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Journal articles on the topic 'Composite aircraft'

Author: Grafiati

Published: 4 June 2021

Last updated: 7 February 2022

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1

Min, Kyung Ju, and Ho Sung Lee. "Composite Materials Characterization for Aircraft Application." Materials Science Forum 857 (May 2016): 169–73. http://dx.doi.org/10.4028/www.scientific.net/msf.857.169.

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Various composite materials have been developed for many of aircrafts feature and it is important to establish the composite materials characterization procedure based on the airworthiness requirement. Since properties of composites are a function of the properties of the constituent phases, their relative amounts, and processing methods, the overall processing must be carefully evaluated. This paper presents a composite materials evaluation procedure for composite aircraft and provide the effective statistical allowable to be approved by airworthiness certification agency. All material, speci

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RUSU, Bogdan, Simona BLINDU BLINDU, Andra MICU, and Valentin SOARE. "Guidelines for Aircraft Composite Panels." INCAS BULLETIN 12, no. 1 (2020): 217–28. http://dx.doi.org/10.13111/2066-8201.2020.12.1.21.

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The objective of this paper is to give a general perspective and present some elementary steps for manufacturing aircraft sandwich panel composites. Composite materials have been widely used in high performance sectors of the aerospace and automotive industry, and there is considerable knowledge and confidence in their static, dynamic and crashworthiness properties. Sandwich composites are becoming more and more used in airframe structural design, mainly for their ability to substantially reduce weight while maintaining their high mechanical properties. The steps for manufacturing a sandwich c

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3

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

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4

Warren, Aaron, Rikard Heslehurst, and Eric Wilson. "Composites and MIL-STD-1530C." International Journal of Structural Integrity 5, no. 1 (2014): 2–16. http://dx.doi.org/10.1108/ijsi-02-2013-0002.

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Purpose – The purpose of this paper is to discuss changes to MIL-STD-1530C “Aircraft Structural Integrity Program” to account for the increased usage of composites in aircraft structures. Design/methodology/approach – The evolution of the Aircraft Structural Integrity Program is presented and the five tasks that comprise the program are assessed for compatibility with composite aircraft structures. Findings – This paper identifies a number of recommended changes to MIL-STD-1530C to ensure that the unique behaviour of composites is considered within the Aircraft Structural Integrity Program. Or

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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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Yu, Ze Liang, and Pu Xue. "Crashworthiness Study of Composite Fuselage Section." Key Engineering Materials 725 (December 2016): 94–98. http://dx.doi.org/10.4028/www.scientific.net/kem.725.94.

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Crashworthiness is one of the requirements for design of aircraft to ensure the safety of passengers on aircraft. With increasing applications of advanced composite in aircraft structures, study on the crashworthiness of composite fuselage is desirable and important. For this purpose, this paper investigates the influence of composites on crashworthiness of fuselage section. Firstly, model of fuselage section of aircraft is established. Skin, frame, stringer and stiffener are made of the composite T800/QY8911 or GLARE. Then, the crash responses subjected to vertical impact velocity of 9.14m/s

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Jacob, Amanda. "Composite aircraft and repair." Reinforced Plastics 55, no. 6 (2011): 3. http://dx.doi.org/10.1016/s0034-3617(11)70147-3.

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Marsh, George. "Training composite aircraft repairers." Reinforced Plastics 57, no. 6 (2013): 30–34. http://dx.doi.org/10.1016/s0034-3617(13)70187-5.

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9

Mun, Wai Chee, Ahmad Rivai, and Omar Bapokutty. "Design and Analysis of an Aircraft Composite Hinge Bracket Using Finite Element Approach." Applied Mechanics and Materials 629 (October 2014): 158–63. http://dx.doi.org/10.4028/www.scientific.net/amm.629.158.

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The use of composite materials in aircraft structures have been increasing for the past decade. The anisotropic and heterogeneous nature of composites remains a major challenge to the design and analysis of composite aircraft structures. Composite structures require a different design approach compared to the design of metallic structures. This paper aims to provide a step by step definitive guide to design and analyze composite structures using finite element approach. A simplified design model for the composite structural design was used to analyze an aircraft composite hinge bracket. The co

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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 com

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Ivanov, Dmitry Urevich, G. Grishanov, and V. Zaskanov. "Development Prospects of Production of Composite Materials in Russian Federation." Key Engineering Materials 746 (July 2017): 305–10. http://dx.doi.org/10.4028/www.scientific.net/kem.746.305.

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The paper analyzes the current state of production of composite materials in the Russian Federation. It is conceded the use of composites in aircraft design of various aircraft manufacturers. Concluded the feasibility of using composite materials in various industries. Peculiarities and prospects of prepreg application in the production of various parts are revealed.

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12

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 da

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13

Zhong, Mian, Bingwei Liu, Chen Li, et al. "Terahertz Spectroscopy and Imaging Detection of Defects in Civil Aircraft Composites." Journal of Spectroscopy 2020 (February 20, 2020): 1–8. http://dx.doi.org/10.1155/2020/2312936.

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Composite materials have increasingly become a high proportion of the structural weight of aircraft due to their excellent performances. Different types of damages may occur in the aircraft service period, which will bring potential safety risks to aircrafts. To investigate the defect damage detection and its spectral characteristics and imaging of carbon-fiber-reinforced polymer composite laminates, defects from the low-velocity impact damage in composites were measured by the THz time-domain reflection imaging system. Results show that there exists obvious THz spectral differences between th

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14

Nugroho, Gesang, Ali Ashar Rafsan Jani, Ridho Ramadhan Trio Sadewo, and Muhammad Satrio. "Manufacturing Process and Flight Testing of an Unmanned Aerial Vehicle (UAV) with Composite Material." Applied Mechanics and Materials 842 (June 2016): 311–18. http://dx.doi.org/10.4028/www.scientific.net/amm.842.311.

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The manufacturing process of lightweight and strong (Unmanned Aerial Vehicle) UAV and composite aircraft flight testing capability is described in this research. Nowadays, UAV development becomes more creative and high technology. Mapping and monitoring process from a UAV will be more effective and efficient. Mapping and monitoring process needs high durability UAV so that development with lightweight and strong material is needed. Lightweight technology is very suitable applied in the UAV technology. The composite material has many benefits for an aerodynamics world. The composite material wa

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15

Dragan, Krzysztof, and Piotr Synaszko. "In-Service Flaw Detection and Quantification in the Composite Structures of Aircraft." Fatigue of Aircraft Structures 2009, no. 1 (2009): 37–41. http://dx.doi.org/10.2478/v10164-010-0003-0.

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In-Service Flaw Detection and Quantification in the Composite Structures of Aircraft Taking into consideration the increased usage of composites for aircraft structures there is a necessity for gathering information about structural integrity of such components. During the manufacturing of composites as well as during in service and maintenance procedures there is a possibility for damage occurrence. There is a large number of failure modes which can happen in such structures. These failure modes affect structural integrity and durability. In this work modern approach for detection of composit

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16

Marks, Lena, and Gerhard Ziegmann. "Composite Design and Technology." Key Engineering Materials 425 (January 2010): 1–17. http://dx.doi.org/10.4028/www.scientific.net/kem.425.1.

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In recent years fibre reinforced plastics play a constantly improving role in a growing field of applications. From the chemical industry through sports equipments up to aircraft production - composites can be used in all these industrial areas. Although materials like glass fibre reinforced or carbon fibre reinforced plastics have a lot of applications in structural parts the knowledge about dimensioning and processing techniques is not exploited for the design of composite structures. If the parts and structures are not built for high performance applications such as in aircrafts, often prin

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17

MASAKI, Shoju. "Aircraft engines and composite materials." Journal of the Japan Society for Composite Materials 14, no. 1 (1988): 2–8. http://dx.doi.org/10.6089/jscm.14.2.

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18

IMAMURA, Tsugio, and Yasuhiro YAMAGUCHI. "Composite Materials for Aircraft Structures." Journal of the Japan Society for Aeronautical and Space Sciences 43, no. 495 (1995): 213–23. http://dx.doi.org/10.2322/jjsass1969.43.213.

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19

Khosravani, Mohammad Reza. "Composite Materials Manufacturing Processes." Applied Mechanics and Materials 110-116 (October 2011): 1361–67. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.1361.

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— Using Composite materials are growing more and more today and we have to use them in possible situation. One of the Composite materials applications is on the Airplane and aero space. Reduction of Airplane weight and more adaptability with nature are examples of benefit of using composite materials in aerospace industries. In this article process of manufacturing of composite materials and specially carbon fiber composite are explained. Advance composite materials are common today and are characterized by the use of expensive, high-performance resin systems and high-strength, high-stiffness

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20

Farrow, IR. "Fatigue of Composite Materials under Aircraft Service Loading." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 210, no. 1 (1996): 101–7. http://dx.doi.org/10.1243/pime_proc_1996_210_348_02.

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Fatigue damage accumulation and analysis methods are considered for composites and contrasted with metals. The failure of current analysis methods is illustrated and explained by the information missing in load idealization data. Detailed local strain operational monitoring with local strain fatigue data is proposed as a future approach to fatigue life assessment of composite materials under aircraft service loading.

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21

Balinova, Yu A., D. V. Graschenkov, A. A. Shavnev, et al. "High-temperature heat-shielding, ceramic and ceramic-metal composite materials for new-generation aviation equipment." Journal of «Almaz – Antey» Air and Defence Corporation, no. 2 (July 19, 2020): 83–92. http://dx.doi.org/10.38013/2542-0542-2020-2-83-92.

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This paper describes achievements of the All-Russian Scientific Research Institute of Aviation Materials in the field of creating high-temperature heat-shielding, ceramic and metal-ceramic composite materials. The advantages and prospects of applying the developed materials in the manufacturing of structural elements of aircraft and friction joints are discussed. The synthesis features and basic properties of metal-ceramic composite materials based on light alloys, refractory metal matrices, ceramic composite materials for use in heavily loaded structural elements of modern aircraft are presen

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22

Chen, Pu Woei, Quen Yaw Sheen, Harn Wen Tan, and Tai Sing Sun. "Fatigue Analysis of Light Aircraft Landing Gear." Advanced Materials Research 550-553 (July 2012): 3092–98. http://dx.doi.org/10.4028/www.scientific.net/amr.550-553.3092.

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Material fatigue is an important issue in structural design, especially for aircraft that undergo long-term alternating stress. Composite materials have been used extensively in aircraft because of their high specific strength ratio. Using composites made from different reinforcing materials and matrices through various manufacturing methods can yield different levels of performance when structures undergo long-term cyclic stress. Currently, composite materials are extensively used to build aircraft for large commercial carriers such as the Boeing 787 and the Airbus A380. Composite materials a

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23

Setlak, Lucjan, Rafał Kowalik, and Tomasz Lusiak. "Practical Use of Composite Materials Used in Military Aircraft." Materials 14, no. 17 (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

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24

Chen, Heng, Teng Fei Lei, Ying Liu, and Xu Wang. "Study of Infrared Thermograph NDT of Airplane Composites." Applied Mechanics and Materials 543-547 (March 2014): 1018–21. http://dx.doi.org/10.4028/www.scientific.net/amm.543-547.1018.

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In this paper, infrared thermal wave NDT techniques are used for aircraft composites. After the infrared image is sharpened and the temperature field is analyzed, aircraft composite material defects can be diagnosed. Experiments show that the infrared NDT techniques can detect defects in aircraft composite image. Images and first-order differential image can be presented more clearly outline the process and temperature variations. Defect size and depth can also be measured. The best experiments are designed for different materials. After several experiments of the precise temperature calibrati

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25

Gordiyenko, E. Yu, M. I. Glushchuk, Yu V. Fomenko, G. V. Shustakova, I. I. Dzeshulska, and Yu F. Ivanko. "Nondesructive Testing of Composite Materials of Aircraft Elements by Active Thermography." Science and innovation 14, no. 2 (2018): 37–47. http://dx.doi.org/10.15407/scine14.02.037.

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26

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 fin

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27

Chen, Pu Woei, Shu Han Chang, and Tsung Hsign Yu. "Analysis of the Dynamic and Static Load of Light Sport Aircraft Composites Landing Gear." Advanced Materials Research 476-478 (February 2012): 406–12. http://dx.doi.org/10.4028/www.scientific.net/amr.476-478.406.

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Composites have become extensively used in aircraft, including the latest Airbus A380 and Boeing 787 models. Due to their high specific strength ratio, the composites can help to reduce fuel consumption. For this reason, small business jets and light aircraft have begun to use composites in their fuselage designs. The main purpose of this study is to analyze the reaction of the composite landing gear of a light sport aircraft (LSA), under loading. Finite element analysis software was used to analyze and compare the static and dynamic loads on the LSA landing gear. Takeoff weight and sink speed

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Sidorina, A. I., A. M. Safronov, K. E. Kutsevich, and O. N. Klimenko. "CARBON FABRICS FOR AIRCRAFT PRODUCTS." Proceedings of VIAM, no. 12 (2020): 47–58. http://dx.doi.org/10.18577/2307-6046-2020-0-12-47-58.

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Current information about the nomenclature of woven reinforcing fillers for composite materials (CM) with a polymer matrix produced at production facilities of FSUE «VIAM», located on the basis of the Voskresensk experimental and technological center for special materials is presented. The main properties of manufactured carbon and hybrid fabrics, promising areas of their application, as well as the main properties of commercially produced and experimental composites based on polymer matrices and woven fillers of FSUE «VIAM» are presented. The directions of further expansion of the range of ma

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29

Radić, Vlado. "Composite materials application in aircraft industry." Vojnotehnicki glasnik 47, no. 6 (1999): 75–87. http://dx.doi.org/10.5937/vojtehg9904075r.

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30

Melton, Robert G. "A composite model of aircraft noise." Journal of Aircraft 22, no. 5 (1985): 443–44. http://dx.doi.org/10.2514/3.45145.

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31

Palumbo, Dan. "Novel sandwich composite aircraft sidewall architectures." Journal of the Acoustical Society of America 129, no. 4 (2011): 2416. http://dx.doi.org/10.1121/1.3587883.

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32

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

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33

Armstrong, Keith. "Civil Aircraft Composite Structure Repair Technology." Materials Technology 14, no. 4 (1999): 198–210. http://dx.doi.org/10.1080/10667857.1999.11752840.

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34

Rusin, M. Yu, V. V. Vasilenko, V. G. Romashin, P. A. Stepanov, I. G. Atroshchenko, and O. V. Shutkina. "Composite Materials for Aircraft Radioparent Domes." Refractories and Industrial Ceramics 55, no. 5 (2015): 391–95. http://dx.doi.org/10.1007/s11148-015-9732-5.

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35

Walczyk, Daniel F., Jean F. Hosford, and John M. Papazian. "Using Reconfigurable Tooling and Surface Heating for Incremental Forming of Composite Aircraft Parts." Journal of Manufacturing Science and Engineering 125, no. 2 (2003): 333–43. http://dx.doi.org/10.1115/1.1561456.

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The application of composites in the aircraft industry has increased significantly over the past few decades. With traditional composite laminate shaping, each layer is made to conform to the mold surface by hand before subsequent layers are added. This is a very labor- and time-intensive process. There is a great deal of interest in developing an automated process for forming composite parts with compound curvatures. The proposed composite forming process utilizes a computer-controlled, reconfigurable discrete element mold to incrementally form a compound curvature part shape from a flat lay-

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36

Zhang, Jian Yu, Feng Rui Liu, and Li Bin Zhao. "Mechanics Design of Connecting Frame in Aircraft Composite Cabin." Advanced Materials Research 97-101 (March 2010): 3362–65. http://dx.doi.org/10.4028/www.scientific.net/amr.97-101.3362.

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The mechanics behaviour of connecting frame in aircraft composite cabin under static load can be expatiated through its dangerous key components. Initial damage and ultimate strength of the key component are studied using progressive damage method. Based on the strength prediction technique, the effects of composites ply angle and the structural layout on structural initial damage and ultimate failure are discussed to exploit the potential composite structural load carry ability. The numerical results show the ply angle modification can provide 26.3% increase on initial failure stress and 14.1

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37

LINDE, PETER. "VIRTUAL TESTING OF STIFFENED COMPOSITE PANELS AT AIRBUS." International Journal of Structural Stability and Dynamics 10, no. 04 (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

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Vieira, Darli Rodrigues, and Alencar Bravo. "Feasibility of green composite aircraft wing projects for unmanned aircraft vehicles." International Journal of Sustainable Aviation 2, no. 3 (2016): 248. http://dx.doi.org/10.1504/ijsa.2016.080244.

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Bravo, Alencar, and Darli Rodrigues Vieira. "Feasibility of green composite aircraft wing projects for unmanned aircraft vehicles." International Journal of Sustainable Aviation 2, no. 3 (2016): 248. http://dx.doi.org/10.1504/ijsa.2016.10001108.

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40

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 demonstrat

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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 (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 cha

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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 (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 campa

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Maier, Raluca. "Study on Increasing Performances of Hybrid Composite Through Pull Out Compression Test Assessement." Materiale Plastice 57, no. 1 (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 researche

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Buonsanti, Michele, Fortunato Ceravolo, and Giovanni Leonardi. "Runway Debris Impact on Aircraft Composite Parts." Key Engineering Materials 754 (September 2017): 283–86. http://dx.doi.org/10.4028/www.scientific.net/kem.754.283.

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In this paper, we perform the behavior of aeronautics composite material subjected to a low energy impact. The proposed study considers the dynamic impact between a small piece of granular material and a large body of composite material. The principal aim is to simulate the impact of runway debris thrown up by the landing gear against an airplane structure. In the simulation, a CFRP composite panel impacted by granular particles at low speed is considered. The finite element analysis, initially on the macroscale and subsequently on the micro-scale, shows the delamination inside the composite a

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Yuan, Zheng, Robert Crouch, Jeff Wollschlager, and Jacob Fish. "Assessment of multiscale designer for fatigue life prediction of advanced composite aircraft structures." Journal of Composite Materials 51, no. 15 (2016): 2131–41. http://dx.doi.org/10.1177/0021998316665163.

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Multiscale Designer, developed by Altair, has been studied for its suitability for fatigue life prediction of advanced composite aircraft structures made of polymer matrix composites. The extensive experimental data provided by the Air Force Research Laboratory have been utilized to characterize the linear, non-linear, monotonic, and cyclic loading properties of micro-constituents comprising the polymer matrix composite system. The characterized properties have been then utilized to predict fatigue life and residual strength and stiffness of the aerospace grade polymer matrix composites.

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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,

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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 analyze

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Lee, Ho Sung, Seyoung A. Lee, and Ji Ung Choi. "Development of Materials Characterization Procedure for Composite Aircraft." Applied Mechanics and Materials 325-326 (June 2013): 46–49. http://dx.doi.org/10.4028/www.scientific.net/amm.325-326.46.

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It is required to characterize the materials according to the regulation in order to manufacture and fabricate components to be used for aircraft. The main purpose of this requirement is to determine the suitability of materials used for safe flight. Since the properties of composite materials are sensitive to the processing, characterization of composite materials has required very conservative methodology and therefore the whole process of characterization has been a redundant and time consuming process. This paper summarizes the efforts to adopt the composite materials characterization proc

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Larsen, M., R. G. Rowe, and D. W. Skelly. "Microstructural characterization of a Cr2Nb-Nb(Cr) microlaminate composite." Proceedings, annual meeting, Electron Microscopy Society of America 52 (1994): 706–7. http://dx.doi.org/10.1017/s0424820100171262.

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The thrust to weight ratio of an aircraft engine is limited by the density and elevated temperature performance of high temperature structural materials. Many material systems are currently under investigation as potential next generation engine materials. Microlaminate composites consisting of alternating layers of a ductile refractory metal for toughening and a high temperature intermetallic compound for elevated temperature strength have applicability in aircraft engine turbines. The lamellar thickness of such a composite must be small because the intrinsic defect size, a crack across the i

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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, Aeroel

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