturing industry, the strength and weight of the material is one of the important considerations in structural design. Composite material is a material composed of two or more forming materials, each of which has different mechanical properties. Aircraft structure in this era are 50 - 80% composed of glass or carbon fiber composite materials as reinforcement. Unfortunately, these fibers when recycled produce harmful CO gas, difficult to degrade naturally and cause itching when in contact with human skin. For this reason, environmentally friendly and strong fibers are needed to replace the role of glass or carbon fibers. Is a bamboo plant, which is abundant in Indonesia which is considered suitable as a substitute material. In this study, a mechanical test and descriptive analysis were carried out on the strength of the composite material with variations in the types of bamboo fibers apus, wulung, tutul and petung. These fibers are arranged with epoxy resin and hardener as a binding material (matrix). And each fiber will be arranged in 0 ° pattern to the matrix. Then each material with a different fiber type will be tested for tensile and bending to obtain the value of stress and strain that occurs at its maximum loading. And the result is the average tensile stress value (Mpa) composite material of apus bamboo is 75.95, wulung bamboo 49.92, petung bamboo 112.73, tutul bamboo 83.85. Then the average bending stress (Mpa) composite material of apus bamboo was 239.073, wulung bamboo 214.236, petung bamboo 249.67, tutul bamboo 272.79. With this result, bamboo fiber composites are considered to be able to replace the role of carbon or glass fibers, as an alternative composite material in some parts of the interior fuselage of aircraft panels. Keyword: Composites material, Matrix, Bamboo Fibers, Carbon and Glass Fibers, Stress and Strain.
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Zhang, Yongjie, Nuo Zhang, Bo Cui, and Lei Shi. "Research on the Design and Analysis Method of the Bird Collision-Resistant Structure of Electric Aircraft Composite Cap-Type-Reinforced Wall Panel-Filled Battery Integration." International Journal of Aerospace Engineering 2022 (July 1, 2022): 1–21. http://dx.doi.org/10.1155/2022/3768195.
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Compared with traditional energy aircraft, electric/hybrid aircraft show the advantages of environmental protection and low carbon and have been considered one of the most promising directions for the future development of the aviation industry. However, the battery (battery box) structure employed in electric/hybrid aircraft generally faces several problems (e.g., insufficient rigidity/strength and low structural load-bearing efficiency). In this study, the composite cap-type-reinforced wall plate structure commonly applied in electric aircraft is developed to fill the battery structure using the internal cavity of the cap type, which leads to the formation of an integrated structure type of a composite cap-type-reinforced wall plate filled battery. The basic static strength analysis of the integrated structure was conducted to measure its basic load-bearing capacity. To investigate the impact resistance of the integrated structure, a series of bird collision simulations were conducted to analyze the impact position, impact angle, impact speed, and other factors on the integrated structure and the design direction of the composite cap-type-reinforced wall plate-filled battery-integrated structure against bird collision was summarized.