Статті в журналах: "Aerospace Structure"

1

RAHIM, Erween, Takayuki OGAWA, Akihiko MIURA, Hiroyuki SASAHARA, Rei Koyasu, and Yasuhiro Yao. "3252 Ultrasonic Torsional Vibration Drilling of Aerospace Structure Material." Proceedings of International Conference on Leading Edge Manufacturing in 21st century : LEM21 2011.6 (2011): _3252–1_—_3252–4_. http://dx.doi.org/10.1299/jsmelem.2011.6._3252-1_.

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2

DOS SANTOS E LUCATO, S. L., R. M. MCMEEKING, and A. G. EVANS. "SMS-12: Shape Morphing Truss Structure for Aerospace and Marine Applications(SMS-II: SMART MATERIALS AND STRUCTURES, NDE)." Proceedings of the JSME Materials and Processing Conference (M&P) 2005 (2005): 30. http://dx.doi.org/10.1299/jsmeintmp.2005.30_4.

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3

Bajurko, Piotr. "Modelling of the Aerospace Structure Demonstrator Subcomponent." Transactions on Aerospace Research 2019, no. 1 (March 1, 2019): 37–52. http://dx.doi.org/10.2478/tar-2019-0004.

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Abstract Carbon-epoxy composite materials, due to their high strength in relation to mass, are increasingly used in the construction of aircraft structures, however, they are susceptible to a number of damages. One of the most common is delamination, which is a serious problem in the context of safe operation of such structures. As part of the TEBUK project, the Institute of Aviation has developed a methodology for forecasting the propagation of delamination. In order to validate the proposed method, an aerial structure demonstrator, modelled on the horizontal stabilizer of the I-23 Manager aircraft, was carried out. However, in order to carry out the validation, it was necessary to "simplify" the demonstrator model. The paper presents a numerical analysis conducted in order to separate from the TEBUK demonstrator model a fragment of the structure, which was used to study the delamination area, as an equivalent of the whole demonstrator. Subcomponent selection was carried out in several stages, narrowing down the analysed area covering delamination in subsequent steps and verifying the compliance of specific parameters with the same parameters obtained in a full demonstrator model. The parameters compared were: energy release rate values on the delamination front line and strain values in the delamination area. The numerical analyses presented in the paper were performed with the use of the MSC.Marc/Mentat calculation package. As a result of the analyses, a fragment of the structure was selected, which allows to significantly reduce the time and labour consumption of the production of the studied object, as well as to facilitate experimental research.

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4

Al-Madani, Ramadan A., M. Jarnaz, K. Alkharmaji, and M. Essuri. "Finite Element Modeling of Composites System in Aerospace Application." Applied Mechanics and Materials 245 (December 2012): 316–22. http://dx.doi.org/10.4028/www.scientific.net/amm.245.316.

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The characteristics of composite materials are of high importance to engineering applications; therefore the increasing use as a substitute for conventional materials, especially in the field of aircraft and space industries. It is a known fact that researchers use finite element programs for the design and analysis of composite structures, use of symmetrical conditions especially in complicated structures, in the modeling and analysis phase of the design, to reduce processing time, memory size required, and simplifying complicated calculations, as well as considering the response of composite structures to different loading conditions to be identical to that of metallic structures. Finite element methods are a popular method used to analyze composite laminate structures. The design of laminated composite structures includes phases that do not exist in the design of traditional metallic structures, for instance, the choice of possible material combinations is huge and the mechanical properties of a composite structure, which are anisotropic by nature, are created in the design phase with the choice of the appropriate fiber orientations and stacking sequence. The use of finite element programs (conventional analysis usually applied in the case of orthotropic materials) to analysis composite structures especially those manufactured using angle ply laminate techniques or a combination of cross and angle ply techniques, as well considering the loading response of the composite structure to be identical to that of structures made of traditional materials, has made the use of, and the results obtained by using such analysis techniques and conditions questionable. Hence, the main objective of this paper is to highlight and present the results obtained when analyzing and modeling symmetrical conditions as applied to commercial materials and that applied to composite laminates. A comparison case study is carried out using cross-ply and angle-ply laminates which concluded that, if the composition of laminate structure is pure cross-ply, the FEA is well suited for predicting the mechanical response of composite structure using principle of symmetry condition. On the other hand that is not the case for angle-ply or mixed-ply laminate structure.

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5

YAMAMOTO, Tetsuya. "Application of adhesive bonded structure on aerospace." Journal of the Surface Finishing Society of Japan 40, no. 11 (1989): 1203–6. http://dx.doi.org/10.4139/sfj.40.1203.

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6

Sainfort, P., Christophe Sigli, G. M. Raynaud, and P. Gomiero. "Structure and Property Control of Aerospace Alloys." Materials Science Forum 242 (January 1997): 25–32. http://dx.doi.org/10.4028/www.scientific.net/msf.242.25.

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7

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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8

Jiayu, Yao. "A method of coding for aerospace product quality DNA." MATEC Web of Conferences 151 (2018): 05006. http://dx.doi.org/10.1051/matecconf/201815105006.

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Aiming at the problem that the manufacturing process of our aerospace products is relatively discrete and the lack of appropriate quality monitoring and feedback mechanism, a method of coding for aerospace product quality DNA was proposed. Based on the structure of biological DNA and the theory of quality assessment, equipment diagnosis and quality traceability, the biological DNA structure was transformed into the structure of aerospace product quality DNA, and the concept of aerospace product quality DNA was defined, including the genetic and variation characteristics of aerospace product quality DNA. The coding rules of aerospace product quality DNA were designed, and the designed encoding rules are applied to the case of welding of wall panels in the manufacturing process of aerospace products. The results show that the coding method can monitor and feedback the core information related to quality in the manufacturing process of aerospace products.

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9

TADA, Yasuo. "Composite structure test facility in Natl. Aerospace Lab.." Journal of the Japan Society for Composite Materials 18, no. 1 (1992): 33–38. http://dx.doi.org/10.6089/jscm.18.33.

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10

Lee, Jong-Woong, Cheol-Won Kong, and Young-Shin Lee. "The Design of Aerospace Structure by Explosive Loading." International Journal of Aerospace and Lightweight Structures (IJALS) - 03, no. 04 (2013): 531. http://dx.doi.org/10.3850/s2010428614000075.

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11

Roemer, Michael. "A Hierarchical Reasoning Structure to Support Aerospace IVHM." SAE International Journal of Aerospace 4, no. 2 (October 18, 2011): 1176–83. http://dx.doi.org/10.4271/2011-01-2665.

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12

Furuya, Hiroshi, N. Kogiso, Saburo Matunaga, and K. Senda. "Applications of Magnesium Alloys for Aerospace Structure Systems." Materials Science Forum 350-351 (August 2000): 341–48. http://dx.doi.org/10.4028/www.scientific.net/msf.350-351.341.

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13

Dragan, Krzysztof, Michał Dziendzikowski, Artur Kurnyta, Michal Salacinski, Sylwester Klysz, and Andrzej Leski. "Composite Aerospace Structure Monitoring with use of Integrated Sensors." Fatigue of Aircraft Structures 2015, no. 7 (December 1, 2015): 12–17. http://dx.doi.org/10.1515/fas-2015-0002.

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Abstract One major challenge confronting the aerospace industry today is to develop a reliable and universal Structural Health Monitoring (SHM) system allowing for direct aircraft inspections and maintenance costs reduction. SHM based on guided Lamb waves is an approach capable of addressing this issue and satisfying all the associated requirements. This paper presents an approach to monitoring damage growth in composite aerospace structures and early damage detection. The main component of the system is a piezoelectric transducers (PZT) network integrated with composites. This work describes sensors’ integration with the structure. In particular, some issues concerning the mathematical algorithms giving information about damage from the impact damage presence and its growth are discussed.

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14

Si, Liang, and Zongfeng Li. "Online structural state assessment for aerospace composite structures using an acousto-ultrasonics-based multi-damage index identification approach." Structural Health Monitoring 19, no. 6 (January 21, 2020): 1790–807. http://dx.doi.org/10.1177/1475921719899334.

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The development of aerospace manufacturing has promoted the application of lightweight composite materials into aerospace structures. Although the aerospace composite structures possess numerous advantages, invisible internal structural damage such as delaminations induced by various external factors can significantly reduce the mechanical affordability, safety, and life-cycle of the structure. Therefore, it is of great significance to monitor and assess the health state and predict accurately the lifetime of aerospace composite structures. An acousto-ultrasonics-based multi-damage index identification approach is thus proposed in this study to identify and quantify possible multiple damage in thin-walled aerospace composite structures. In this approach, two indices for damage quantification were proposed: the energy and phase divergence indices. The energy index defines the reflected energy resulting from damage, and the phase divergence index defines the instantaneous phase variation of propagating waves due to damage. The two damage indices are obtained through the developed mode decomposition and spectral element analysis using sensor response signals collected by a transducer array placed onto the examined structure. Through a series of relevant experimental tests on the fabricated laminated composite panels with/without damage, the proposed acousto-ultrasonics-based multi-damage index identification approach was validated. The developed damage indices are competent to evaluate a structural health state in terms of damage quantification, and all of the validation results fell well in the prospected ranges. Moreover, it shows a linear and consistent trend between the variation of two damage indices and damage extents. Based on the particular relation, the linear regressive prediction functions were established separately regarding the two damage indices. They can be used to assess a structural health state due to the damage growth in real time. The proposed multi-damage index identification approach demonstrates its potential to serve as an online assessment tool to be aware of the reliability condition of a composite structure.

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15

Andrei - Daniel, VOICU. "Benefits of 3D printing technologies for aerospace lattice structures." Scientific Bulletin of Naval Academy XXIV, no. 1 (July 15, 2021): 8–16. http://dx.doi.org/10.21279/1454-864x-21-i1-001.

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The article makes a brief presentation of the latest 3D printing methods that are used for manufacturing aerospace lattice structures. Most 3D printing technologies are not fully deployed on the industrial scale of aerospace sector, but are rather used for rapid prototyping of components. One of the main potential applications is for them to offer a rapid solution for remote operations, where it is difficult to supply parts. Additive manufactured lattice structures are cellular structures based on biomimicry (inspired from nature lattice structures such as bones, metal crystallography, etc.), that possess many superior properties compared to solid materials and are ideal for fabricating aerospace structures mainly due to the mass reduction they introduce and the high strength-to-weight ratio. Their mechanical properties are defined by the infill percentage, the geometry of the cell structure and the material used in the manufacturing process.

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16

Skarka, Wojciech, and Andrzej Jałowiecki. "Automation of a Thin-Layer Load-Bearing Structure Design on the Example of High Altitude Long Endurance Unmanned Aerial Vehicle (HALE UAV)." Applied Sciences 11, no. 6 (March 16, 2021): 2645. http://dx.doi.org/10.3390/app11062645.

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In the aerospace industry, thin-layer composites are increasingly used for load-bearing structures. When designing such composite structures, particular attention must be paid to the development of an appropriate geometric form of the structure to increase the structure’s load capacity and reduce the possibility of a loss of stability and harmful aeroelastic phenomena. For this reason, the use of knowledge-based engineering support methods is complicated. Software was developed to propose and quickly evaluate a thin-layer load-bearing structure using generative modeling methods to facilitate development of the initial concept of an aerospace load-bearing structure. Finite Element Method (FEM) analysis verifies and improves such structures. The most important contributions of the paper are a methodology for automating the design of ultralight and highly flexible aircraft structures with the use of generative modelling, proposing and verifying the form of generative models for selected fragments of the structure, especially wings, and integration of the use of generative models for iterative improvement of structures using low- and middle-fidelity methods of numerical verification.

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17

Chen, Yisheng, Qianglong Wang, Chong Wang, Peng Gong, Yincheng Shi, Yi Yu, and Zhenyu Liu. "Topology Optimization Design and Experimental Research of a 3D-Printed Metal Aerospace Bracket Considering Fatigue Performance." Applied Sciences 11, no. 15 (July 21, 2021): 6671. http://dx.doi.org/10.3390/app11156671.

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In the aerospace industry, spacecraft often serve in harsh operating environments, so the design of ultra-lightweight and high-performance structures is a major requirement in aerospace structure design. In this article, a lightweight aerospace bracket considering fatigue performance was designed by topology optimization and manufactured by 3D-printing. Considering the requirements of assembly with a fixture for fatigue testing and avoiding stress concentration, a reconstructed model was presented by CAD software before manufacturing. To improve the fatigue performance of the structure, this article proposes the design idea of abstracting the practiced working condition of the bracket subjected to cycle loads in the vertical direction via a multiple load-case topology optimization problem by minimizing compliance under a variety of asymmetric extreme loading conditions. Parameter sweeping was used to improve the computational efficiency. The mass of the new bracket was reduced by 37% compared to the original structure. Both numerical simulation and the fatigue test were implemented to support the validity of the new bracket. This work indicates that the integration of the proposed topology optimization design method and additive manufacturing can be a powerful tool for the design of lightweight structures considering fatigue performance.

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18

Luo, Haitao, Peng Wang, Tingke Wu, and Haonan Wang. "DYNAMIC SIMULATION AND TEST ANALYSIS OF SPACE TRUSS AND LOAD STRUCTURE." International Journal of Engineering Technologies and Management Research 5, no. 3 (February 13, 2020): 123–33. http://dx.doi.org/10.29121/ijetmr.v5.i3.2018.183.

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The dynamic characteristics of aerospace products play a decisive role in environmental adaptability of products, because aerospace products are subjected to vibration environment during launching process. This paper describes the design of a space truss and the load structure, in order to get the dynamic characteristics, finite element modal analysis and modal test is done on the structural model, through correlation analysis to determine the degree of conformity of the finite element model with the experimental model. It is determined that the finite element mode of truss and load structure is similar to the test mode, the finite element model is acceptable; The dynamic simulation of the structure is carried out by the qualified finite element model, and the dynamic simulation results are verified by the vibration test; The method for obtaining the dynamic characteristics of aerospace products and the way of dynamic simulation for launching process is of great reference value for the design of aerospace products.

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19

Wang, Yu, Lei Liu, Yu Xing, and Zhenbo Yang. "Investigation of wing structure layout of aerospace plane based on the finite element method." Advances in Mechanical Engineering 9, no. 7 (July 2017): 168781401771370. http://dx.doi.org/10.1177/1687814017713701.

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The aerospace plane is an innovative kind of reusable aircraft, which is able to reach the low earth orbit flying like the conventional plane. Two kinds of aerospace plane wing structures are designed and parameterized for the delta wing with a strake, one of which is an equal percentage multi-web structure, and the other is a parallel multi-web structure. The two types of structure layouts were analyzed in the subsonic, transonic, supersonic, and hypersonic conditions using the finite element method. Contrasting the strength and stiffness characteristics, and estimating the structure weight, it demonstrated that the parallel multi-web wing had better performance than the equal percentage multi-web wing in terms of mechanical characteristic and weight. Then, based on the parameterized parallel multi-web wing, the thicknesses of webs, skins, and ribs were optimized to reduce the structure weight.

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20

Iwahori, Yutaka. "Overview of CFRP Structure Manufacturing Technology in Aerospace Industries." Seikei-Kakou 28, no. 12 (November 20, 2016): 484–89. http://dx.doi.org/10.4325/seikeikakou.28.484.

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21

Chen, Shuang, and Qing Feng Zhang. "Numerical Study on Structure Thermal Protection of Aerospace Plane." Advanced Materials Research 900 (February 2014): 814–17. http://dx.doi.org/10.4028/www.scientific.net/amr.900.814.

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The letter relying on the status of existing thermal protection system and existing flight parameters, appropriate metal thermal protection system being able to reproduced are designed; according to the distribution of heat-flow density we make certain the structure and thickness of the heat shield, structure of cooling bed and pressure of cooling air, velocity of flow and so on. The distributions of temperature of points on the nose and the inside of skin are calculated.

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22

R.A. NOVIKOV. "Organizational Structure of Forces Performing Combat Missions in Aerospace." Military Thought 26, no. 002 (June 30, 2017): 134–51. http://dx.doi.org/10.21557/mth.49108866.

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23

TADA, Yasuo. "Heat Resistant Structure in Aerospace Plane and Functionally Materials." Journal of the Japan Society for Aeronautical and Space Sciences 40, no. 461 (1992): 315–25. http://dx.doi.org/10.2322/jjsass1969.40.315.

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24

Nicholson, K. J., O. Dunbabin, T. Baum, and K. Ghorbani. "Characterisation of integrated microstrip lines in aerospace composite structure." Electronics Letters 53, no. 1 (January 2017): 36–38. http://dx.doi.org/10.1049/el.2016.3771.

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25

Sairajan, K. K., G. S. Aglietti, and K. M. Mani. "A review of multifunctional structure technology for aerospace applications." Acta Astronautica 120 (March 2016): 30–42. http://dx.doi.org/10.1016/j.actaastro.2015.11.024.

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26

Crump, D. A., J. M. Dulieu-Barton, and J. Savage. "The Manufacturing Procedure for Aerospace Secondary Sandwich Structure Panels." Journal of Sandwich Structures & Materials 12, no. 4 (June 10, 2009): 421–47. http://dx.doi.org/10.1177/1099636209104531.

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27

Fiorina, M., A. Seman, B. Castanie, K. M. Ali, C. Schwob, and L. Mezeix. "Spring-in prediction for carbon/epoxy aerospace composite structure." Composite Structures 168 (May 2017): 739–45. http://dx.doi.org/10.1016/j.compstruct.2017.02.074.

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28

Bari, Klaudio, and Lucie Bollenbach. "Spiderweb Cellular Structures Manufactured via Additive Layer Manufacturing for Aerospace Application." Journal of Composites Science 6, no. 5 (May 1, 2022): 133. http://dx.doi.org/10.3390/jcs6050133.

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With increasing the energy costs and aiming for fossil-free Europe, cellular structures could provide a cost-effective tool for saving fuel consumption in aircraft. To achieve this goal, a cellular structure topology is a rapidly growing area of research facilitated by developments in additive layer manufacturing. These low-density structures are particularly promising for their aerospace applications. In this paper, four cellular structure topologies are developed to serve as a vibration damper in small electric aircraft motor, we have compared their performance with the original motor holder in the aircraft. This paper introduces the roadmap of scaffolding concept design and provides a novel concept in vibration damping. Based on the FEA simulation, aluminium 6061T spiderweb-inspired lattices (weight 0.3473 g and porosity 84%) have proven to have the lowest natural resonance and highest yield strength to weight ratio compared to other scaffolding concepts.

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29

KRAEV, Viacheslav. "Experimental research of incipient turbulent flow frequency spectra in hydrodynamic unsteadiness." INCAS BULLETIN 13, no. 2 (June 4, 2021): 91–102. http://dx.doi.org/10.13111/2066-8201.2021.13.2.10.

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Hydraulic and heat transfer processes play a very important role in the design and prototyping of aerospace technology. Unsteady conditions are the peculiarity of mostly aerospace systems. Flow acceleration and deceleration may significantly affect the heat transfer and hydrodynamic process in channels of aerospace systems. For unsteady process modeling, a fundamental research of unsteady hydrodynamic turbulent flow structure., Moscow Aviation Institute National Research University (MAI) has been building unsteady turbulent flow structures since 1989. An experimental facility was designed to provide gas flow acceleration and deceleration. Experimental data of a turbulent gas flow structure during flow acceleration and flow deceleration are presented. The frequency spectra of axial and radial velocity pulsations are based on experimental data. The results of experimental turbulent flow research demonstrate the fundamental hydrodynamic unsteadiness influence on the flow structure. The main results of the flow acceleration and deceleration experimental research show that there are tangible differences from the steady flow structure. The analysis of unsteady conditions influence on the turbulent pulsations generation and development mechanisms is presented. The results show the unsteady conditions influence onto turbulent vortexes disintegration tempo. The present paper describes a method of experimental research, methodology of data processing and turbulent accelerated and decelerated flow spectra results.

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30

Hu, Zhi Qing, Ji Zhao, and Zeng Ming Feng. "FEM-Based Analysis of Micro-Structure Parameters for Roll Forming on Aluminum Alloy Sheet." Materials Science Forum 762 (July 2013): 763–68. http://dx.doi.org/10.4028/www.scientific.net/msf.762.763.

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Micro-structured surfaces with drag reduction, desorption, and excellent optical performance are widely used in the field of automotive, aerospace, marine applications. Therefore, the manufacturing of the micro-structure on the metal surface is of high impotance. Although the processing methods for micro-patterning of surfaces have progressed in recent years, micro-structure processing is still not used on large metal surfaces. In this paper, a method of roll forming micro-structure on the plate surface is proposed. A simulation model for micro-structure roll forming (MRF) was presented by using three-dimensional finite element method (FEM). The strain and stress, and the displacements caused by micro-structure were analyzed. The results provide theoretical guidance for the design of different micro-structures and the sequence of their processing.

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31

ZHAO, Ji-peng, Bin YU, Rui-jie OUYANG, Tian-ju MA, Sen-dong GU, Wen-bo YANG, and Yan-hui HOU. "Mechanism Study of Bi-Material COPV Structure Based on Composite Structure Design Theory." Journal of Physics: Conference Series 2289, no. 1 (June 1, 2022): 012016. http://dx.doi.org/10.1088/1742-6596/2289/1/012016.

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Abstract Composite over-wrapped pressure vessels (COPVs) are widely used in aerospace, aviation, army, Navy, nuclear industry and other military and civil fields because of their light weight, high strength, high reliability and safety, leak before burst (LBB) failure mode safety and many other characteristics. Because the aerospace field has very strict requirements on the weight of platform structure products including COPV, it is necessary to improve the mass efficient of COPV and achieve the characteristics of light weight and high strength. In this paper, through the optimization of composite material grid theory algorithm, the relationship between bidirectional stress and internal pressure of cylinder and dome of isotropic material is deduced. On this basis, the grid theory equations of bidirectional stress and internal pressure load of COPV cylinder and dome are deduced, and the wall thickness equations of ordinary rotating curve head, equal tension head and hemispherical head are proposed. According to the grid theory model of membrane stress of COPV cylinder, the author completed the grid theory algorithm derivation of elastic and plastic lined COPV. This paper is the exploration of composite dome structure analysis, which lays a foundation for the subsequent solution of composite dome grid theory.

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32

Żółtowski, Mariusz. "The Reliability Testing of Brick Infrastructure with Operating Modal Analysis / Badanie Niezawodności Infrastruktury Murowej Z Użyciem Operacyjnej Analizy Modalnej." Journal of KONBiN 25, no. 1 (March 1, 2013): 145–64. http://dx.doi.org/10.2478/jok-2013-0075.

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Abstract Modal analysis is widely used in the removal of defects caused by vibration of infrastructure, structure modification, updating the analytical model, or the control of the state and is used to monitor the vibration of structures in the aerospace and civil engineering mechanics from early 1990 began to pay close attention to the use of operational modal analysis (OMA) in a study of the existing building structures. In this case, the vibration exciter platforms, buildings, towers, bridges, etc. to force Operating (ambient). Here we measure only the response of the force generated by the environment. OMA is also very attractive for aerospace and mechanical engineering. This article presents the results of the existing building structure (reinforced concrete wall using operational modal analysis software and used to carry out the LMS and visualization of the results of such research.

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33

Dollah, N. A., M. R. Saad, and A. CheIdris. "Inflatable structure for aerospace application: Historical perspective and future outlook." Journal of Fundamental and Applied Sciences 9, no. 3S (January 17, 2018): 317. http://dx.doi.org/10.4314/jfas.v9i3s.26.

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34

Thankachen, Anoop, and Santosh kumar. "Design Optimization and Analysis of Rocket Structure for Aerospace Applications." International Journal of Engineering Trends and Technology 24, no. 6 (June 25, 2015): 286–91. http://dx.doi.org/10.14445/22315381/ijett-v24p251.

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35

Abdul Nassir, Azizah, Yee Hooi Min, and Syahrul Fithry Senin. "Computational Mechanics Analysis in Elevated Shell Platform Structures." Journal of Mechanical Engineering 18, no. 3 (September 15, 2021): 247–59. http://dx.doi.org/10.24191/jmeche.v18i3.15430.

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Shell structures are usually used in roof applications and aerospace structures. The advantage of these structures is not fully utilized in transmitting applied force. A thin-shell structure can be used for building construction and aerospace structures due to its lightweight nature. The township high load in this study refers to the high-speed airflow in the case of aerospace. This study was conducted to justify the feasibility of applying a thin-shell structure as an elevated shell platform for township foundations, where several different geometries were analyzed using finite element analysis (FEA) and artificial neural network (ANN). In the findings, all maximum stresses from different geometries are lower than the design value, thus verifying the feasibility of constructing a shell platform for heavy loading applications. The regression plots from the ANN output show that all geometries approached the value of 1, which means that the predicted ANN output and actual datasets of FEA are almost similar. From the ANN predicted output, the mean square error (MSE) was calculated. All the MSE values obtained from each geometry approached zero, indicating the analysis is precise and has a minimal error. Thus, this study has justified the feasibility of proposing elevated shells for township applications, which can be used as a reference in the design phase for future implementation.

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36

Манько, Т. А., И. А. Гусарова та Д. С. Калиниченко. "АЭРОКОСМИЧЕСКАЯ ТРАНСПОРТНАЯ СИСТЕМА – БУДУЩЕЕ УКРАИНЫ". System design and analysis of aerospace technique characteristics 27, № 2 (17 травня 2022): 84–89. http://dx.doi.org/10.15421/471926.

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The analytical review of the issue of the aerospace system creation in Ukraine and its importance is shown. Reusable aerospace system require to develop nonablating heat-proof and thermal protective structure.

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37

Zhu, Juntao, Tuanjie Li, Bo Li, Yaqiong Tang, Zuowei Wang, and Qingjuan Duan. "A Passive Vibration Control Method of Modular Space Structures Based on Band Gap Optimization." International Journal of Aerospace Engineering 2022 (September 9, 2022): 1–17. http://dx.doi.org/10.1155/2022/1862392.

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Modular space structure has become a research hotspot in the aerospace field. In the microgravity and weak damping space environment, modular space structures may continuously vibrate due to the transient excitation caused by satellite attitude adjustment or space debris impact, which will make the structure unstable. Therefore, a passive vibration control method based on band gap design is proposed for the modular space structures. Firstly, a modular spectral element model based on the super element is established, and the modular spectral element model is expanded into modular space structures. Then, band gap characteristics of the modular space structure are analyzed and optimized to improve the wave isolation ability. The numerical simulation shows that the elastic wave in the band gap can be effectively isolated and the band gap is significantly improved by optimizing structural parameters.

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Baur, Jeff, and Edward Silverman. "Challenges and Opportunities in Multifunctional Nanocomposite Structures for Aerospace Applications." MRS Bulletin 32, no. 4 (April 2007): 328–34. http://dx.doi.org/10.1557/mrs2007.231.

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AbstractOne important application of nanocomposites is their use in engineered structural composites. Among the wide variety of structural applications, fiber-reinforced composites for aerospace structures have some of the most demanding physical, chemical, electrical, thermal, and mechanical property requirements. Nanocomposites offer tremendous po tential to improve the properties of advanced engineered composites with modest additional weight and easy integration into current proc essing schemes. Sig nificant progress has been made in fulfilling this vision. In particular, nanocomposites have been applied at numerous locations within hierarchical composites to improve specific properties and optimize the multifunctional properties of the overall structure. Within this ar ticle, we review the status of nanocomposite incorporation into aerospace composite structures and the need for continued development.

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39

Lin, Xueqi, Bing Wang, Shuncong Zhong, Hui Chen, and Dianzi Liu. "Smart driving of a bilayered composite tape-spring structure." Journal of Physics: Conference Series 2403, no. 1 (December 1, 2022): 012042. http://dx.doi.org/10.1088/1742-6596/2403/1/012042.

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Abstract Composite tape-springs (CTS) structure has been applied to spatial developable structures due to its bistability. There is growing interest in smart driving of the CTS-based structures because of the limitations on the working environment. Here, we propose a detailed analysis of the smart driving of the CTS structure. This is achieved by using smart materials to develop a bilayered CTS intelligent structure: the smart material forms the active layer to generate stress/strain to drive the structure; the CTS layer acts as a passive layer where its intrinsic bistability, designability further enriches the diversity of intelligent morphing structures. A theoretical analytical model is developed to anticipate the bistability; the stability criteria are then determined to guide the intelligent morphing design. These will facilitate the future smart driving design of aerospace deployable structures.

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40

Torbali, Muhammet E., Argyrios Zolotas, and Nicolas P. Avdelidis. "A State-of-the-Art Review of Non-Destructive Testing Image Fusion and Critical Insights on the Inspection of Aerospace Composites towards Sustainable Maintenance Repair Operations." Applied Sciences 13, no. 4 (February 20, 2023): 2732. http://dx.doi.org/10.3390/app13042732.

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Non-destructive testing (NDT) of aerospace structures has gained significant interest, given its non-destructive and economic inspection nature enabling future sustainable aerospace maintenance repair operations (MROs). NDT has been applied to many different domains, and there is a number of such methods having their individual sensor technology characteristics, working principles, pros and cons. Increasingly, NDT approaches have been investigated alongside the use of data fusion with the aim of combining sensing information for improved inspection performance and more informative structural health condition outcomes for the relevant structure. Within this context, image fusion has been a particular focus. This review paper aims to provide a comprehensive survey of the recent progress and development trends in NDT-based image fusion. A particular aspect included in this work is providing critical insights on the reliable inspection of aerospace composites, given the weight-saving potential and superior mechanical properties of composites for use in aerospace structures and support for airworthiness. As the integration of NDT approaches for composite materials is rather limited in the current literature, some examples from non-composite materials are also presented as a means of providing insights into the fusion potential.

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41

Baaran, J., L. Kärger, and A. Wetzel. "Efficient prediction of damage resistance and tolerance of composite aerospace structures." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 222, no. 2 (February 1, 2008): 179–88. http://dx.doi.org/10.1243/09544100jaero278.

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The present work introduces efficient methodologies based on the finite-element method for a quick evaluation of damage resistance and damage tolerance of composite aerospace structures. Monolithic, stringer-stiffened structures, and sandwich structures are considered. The presented methodologies cover the simulation of the dynamic response of a structure during a low velocity impact event including the prediction of the internal non-visible or barely visible damage that develops during the impact. Additionally, methods for the prediction of the compression-after-impact strength are presented. In order to permit an accurate and efficient calculation of deformations and stresses in sandwich structures, special finite-element formulations have been developed. A comparison of simulation results with experimental data is presented for a two-stringer monolithic panel and for a honeycomb sandwich plate. The examples demonstrate that the presented methodologies can be used to quickly assess the damage tolerance of composite structures.

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42

Warner, Timothy. "Recently-Developed Aluminium Solutions for Aerospace Applications." Materials Science Forum 519-521 (July 2006): 1271–78. http://dx.doi.org/10.4028/www.scientific.net/msf.519-521.1271.

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Two principal approaches are available to materials’ engineers to improve the overall cost-weight balance of metallic airframe structures: improving alloy performance and optimising materials’ utilisation. Although both approaches have been successful in the past, they are most effective when applied concomitantly. The Aluminium industry has a long record of improving aerospace alloys’ performance. Nevertheless, even in apparently well-explored alloy systems such as the 7xxx family, products with improved damage tolerance-strength balances have recently been developed, thanks to an improved understanding of the optimum Zn-Mg-Cu combinations for the required property balances but also to developments in casting capability. Novel dispersoids and dispersoid combinations have enabled further improvements of the performance of existing alloy families. For example, appropriate Sc and Zr additions have a significant impact on the grain structure of 2xxx alloys and thus on performance. Another high potential approach for alloy performance improvements is the optimisation of Al-Cu-Li-(Mg-Ag-Zn) alloys. These so-called “third generation Al-Li alloys” were principally developed for military and space applications; in order to meet the demands of future commercial airframes, more damage tolerant variants are being developed. AA2198 and AA2050 are used to illustrate the potential of these higher damage tolerance Al-Cu-Li alloys. However, materials performance improvements are only part of the potential developments of metallic solutions for airframes. Further gains of a similar magnitude in component weight and cost can be achieved by applying new technologies and new design solutions to metallic structures. The future of metallic airframes will depend on the concomitant application of both these approaches.

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43

Steinchen, W., L. Yang, G. Kupfer, and P. Mäckel. "Non-destructive testing of aerospace composite materials using digital shearography." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 212, no. 1 (January 1, 1998): 21–30. http://dx.doi.org/10.1243/0954410981532108.

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Digital shearography, a laser interferometry technique in conjunction with the digital imaging processing, has the potential for identifying defects both in small- and large-scale structures. This paper will focus on the recent development of digital shearography for non-destructive testing (NDT). With the improvement of the measuring methods and the development of a small and mobile measuring device in conjunction with a user-guided program, Shearwin, this laser inspection technique can be used easily in the environment of fieldwork. A few examples show its application in the aerospace industry for NDT of composites, e.g. GLARE panel, honeycomb structure and glass (or carbon)-fibre-reinforced plastics, etc.

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44

Langley, R. S., and N. S. Bardell. "A review of current analysis capabilities applicable to the high frequency vibration prediction of aerospace structures." Aeronautical Journal 102, no. 1015 (May 1998): 287–97. http://dx.doi.org/10.1017/s0001924000065325.

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AbstractMany situations arise in which aerospace structures are subjected to high frequency excitation, in the sense that the wavelength of the induced dynamic response is much shorter than the overall dimensions of the structure. The application of the conventional finite element method to this type of problem faces two difficulties: (i) the short wavelength of the structural deformation requires the use of many elements, which renders the method computationally expensive or even impracticable, and (ii) the response of the structure at high frequencies can be very sensitive to structural detail, and thus response predictions for an ‘ideal’ structure may differ significantly from the performance of the actual system. For a number of years research effort has been directed towards the development of alternative analysis methods for high frequency vibrations, and recent developments in this area are reviewed in the present paper. The methods considered are: (i) hierarchical versions of the finite element method, (ii) the dynamic stiffness method, (iii)periodic structure theory, (iv)statistical energy analysis and (v) wave intensity analysis.

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45

Brischetto, Salvatore. "Analysis of natural fibre composites for aerospace structures." Aircraft Engineering and Aerospace Technology 90, no. 9 (November 14, 2018): 1372–84. http://dx.doi.org/10.1108/aeat-06-2017-0152.

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Purpose The main idea is the comparison between composites including natural fibres (such as the linoleum fibres) and typical composites including carbon fibres or glass fibres. The comparison is proposed for different structures (plates, cylinders, cylindrical and spherical shells), lamination sequences (cross-ply laminates and sandwiches with composite skins) and thickness ratios. The purpose of this paper is to understand if linoleum fibres could be useful for some specific aerospace applications. Design/methodology/approach A general exact three-dimensional shell model is used for the static analysis of the proposed structures to obtain displacements and stresses through the thickness. The shell model is based on a layer-wise approach and the differential equations of equilibrium are solved by means of the exponential matrix method. Findings In qualitative terms, composites including linoleum fibres have a mechanical behaviour similar to composites including glass or carbon fibres. In terms of stress and displacement values, composites including linoleum fibres can be used in aerospace applications with limited loads. They are comparable with composites including glass fibres. In general, they are not competitive with respect to composites including carbon fibres. Such conclusions have been verified for different structure geometries, lamination sequences and thickness ratios. Originality/value The proposed general exact 3D shell model allows the analysis of different geometries (plates and shells), materials and laminations in a unified manner using the differential equilibrium equations written in general orthogonal curvilinear coordinates. These equations written for spherical shells degenerate in those for cylinders, cylindrical shell panels and plates by means of opportune considerations about the radii of curvature. The proposed shell model allows an exhaustive comparison between different laminated and sandwich composite structures considering the typical zigzag form of displacements and the correct imposition of compatibility conditions for displacements and equilibrium conditions for transverse stresses.

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Mohamed, Tamer Z. Fouad. "Structuring Knowledge Management in Aerospace Open Innovation Alliances Using Industrial Service Blueprinting." Applied Mechanics and Materials 629 (October 2014): 363–69. http://dx.doi.org/10.4028/www.scientific.net/amm.629.363.

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The paper aims to structure the knowledge management system (KMS) in aerospace alliances based on open innovation to foster industry diffusion and growth. Literature review discussed core questions, challenges and opportunities of Research and Development (R&D) collaboration in the aerospace industry where open innovation and crowdsourcing can be an effective and efficient solution. The paper eventually adopted Industrial Service Blueprinting (ISB) framework and proposed open innovation solutions for aerospace R&D alliances.

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Deng, Haoyu, Junpeng Zhao, and Chunjie Wang. "Bionic Design Method of a Non-Uniform Lattice Structure for a Landing Footpad." Aerospace 9, no. 4 (April 15, 2022): 220. http://dx.doi.org/10.3390/aerospace9040220.

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Due to its excellent performance and high design freedom, the lattice structure has shown excellent capabilities and considerable potential in aerospace and other fields. Inspired by the bamboo structure, a lattice cell configuration namely BCC4IZ is designed and a lattice alternative layout is obtained. Then, a design and modeling method for non-uniform lattice structures is proposed. Four designs of the landing footpad with different kinds of lattice cells are developed. A series of dynamic explicit finite element simulations were conducted to evaluate and compare the energy absorption and capacity of resisting impact deformation performance of different designs. The results show that the combination of the bionic design and the lattice structure can effectively improve the performance of the lattice-filled footpad. This study proves the feasibility and potential of application for bionic design in lattice structure.

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Cristina-Diana, BRATU, ONCESCU Ionut-Cosmin, DIMA Ion, and PETRE Alexandra Raluca. "The validation of an aerospace structure through the sine vibration analysis." INCAS BULLETIN 10, no. 2 (June 7, 2018): 145–56. http://dx.doi.org/10.13111/2066-8201.2018.10.2.14.

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D’Angelo, Gianni, and Salvatore Rampone. "Feature extraction and soft computing methods for aerospace structure defect classification." Measurement 85 (May 2016): 192–209. http://dx.doi.org/10.1016/j.measurement.2016.02.027.

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50

Kermanpur, A., P. D. Lee, M. McLean, and S. Tin. "Integrated modeling for the manufacture of aerospace discs: Grain structure evolution." JOM 56, no. 3 (March 2004): 72–78. http://dx.doi.org/10.1007/s11837-004-0040-7.

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