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Journal articles on the topic 'Aerospace Structure'

Author: Grafiati

Published: 14 March 2023

Last updated: 31 July 2025

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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

Bajurko, Piotr. "Modelling of the Aerospace Structure Demonstrator Subcomponent." Transactions on Aerospace Research 2019, no. 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 ai

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3

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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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

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5

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 (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

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6

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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7

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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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 qu

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9

Bai, Yan, Chuncheng Xiao, Zijian Wei, and Lan Yin. "Study on Structure health monitoring method of space vehicle based on PVDF piezoelectric film." Journal of Physics: Conference Series 2479, no. 1 (2023): 012022. http://dx.doi.org/10.1088/1742-6596/2479/1/012022.

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Abstract At present, health monitoring technology of large structures has been paid more and more attention, among which structure measurement system based on PVDF piezoelectric film sensor has been widely used in various fields. To solve the problem that large structural parts of aerospace are easy to be damaged, a load measurement system based on PVDF piezoelectric film sensor is built in this paper given the complex design structure of aerospace. A large cylinder of aerospace is taken as the test part, the stress state of structural parts is measured online, and the corresponding load value

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10

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 (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 ident

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11

Thomas, D. K. "Advanced Composites in Aerospace Engineering." Progress in Rubber and Plastics Technology 4, no. 4 (1988): 1–20. https://doi.org/10.1177/147776068800400401.

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The development of composites for use in airframe engineering received a major boost with the introduction of carbon fibres in the mid-60s. The exploitation of these materials in the UK aerospace industry focussed very sharply on application in primary, i.e. high load bearing, structure, and great emphasis was therefore placed on the production of material of the highest quality using well tried and tested fabrication routes. Establishing the necessary level of confidence in carbon fibre/epoxy resin composites as airframe structural materials also required an extensive and complex programme of

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12

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 (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 d

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13

Xu, Shuhong, Xiaojiao Yu, Yue Gao, Sicong Wang, and Lining Sun. "Mechanical Property Analysis of a Boom–Membrane Structure Used for Aerospace Technologies." Materials 17, no. 13 (2024): 3204. http://dx.doi.org/10.3390/ma17133204.

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Traditional deployable truss space structures previously had upper limits on their key indicators, such as the deployed area, folded ratio and total weight, and hence, the application of new extendable mechanisms with novel deployment types is desired. Foldable extendable tape spring booms made from FRP (fiber-reinforced polymer) laminate composites and their corresponding boom–membrane structures were invented in recent years to satisfy the needs of the large-scale requirements of spacecraft, especially for antennas, solar sails and solar arrays. This paper aimed to analyze the properties of

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14

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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15

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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16

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

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17

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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18

Chen, Yisheng, Qianglong Wang, Chong Wang, et al. "Topology Optimization Design and Experimental Research of a 3D-Printed Metal Aerospace Bracket Considering Fatigue Performance." Applied Sciences 11, no. 15 (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 a

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19

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 (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

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20

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 (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,

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21

Khan, Numan, Valerio Acanfora, and Aniello Riccio. "Non-Conventional Wing Structure Design with Lattice Infilled through Design for Additive Manufacturing." Materials 17, no. 7 (2024): 1470. http://dx.doi.org/10.3390/ma17071470.

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Lightweight structures with a high stiffness-to-weight ratio always play a significant role in weight reduction in the aerospace sector. The exploration of non-conventional structures for aerospace applications has been a point of interest over the past few decades. The adaptation of lattice structure and additive manufacturing in the design can lead to improvement in mechanical properties and significant weight reduction. The practicality of the non-conventional wing structure with lattices infilled as a replacement for the conventional spar–ribs wing is determined through finite element anal

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22

Andrei - Daniel, VOICU. "Benefits of 3D printing technologies for aerospace lattice structures." Scientific Bulletin of Naval Academy XXIV, no. 1 (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.),

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23

Wenhe, Liao, and Dai Ning. "Current status and challenges of lightweight design and manufacturing technology for aerospace structures." Scientific Insights and Discoveries Review 4 (October 14, 2024): 181–207. http://dx.doi.org/10.59782/sidr.v4i1.143.

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Lightweight technology refers to the technology of reducing the structural mass by optimizing materials, structures and manufacturing processes while meeting the requirements of structural performance. It has become one of the key technologies for the development of the new generation of aerospace equipment. This paper first analyzes the development history of lightweight technology. Secondly, from the perspectives of design principles, composition methods and optimization methods, three types of lightweight design methods are introduced: bionic structure design, cellular structure design and

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24

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 (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

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25

Haitao, Luo, Wang Peng, Wu Tingke, and Wang Haonan. "DYNAMIC SIMULATION AND TEST ANALYSIS OF SPACE TRUSS AND LOAD STRUCTURE." International Journal of Engineering Technologies and Management Research 5, no. 3 (2018): 123–33. https://doi.org/10.5281/zenodo.1216829.

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<strong><em>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 a

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26

Guo, Zhengjie, Yuting Ma, Tayyeb Ali, et al. "Enhanced Compressive Properties of Additively Manufactured Ti-6Al-4V Gradient Lattice Structures." Metals 15, no. 3 (2025): 230. https://doi.org/10.3390/met15030230.

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Lattice structures are widely used in the aerospace and biomedical fields, due to their lightweight, high specific strength, large specific surface area, good biocompatibility, etc. However, the balancing of the weight and the mechanical properties remains a challenge in designing lattice structures. Combining experiments and simulations, the present work first designs and evaluates the mechanical properties of uniform and gradient topology-optimized Ti-6Al-4V lattices with the same overall porosity of 84.27%, employing finite element simulations. Then, laser powder bed fusion technology is us

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27

Kausar, Ayesha, and Ishaq Ahmad. "Leading-Edge Polymer/Carbonaceous Nano-Reinforcement Nanocomposites—Opportunities for Space Sector." Advances in Materials Science 23, no. 4 (2023): 99–122. http://dx.doi.org/10.2478/adms-2023-0025.

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Abstract Carbonaceous or nanocarbon nano-reinforcement nanocomposites have been found as emergent candidates for aerospace industry. Consequently, the multifunctional nanocomposites have been fabricated using marvelous nanocarbon nanostructures like graphene, carbon nanotube, fullerene, carbon black, etc. Manufacturing techniques have also been engrossed for the formation of high performance engineering nanocomposites having fine strength, heat stability, flame resistance, and other space desired features. These practices include solution, in situ, and melt procedures, on top of specific space

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28

KRAEV, Viacheslav. "Experimental research of incipient turbulent flow frequency spectra in hydrodynamic unsteadiness." INCAS BULLETIN 13, no. 2 (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 p

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29

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 usi

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30

Bari, Klaudio, and Lucie Bollenbach. "Spiderweb Cellular Structures Manufactured via Additive Layer Manufacturing for Aerospace Application." Journal of Composites Science 6, no. 5 (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

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31

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

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32

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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33

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

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34

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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35

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

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36

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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37

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 (2009): 421–47. http://dx.doi.org/10.1177/1099636209104531.

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38

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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39

Jiang, Zihao, Renwen Chen, Hao Liu, and Boyu Zheng. "Study on fluid-structure interaction vibration characteristics of aerospace piping systems." Journal of Physics: Conference Series 2977, no. 1 (2025): 012039. https://doi.org/10.1088/1742-6596/2977/1/012039.

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Abstract This paper investigates the vibration characteristics of aircraft fuel pipelines under fluid-structure interaction conditions. A detailed analysis of the vibration modes of the aerospace engine piping system is conducted using simulation software, with a particular focus on the effects of clamp mounting methods, fluid type, and fluid flow rate on the vibration behavior of the piping. The research results demonstrate that the appropriate placement of clamps and optimal selection of fluid parameters play a crucial role in enhancing the stability and safety of the piping system. The find

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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 (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

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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 (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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42

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 (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 analys

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43

Chen, Mingtai. "A Redesigned Physical Laboratory Approach to Aerospace Engineering Structure Education." Laboratories 2, no. 1 (2025): 6. https://doi.org/10.3390/laboratories2010006.

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This paper presents a redesign of the MAE 372 Aerospace Structures Laboratory at North Carolina State University (NCSU), incorporating both traditional laboratory demonstrations and an integrated student project to enhance hands-on learning. The redesign aligns with Accreditation Board for Engineering and Technology (ABET)’s emphasis on engineering education that bridges theoretical learning and practical, real-world experiences. In the redesigned laboratory, students participate in four laboratory demonstrations focused on fundamental structural concepts, followed by a student-led project in

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44

Ferro, Carlo Giovanni, Sara Varetti, and Paolo Maggiore. "Experimental Evaluation of Mechanical Compression Properties of Aluminum Alloy Lattice Trusses for Anti-Ice System Applications." Machines 12, no. 6 (2024): 404. http://dx.doi.org/10.3390/machines12060404.

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Lattice structures have emerged as promising materials for aerospace structure applications due to their high strength-to-weight ratios, customizable properties, and efficient use of materials. These properties make them attractive for use in anti-ice systems, where lightweight and heat exchange are essential. This paper presents an extensive experimental investigation into mechanical compression properties of lattice trusses fabricated from AlSi10Mg powder alloy, a material commonly used in casted aerospace parts. The truss structures were manufactured using the additive manufacturing selecti

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IJRAME, Journal. "Vibration Control on a Thin Walled Aerospace Nosecone with Preload." International Journal of Research in Aeronautical and Mechanical Engineering 13, no. 5 (2025): 46–59. https://doi.org/10.5281/zenodo.15564396.

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This project explores the vibrational behavior (natural frequencies) of thin-walled aerospace structures, with a focus on optimizing nosecone design. It aims to enhance structural stability and reduce the risk of vibration induced failures, which are critical concerns in aerospace applications. The study begins with a detailed literature review and a careful selection of aerospace-grade materials, including composites and alloys known for their superior structural properties. Key geometrical parameters of the nosecone are optimized to improve performance. Using Design Modeler in ANSYS, a detai

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46

ZHAO, Ji-peng, Bin YU, Rui-jie OUYANG, et al. "Mechanism Study of Bi-Material COPV Structure Based on Composite Structure Design Theory." Journal of Physics: Conference Series 2289, no. 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 compo

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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 structur

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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 (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 h

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Li, Quankun, and Xingjian Jing. "A novel nonlinear vibration feature-based approach for evaluating bolt-loosening faults in aerospace structures." HKIE Transactions 30, no. 4 (2023): 13–21. http://dx.doi.org/10.33430/v30n4thie-2023-0011.

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Aerospace structures such as aircraft and satellites are frequently subjected to bolt-loosening faults in service, which will seriously affect structural integrity, reliability and safety. In this paper, the development of a novel approach based on nonlinear vibration features is presented to evaluate potential bolt-loosening faults in these structures. Firstly, the complex aerospace structure is decomposed into some simple T-type substructures based on structural configurations and features. Then, a general T-type multi-degree-of-freedom (MDOF) model simulating bolt-loosening faults and nonli

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Baur, Jeff, and Edward Silverman. "Challenges and Opportunities in Multifunctional Nanocomposite Structures for Aerospace Applications." MRS Bulletin 32, no. 4 (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 ha

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