Journal articles: 'Mechanical and aerospace'

1

Tennant, Roy. "Mechanical Surface Finishing in the Aerospace Industry." Aircraft Engineering and Aerospace Technology 64, no. 3 (March 1992): 4–14. http://dx.doi.org/10.1108/eb037216.

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Smith, Robert. "AEROSPACE SPACE: Report of the BINDT Aerospace Group." Insight - Non-Destructive Testing and Condition Monitoring 52, no. 3 (March 2010): 120–22. http://dx.doi.org/10.1784/insi.2010.52.3.120.

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Butenegro, José Antonio, Mohsen Bahrami, Yentl Swolfs, Jan Ivens, Miguel Ángel Martínez, and Juana Abenojar. "Novel Sustainable Composites Incorporating a Biobased Thermoplastic Matrix and Recycled Aerospace Prepreg Waste: Development and Characterization." Polymers 15, no. 16 (August 18, 2023): 3447. http://dx.doi.org/10.3390/polym15163447.

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Carbon fiber-reinforced polymer (CFRP) composite materials are widely used in engineering applications, but their production generates a significant amount of waste. This paper aims to explore the potential of incorporating mechanically recycled aerospace prepreg waste in thermoplastic composite materials to reduce the environmental impact of composite material production and promote the use of recycled materials. The composite material developed in this study incorporates a bio−based thermoplastic polymer, polyamide 11 (PA11), as the matrix material and recycled aerospace prepreg waste quasi-one-dimensionally arranged as reinforcement. Mechanical, thermal, and thermomechanical characterizations were performed through tensile, flexural, and impact tests, as well as differential scanning calorimetry (DSC) and dynamic mechanical analysis (DMA). Compared to previous studies that used a different recycled CFRP in the shape of rods, the results show that the recycled prepregs are a suitable reinforcement, enhancing the reinforcement-matrix adhesion and leading to higher mechanical properties. The tensile results were evaluated by SEM, and the impact tests were evaluated by CT scans. The results demonstrate the potential of incorporating recycled aerospace prepreg waste in thermoplastic composite materials to produce high-performance and sustainable components in the aerospace and automotive industries.

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Valenti, Michael. "Re-Engineering Aerospace Design." Mechanical Engineering 120, no. 01 (January 1, 1998): 70–72. http://dx.doi.org/10.1115/1.1998-jan-5.

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This article reviews that by integrating its CAD/CAM tools, Boeing’s Space Systems Unit hopes to enhance the quality of its products as it reduces both design- and manufacturing-cycle times. Sharper market competition led management to re-emphasize the practice and couple it with integrated CAD/CAM systems to provide a more supportive environment for concurrent engineering, thereby assuring the customer that cost, schedule, and quality goals would be met. This concept, called integrated product development (IPD), was launched in 1991. Boeing’s intention is to use the IPD strategy to reduce design-cycle time and manufacturing-cycle time as well as recurring costs. To support IPD, the Boeing designers developed electronic change control (ECC), an online system that enables engineers, technicians, manufacturers, and logisticians throughout the company to track and control engineering changes on a network of minicomputers, workstations, and desktops. Among the Unigraphics-based tools Boeing uses in IPD is the electronic development fixture (EDF), a three-dimensional digital model. EDF enables its users to electronically investigate fit, form, function, and interference detection.

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Randall, Jason P., Mary Ann B. Meador, and Sadhan C. Jana. "Tailoring Mechanical Properties of Aerogels for Aerospace Applications." ACS Applied Materials & Interfaces 3, no. 3 (March 2011): 613–26. http://dx.doi.org/10.1021/am200007n.

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Bhat, Aayush, Sejal Budholiya, Sakthivel Aravind Raj, Mohamed Thariq Hameed Sultan, David Hui, Ain Umaira Md Shah, and Syafiqah Nur Azrie Safri. "Review on nanocomposites based on aerospace applications." Nanotechnology Reviews 10, no. 1 (January 1, 2021): 237–53. http://dx.doi.org/10.1515/ntrev-2021-0018.

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Abstract Advanced materials were used and are being implemented in structural, mechanical, and high-end applications. Contemporary materials are used and being implemented in structural, mechanical, and high-end applications. Composites have several major capabilities, some of them being able to resist fatigue, corrosion-resistance, and production of lightweight components with almost no compromise to the reliability, etc. Nanocomposites are a branch of materials within composites, known for their greater mechanical properties than regular composite materials. The use of nanocomposites in the aerospace industry currently faces a research gap, mainly identifying the future scope for application. Most successes in the aerospace industry are because of the use of suitable nanocomposites. This review article highlights the various nanocomposite materials and their properties, manufacturing methods, and their application, with key emphasis on exploiting their advanced and immense mechanical properties in the aerospace industry. Aerospace structures have used around 120,000 materials; herein, nanocomposites such as MgB2, multi-walled carbon nanotubes, and acrylonitrile butadiene styrene/montmorillonite nanocomposites are discussed, and these highlight properties such as mechanical strength, durability, flame retardancy, chemical resistance, and thermal stability in the aerospace application for lightweight spacecraft structures, coatings against the harsh climate of the space environment, and development of microelectronic subsystems.

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Yogesh, P., Santaji Krishna Shinde, Shyamlal C, R. Suresh kumar, Moti Lal Rinawa, G. Puthilibai, M. Sudhakar, Kassu Negash, and Rajesh S. "Mechanical Strengthening of Lightweight Aluminium Alloys through Friction Stir Process." Advances in Materials Science and Engineering 2022 (April 6, 2022): 1–10. http://dx.doi.org/10.1155/2022/8907250.

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The aerospace industries are focused on lightweighting with alloys having good tensile strength, fracture toughness, fatigue resistance, and corrosion resistance. The friction stir welding technology is one of the productive techniques in the aerospace industry to join such alloys with little ease. This paper deals with the composition of alloying elements that makes the structure lightweight and the impact of the precipitates evolved out of the selected alloying elements on the mechanical properties such as tensile strength and hardness of the joint in the aerospace alloys such as AA2xxx conventional aluminium alloys, AA2xxx lithium-based aluminium alloys, and AA7xxx aluminium alloys.

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Kovalev, I. V., N. A. Testoyedov, and A. A. Voroshilova. "Overview of IV International Conference on Advanced Technologies in Aerospace, Mechanical and Automation Engineering – MIST Aerospace-IV-2021." IOP Conference Series: Materials Science and Engineering 1227, no. 1 (February 1, 2022): 011001. http://dx.doi.org/10.1088/1757-899x/1227/1/011001.

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Abstract The overview describes the main directions and results of the IV International Conference on Advanced Technologies in Aerospace, Mechanical and Automation Engineering (MIST Aerospace-IV-2021) held in Krasnoyarsk on 10-11 December 2021. It gives the details about the participants and the proceedings. The purpose of the Conference is to share the experience of leading experts in the application of advanced science-intensive and information technologies in the aerospace industry, mechanical engineering and automation of technological processes and production.

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Morrison, Gale. "The Art of Aerospace Composites." Mechanical Engineering 121, no. 04 (April 1, 1999): 58–61. http://dx.doi.org/10.1115/1.1999-apr-4.

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This article reviews the advanced resin transfer molding (RTM) process of GKN Westland Aerospace. This process is refined enough, with customized equipment and a proprietary resin binding material, so that hundreds of different aircraft parts that would otherwise be heavier (made of titanium) are being produced for customers that include GE, Pratt & Whitney, Lockheed Martin, and Boeing. GKN is making five-axis, hollow vein, and integrated attachment nodes. It has produced carbon-fiber and resin components as thick as 3½ inches, and designs can combine what were many parts. Depending on the part and desired strength (in the desired directions), the fiber tow is woven in a variety of ways. For strength in mainly one direction, the engineers specify that 75 percent of the tow runs in one direction and just 25 percent of it is used to weave across it, for example. The next step in GKN’s advanced RTM evolution is a unihybrid composite that takes great loads in just one direction and can be made very thick, up to 3½ inches. A slightly less rigorous process has already been licensed, to a company in Mexico that produces a component for the Dodge Viper sports car.

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Salkind, Michael. "Aerospace materials research opportunities." Advanced Materials 1, no. 5 (1989): 157–64. http://dx.doi.org/10.1002/adma.19890010506.

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Shugurov, Artur. "Microstructure and Mechanical Properties of Titanium Alloys." Metals 11, no. 10 (October 12, 2021): 1617. http://dx.doi.org/10.3390/met11101617.

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Kausar, Ayesha, Ishaq Ahmad, M. H. Eisa, and Malik Maaza. "Graphene Nanocomposites in Space Sector—Fundamentals and Advancements." C 9, no. 1 (March 3, 2023): 29. http://dx.doi.org/10.3390/c9010029.

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Graphene is one of the most significant carbon nanomaterials, with a one-atom-thick two-dimensional nanostructure. Like other nanocarbons, graphene has been used as a polymer reinforcement. This review explores the impact of graphene and graphene-based nanocomposites on aerospace applications. The fabrication and indispensable features of graphene-derived nanocomposites have been considered. Numerous polymers and nanocomposites have been employed for aerospace systems such as reinforced thermosetting/thermoplastic polymers and epoxy/graphene nanocomposites. Moreover, graphene-modified carbon-fiber-based composites have been discussed for the space sector. Aerospace nanocomposites with graphene have been investigated for superior processability, structural features, morphology, heat stability, mechanical properties, flame resistance, electrical/thermal conductivity, radiation protection, and adhesion applications. Subsequently, epoxy and graphene-derived nanocomposites have been explored for heat/mechanically stable aerospace engineering structures, radiation-shielding materials, adhesives, coatings, etc.

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Jiang, Shang, Hongjin Liu, Zucheng Gu, and Qun Liu. "Mechanical Simulation Analysis of Aerospace High Reliability Electronic Equipment." Journal of Physics: Conference Series 2187, no. 1 (February 1, 2022): 012035. http://dx.doi.org/10.1088/1742-6596/2187/1/012035.

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Abstract In order to meet the requirements of high reliability, the structural performance of aerospace electronic equipment must meet the requirements of long-term stable work under severe mechanical conditions. The finite element model of electronic equipment from structural frame to printed circuit board and important components is established in detail. The mechanical analysis of the whole machine under the working conditions of modal analysis, random vibration and sinusoidal vibration is carried out, and the natural frequency, vibration mode and corresponding stress-strain data of each component are obtained. Through the PCB deformation check and structural strength check, the design safety margin of the whole machine is obtained. The analysis results provide the design basis for the structure finalization of aerospace electronic equipment, shorten the research and development cycle, reduce the experimental cost, and have important significance for the structure design of electronic equipment.

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Scarselli, G., Carola Corcione, F. Nicassio, and A. Maffezzoli. "Adhesive joints with improved mechanical properties for aerospace applications." International Journal of Adhesion and Adhesives 75 (June 2017): 174–80. http://dx.doi.org/10.1016/j.ijadhadh.2017.03.012.

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Antunes, D. M., V. Infante, and A. Reis. "Mechanical characterization and experimental performance of an aerospace adhesive." Engineering Failure Analysis 69 (November 2016): 43–56. http://dx.doi.org/10.1016/j.engfailanal.2016.04.010.

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Barile, C., C. Casavola, and F. De Cillis. "Mechanical comparison of new composite materials for aerospace applications." Composites Part B: Engineering 162 (April 2019): 122–28. http://dx.doi.org/10.1016/j.compositesb.2018.10.101.

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Livingstone, K. "Tribology in Aerospace." Tribology International 18, no. 3 (June 1985): 193–94. http://dx.doi.org/10.1016/0301-679x(85)90148-3.

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Lansdown, A. R. "Aerospace bearing technology." Tribology International 22, no. 4 (August 1989): 302–3. http://dx.doi.org/10.1016/0301-679x(89)90107-2.

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Kovalev, Igor V., and Anna A. Voroshilova. "Overview of the International Conference “Advanced Technologies in Aerospace, Mechanical and Automation Engineering – MIST: Aerospace-II”." IOP Conference Series: Materials Science and Engineering 734 (January 29, 2020): 011001. http://dx.doi.org/10.1088/1757-899x/734/1/011001.

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Waller, Matthew D., Sean M. McIntyre, and Kevin L. Koudela. "Composite Materials for Hybrid Aerospace Gears." Journal of the American Helicopter Society 65, no. 4 (October 1, 2020): 1–11. http://dx.doi.org/10.4050/jahs.65.042010.

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Hybrid steel-composite gears, which combine steel teeth with a fiber-reinforced polymer composite core, are a rapidly emerging technology for weight reduction in aerospace drivetrain systems. However, power transmission gears—and especially the requirement of rotorcraft gearboxes to operate under loss of lubrication—are a very challenging application for composite materials, due to the combination of mechanical and thermal loads. In this work, composite materials, including newly developed hybrid laminates featuring multiple grades of carbon fiber, are fabricated. Mechanical and thermal testing, along with ply-level finite element analysis, are employed to assess the suitability of these composite materials for hybrid aerospace gear applications. Particular focus is given to high-temperature epoxy and bismaleimide resins and to hybrid laminates reinforced by multiple grades of carbon fiber. This hybrid drivetrain technology would manifest significant weight reductions without compromising gear performance.

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Abrate, Serge. "Soft impacts on aerospace structures." Progress in Aerospace Sciences 81 (February 2016): 1–17. http://dx.doi.org/10.1016/j.paerosci.2015.11.005.

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S, Nikkisha, Rohan S, Pragyan Pattanaik Pattanaik, Ankit Kumar Mishra, and Dheva Darshini. "Review Study on Mechanical and Thermal Properties of Ceramic Materials for Future Aerospace Applications." Materials and its Characterization 1, no. 2 (December 1, 2022): 107–13. http://dx.doi.org/10.46632/mc/1/2/7.

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We are investigating the usage of ceramic materials in the aerospace sector. Ceramics are being used in a restricted number of aeronautical structural applications. Ceramics brittleness, lack of malleability, and expensive cost has been key deterrents to their widespread usage. We can determine the mechanical and thermal properties of this material by studying its mechanical and thermal properties such as strength, hardness, elasticity, grip and fracture, and thermal conductivity, diffusivity, thermal expansion, coefficient of expansion, and diffusivity. Some ceramic materials offer qualities that are important in aerospace applications, as well as the benefits and drawbacks of employing ceramic in the aerospace sector.

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Rameswara Reddy, Y. "Composite Laminates for Aerospace and Packaging Fields." Asian Review of Mechanical Engineering 12, no. 1 (June 21, 2023): 39–43. http://dx.doi.org/10.51983/arme-2023.12.1.3674.

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Composite materials have become increasingly popular and widely used in the present world due to their unique combination of properties that cannot be achieved by any single material. In the current study the mechanical properties of composite laminates (Jute, palm and banana fibers) were fabricated by varying groundnut husk and seashell powders quantities (5, 10, 15 and 20gms) in epoxy resin using hand layup technique. In according to the ASTM standards, a mixture of Epoxy (LY556) and Hardener (araldite) HY951 is used. The ratio of epoxy to hardener is 10:1. The material will be properly mixed for some time before being used to create laminates. Samples were fabricated with different compositions of jute, palm and banana fibers. Tensile, Compression properties of laminates were analyzed by testing composite laminates on universal testing machine. In this context the weight ratio of groundnut husk to seashell powder is 2:1. Analysis states that both the powders have impact on the mechanical properties of laminates. The impact of groundnut husk powder is slightly more on the laminates mechanical properties (tensile, compression) when related to seashell powder.

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McEnteggart, Ian. "Mechanical Testing of Automotive Components." AM&P Technical Articles 174, no. 3 (March 1, 2016): 21–23. http://dx.doi.org/10.31399/asm.amp.2016-03.p021.

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Abstract Successful use of composite materials requires a thorough understanding of their mechanical properties. Although a range of mechanical tests is required to obtain data, the aerospace industry has already developed, validated, and standardized these test methods. This article reviews some of key test methods used with composites.

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Fereiduni, Eskandar, Ali Ghasemi, and Mohamed Elbestawi. "Selective Laser Melting of Aluminum and Titanium Matrix Composites: Recent Progress and Potential Applications in the Aerospace Industry." Aerospace 7, no. 6 (June 11, 2020): 77. http://dx.doi.org/10.3390/aerospace7060077.

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Selective laser melting (SLM) is a near-net-shape time- and cost-effective manufacturing technique, which can create strong and efficient components with potential applications in the aerospace industry. To meet the requirements of the growing aerospace industrial demands, lighter materials with enhanced mechanical properties are of the utmost need. Metal matrix composites (MMCs) are extraordinary engineering materials with tailorable properties, bilaterally benefiting from the desired properties of reinforcement and matrix constituents. Among a wide range of MMCs currently available, aluminum matrix composites (AMCs) and titanium matrix composites (TMCs) are highly potential candidates for aerospace applications owing to their outstanding strength-to-weight ratio. However, the feasibility of SLM-fabricated composites utilization in aerospace applications is still challenging. This review addresses the SLM of AMCs/TMCs by considering the processability (densification level) and microstructural evolutions as the most significant factors determining the mechanical properties of the final part. The mechanical properties of fabricated MMCs are assessed in terms of hardness, tensile/compressive strength, ductility, and wear resistance, and are compared to their monolithic states. The knowledge gained from process–microstructure–mechanical properties relationship investigations can pave the way to make the existing materials better and invent new materials compatible with growing aerospace industrial demands.

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Maisuradze, Mikhail V., Maxim A. Ryzhkov, and Dmitriy I. Lebedev. "Mechanical Properties of a Mild-Alloy Steel for Aerospace Engineering." Defect and Diffusion Forum 410 (August 17, 2021): 221–26. http://dx.doi.org/10.4028/www.scientific.net/ddf.410.221.

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The features of microstructure and mechanical properties of the aerospace high strength steel were studied after the implementation of various heat treatment modes: conventional oil quenching and tempering, quenching-partitioning, austempering. The dependence of the mechanical properties on the tempering temperature was determined. The basic patterns of the formation of mechanical properties during the implementation of isothermal heat treatment were considered. The optimal heat treatment conditions for the studied steel were established.

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Boldyrev, Alexander I., Alexander A. Boldyrev, and Oleg N. Fedonin. "Processing of parts for aerospace engineering." MATEC Web of Conferences 224 (2018): 01096. http://dx.doi.org/10.1051/matecconf/201822401096.

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The article is devoted to combined processing techniques applied in modern industrial production for fabrication of aerospace engineering parts. The attainable process parameters are found for each technique. It is shown that electrochemical mechanical processing technique has maximal technological capability, this allows the increase of endurance strength and decrease of item mass.

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Ramachandran, Karthikeyan, Vignesh Boopalan, Joseph C. Bear, and Ram Subramani. "Multi-walled carbon nanotubes (MWCNTs)-reinforced ceramic nanocomposites for aerospace applications: a review." Journal of Materials Science 57, no. 6 (December 13, 2021): 3923–53. http://dx.doi.org/10.1007/s10853-021-06760-x.

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AbstractAdvances in the nanotechnology have been actively applied to the field of aerospace engineering where there is a constant necessity of high durable material with low density and better thermo-mechanical properties. Over the past decade, carbon nanotubes-based composites are widely utilised owing to its fascinating properties resulting in series of multidisciplinary industrial applications. Carbon nanotubes (CNTs) are rolled up sheets of carbon in nanoscale which offers excellent thermal and mechanical properties at lower density which makes them suitable reinforcement for composites in aerospace applications. Owing to its high Young’s modulus and chemically inert behaviour, CNTs are forefront of material research with applications varying from water purification to aerospace applications where applicational sector remains a mystery. Although there has been numerous research on the CNTs-based materials, there are only limited studies focusing on its utilisation for the field of aerospace engineering. As a result, in this review, we intend to cover the processing and synthesis techniques, thermal and mechanical properties as well as few industrial applications of CNTs-reinforced ceramic composites. Further, any potential development in additive manufacturing-based technique for fabricating CNT/ceramics and its applications in aerospace industries have been highlighted.

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Purushotham, Dr G., and Yathin K. L. "Study of Mechanical Behavior for Tamarind Shell Powder and Coconut Coir Fiber Epoxy Composite for Aerospace Application." International Journal of Trend in Scientific Research and Development Volume-3, Issue-1 (December 31, 2018): 941–49. http://dx.doi.org/10.31142/ijtsrd19159.

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Cavalier, Jean Claude, Isabelle Berdoyes, and Eric Bouillon. "Composites in Aerospace Industry." Advances in Science and Technology 50 (October 2006): 153–62. http://dx.doi.org/10.4028/www.scientific.net/ast.50.153.

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Since more than twenty five years, composite materials have been with continuously increasing spatial and aeronautical applications requirements. The thermostructural composites materials are of utmost importance for satisfying the needs of mechanical and thermal characteristics at very high temperature and in severe environments. This paper deals with a large variety of applications concerning the aerospace and nuclear applications like nozzles and hot gas valves for Solid Rocket Motor (SRM), brake disks for planes, aerospace turbine engine exhaust nozzles, thermal protection system for reentry vehicles, but also Divert and Attitude Control System (DACS) for interceptors, heat exchangers for hypersonic propulsion systems, plasma facing components for nuclear fusion applications and special components for nuclear fission applications. We will see that Carbon/Carbon and Ceramic Matrix Composites are leading candidate materials for these hightemperature structural applications. This lecture will identify the current state-of-the-art and new technological developments. A description of the main steps of the manufacturing processes will be made.

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Barrington, Norman A. "Past, present and future in UK aerospace." Strain 33, no. 4 (November 1997): 111–14. http://dx.doi.org/10.1111/j.1475-1305.1997.tb01057.x.

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Branco, Ricardo, Filippo Berto, and Andrei Kotousov. "Special Issue on “Mechanical Behaviour of Aluminium Alloys”." Applied Sciences 8, no. 10 (October 9, 2018): 1854. http://dx.doi.org/10.3390/app8101854.

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Aluminium alloys are the most common type of non-ferrous material utilised for a wide range of engineering applications, namely in the automotive, aerospace, and structural industries, among others. [...]

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Gomez-Gallegos, Ares, Paranjayee Mandal, Diego Gonzalez, Nicola Zuelli, and Paul Blackwell. "Studies on Titanium Alloys for Aerospace Application." Defect and Diffusion Forum 385 (July 2018): 419–23. http://dx.doi.org/10.4028/www.scientific.net/ddf.385.419.

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Since the development of the Ti54M titanium alloy in 2003, its application within the aerospace sector has gradually increased due to the combination of properties such as improved forgeability and machinability, low flow stress at elevated temperatures, and superplastic characteristics. However, for the successful exploitation of Ti54M a comprehensive understanding of its mechanical characteristics, microstructure stability, and superplastic behaviour is required. The superplastic forming of titanium alloys is characterised by high deformation at slow strain rates and high temperatures which influence the material microstructure, and in turn, determine the forming parameters. These mechanisms make the prediction of the material behaviour very challenging, limiting its application within the aerospace industry. Even though Ti54M has been commercially available for over 10 years, further studies of its mechanical and superplastic properties are still required with the aim of assessing its applicability within the aerospace industry as a replacement for other commercial titanium alloys. Therefore, in this work a study of the mechanical and superplastic properties of Ti54M, in comparison with other commercial titanium alloys used in the aerospace industry - i.e. Ti-6AL-4V, and Ti-6-2-4-2 - is presented. The final objective of this study, carried out at the Advanced Forming Research Centre (AFRC, University of Strathclyde, UK), is to obtain material data to calibrate and validate a model capable of estimating the behaviour and grain size evolution of titanium alloys at superplastic conditions.

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Goldin, Daniel S., Samuel L. Venneri, and Ahmed K. Noor. "The Great Out of the Small." Mechanical Engineering 122, no. 11 (November 1, 2000): 70–79. http://dx.doi.org/10.1115/1.2000-nov-1.

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This article discusses that a wealth of technological breakthroughs is likely to come from mimicking the interactions of biological systems and their response to the environment. The following next few decades will witness thinking, learning, evolvable aerospace systems. It will also see systems-on-a-chip, in which miniaturization allows all electronic systems of an aerospace vehicle (computer, memory, guidance, navigation, communications, power, and sensors) to fit on a tiny chip. Such aerospace systems cannot be realized with present technologies. The synergistic coupling of biotechnology, nanotechnology, and information technology with other leading edge aerospace technologies can produce breakthroughs in vehicle concepts and exploration missions, enable new science, and reshape our frame of reference for the future. The potential benefits of these technologies are pervasive and extend to several non-aerospace fields, such as high-performance computing and communications, land and sea transportation systems, health care, and advanced energy conversion and storage.

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Allen, J. E. "Aeronautics-1903; aerospace-2003; ? ? 2103." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 219, no. 3 (March 1, 2005): 235–60. http://dx.doi.org/10.1243/095441005x30252.

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The centenary of the first manned flight was a unique occasion permitting a rare opportunity to range far into both the past and the future. Most of aeronautics must inevitably be focussed on the near future and immediate actions. However, there are some very long-term underlying issues which are invisible from a day-to-day perspective, but which should not be overlooked as they can be used very often to guide decisions that might otherwise be unsound. In Part 1, the paper reviews the major breakthroughs that have impelled aeronautics along a startling trajectory of success, with some mention of the uncertain beginnings, when even Wilbur Wright considered that all his aerodynamic theories were in a muddle. In that spirit, in Part 2, some attempts are made to anticipate possible breakthroughs that might happen in the 21st century. However, aeronautics does not stand alone. Considerations, such as other transport modes, energy substitution, non-vehicular transport, and the consequences of major global political alignments, will be reviewed in order to seek new aeronautical challenges of the future. Some other long-term, but non-aeronautical engineering, initiatives relevant to the IMechE are introduced and discussed in the appendix

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Dorey, G., C. J. Peel, and P. T. Curtis. "Advanced Materials for Aerospace Structures." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 208, no. 1 (January 1994): 1–8. http://dx.doi.org/10.1243/pime_proc_1994_208_247_02.

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The role of materials in aerospace structures is discussed in terms of engineering performance, at affordable costs, for a variety of applications. Vehicle performance can be extended by improved materials performance and examples are given of new materials (alloys, polymer matrix composites, metal matrix composites and hybrid laminates), from the concept of new microstructures through development of new manufacturing processes to pilot scale production.

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Ponomarev, S. I. "Automation of the technology of connecting parts in the manufacture of aerospace products." Glavnyj mekhanik (Chief Mechanic), no. 5 (May 14, 2021): 24–32. http://dx.doi.org/10.33920/pro-2-2105-02.

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The paper describes the improvement of the technology of manufacturing parts and components of aerospace production using computer-aided design and technological process control. The theoretical foundations and algorithms for constructing the technological process of manufacturing parts and components of the aerospace industry using various methods of joining heat-resistant materials, for example, by diffusion welding, are designed on the basis of theoretical and experimental studies proposed by the author of the patented connection method «Method for joining a heat-resistant cobalt-based alloy with silicon nitride-based ceramics» and technological equipment «Installation for obtaining metal-ceramic products», as well as «Attribute database for creating technological processes for obtaining parts of aerospace production by diffusion welding» and «Attribute database of technological equipment, tools and devices for mechanical processing of aerospace production parts», registered in the register of databases of the Russian Federation. The research is conducted at the Department of Mechanical Engineering Technology of the Institute of Mechanical Engineering and Mechatronics of the Siberian State University of Science and Technology named after academician M.F. Reshetnev.

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Mahulikar, Shripad P., Hemant R. Sonawane, and G. Arvind Rao. "Infrared signature studies of aerospace vehicles." Progress in Aerospace Sciences 43, no. 7-8 (October 2007): 218–45. http://dx.doi.org/10.1016/j.paerosci.2007.06.002.

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Badcock, K. J., G. N. Barakos, R. M. Cummings, M. Platzer, N. Qin, C. H. Sieverding, and J. Wendt. "Bryan Richards: Contributions to aerospace engineering." Progress in Aerospace Sciences 101 (August 2018): 1–12. http://dx.doi.org/10.1016/j.paerosci.2018.07.002.

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Caiazzo, Fabrizia, Vittorio Alfieri, and Vincenzo Sergi. "Investigation on Mechanical Properties of Disk Laser Welded Aerospace Alloys." Advanced Materials Research 702 (May 2013): 128–34. http://dx.doi.org/10.4028/www.scientific.net/amr.702.128.

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The original micro structure of the base metal is significantly affected by a welding thermal cycle, irrespective of the type of the heat source. Hence, new phases and different grain size result in the welding bead. The tensile strength of the overall structure is affected in turn. Tensile tests are normally conducted to eventually test a square butt joint configuration. In conjunction, micro hardness is thought to be a good indicator to predict where the fracture would occur in the welded structure. Referring to common metal alloys for aerospace and considering a diode-pumped disk-laser source, the response of the base metal to the laser beam is investigated in this paper. Autogenous welding of aluminum alloy 2024, autogenous welding of titanium alloy Ti-6Al-4V and dissimilar welding of Haynes 188 with Inconel 718 are discussed, with respect to micro structure changes in the fused zone and in the heat affected zone. The failure mode is examined.

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WANG, Gang. "Microstructural Characteristics-based Mechanical Behavior of Aerospace Al-Cu Alloys." Journal of Mechanical Engineering 54, no. 1 (2018): 77. http://dx.doi.org/10.3901/jme.2018.09.077.

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Veerappan, G., M. Ravichandran, and S. Marichamy. "Mechanical properties and machinability of waspaloy for aerospace applications – review." IOP Conference Series: Materials Science and Engineering 402 (October 1, 2018): 012039. http://dx.doi.org/10.1088/1757-899x/402/1/012039.

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Duong, Loc, and Kazem Kazerounian. "Design Improvement of the Mechanical Coupling Diaphragms for Aerospace Applications#." Mechanics Based Design of Structures and Machines 35, no. 4 (November 8, 2007): 467–79. http://dx.doi.org/10.1080/15397730701673304.

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Froes, F. H. (Sam), Rod Boyer, and Bhaskar Dutta. "Additive Manufacturing for Aerospace Applications, Part II." AM&P Technical Articles 175, no. 6 (September 1, 2017): 18–22. http://dx.doi.org/10.31399/asm.amp.2017-06.p018.

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Abstract Fabrication of aerospace components using additive manufacturing (AM) has matured to the point where part microstructures and mechanical properties compare well with those of conventionally produced material. This article looks at characteristics of AM methods, post-processing of AM parts, and AM part properties.

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Froes, F. H. (Sam), Rod Boyer, and Bhaskar Dutta. "Additive Manufacturing for Aerospace Applications, Part I." AM&P Technical Articles 175, no. 5 (July 1, 2017): 36–40. http://dx.doi.org/10.31399/asm.amp.2017-05.p036.

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Abstract Fabrication of aerospace components using additive manufacturing (AM) has matured to the point where part microstructures and mechanical properties compare well with those of conventionally produced material. This article discusses the basics of AM, part design considerations, CAD models, and build and powder removal considerations.

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Comer, A. J., J. X. Dhôte, W. F. Stanley, and T. M. Young. "Thermo-mechanical fatigue analysis of liquid shim in mechanically fastened hybrid joints for aerospace applications." Composite Structures 94, no. 7 (June 2012): 2181–87. http://dx.doi.org/10.1016/j.compstruct.2012.01.008.

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Babaelahi, Mojtaba, and Mohammad Reza Raveshi. "Analytical efficiency analysis of aerospace radiating fin." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 228, no. 17 (March 11, 2014): 3133–40. http://dx.doi.org/10.1177/0954406214526963.

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The present article investigates heat transfer phenomenon in an aerospace radiating fin, analytically. Radiating extended surfaces are widely used to enhance heat transfer between primary surface and the environment. The performance of such a surface is significantly affected by variable thermal conductivity; especially in the case of large temperature differences happened in the actual aerospace applications. To study the effect of thermal conductivity variation, linear length-dependent function of thermal conductivity, is considered. In this study, two newest and popular analytical methods, differential transform method and optimal homotopy asymptotic method are used to evaluate the temperature profile and efficiency of radiating fin. For this purpose, after deriving and dimensionalizing the radiating fin heat transfer equation and briefly introducing these two methods, they are employed to solve the radiating fin problem. The obtained results are compared with the numerical ones to verify the accuracy of the proposed methods and choosing the better one between them, which is exclusive for this paper. Then, the effects of thermal conductivity and thermo-geometric radiating fin parameter on temperature profile and fin’s efficiency are completely discussed, which can help materials science researchers to design more compact and efficient radiating fin for using in aerospace and satellite applications.

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Das, D. K., and Jit Sarkar. "Graphene–magnesium nanocomposite: An advanced material for aerospace application." Modern Physics Letters B 32, no. 06 (February 28, 2018): 1850075. http://dx.doi.org/10.1142/s0217984918500756.

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This work focuses on the analytical study of mechanical and thermal properties of a nanocomposite that can be obtained by reinforcing graphene in magnesium. The estimated mechanical and thermal properties of graphene–magnesium nanocomposite are much higher than magnesium and other existing alloys used in aerospace materials. We also altered the weight percentage of graphene in the composite and observed mechanical and thermal properties of the composite increase with increase in concentration of graphene reinforcement. The Young’s modulus and thermal conductivity of graphene–magnesium nanocomposite are found to be [Formula: see text][Formula: see text]165 GPa and [Formula: see text][Formula: see text]175 W/mK, respectively. Nanocomposite material with desired properties for targeted applications can also be designed by our analytical modeling technique. This graphene–magnesium nanocomposite can be used for designing improved aerospace structure systems with enhanced properties.

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Jadhav, Prakash. "Passive Morphing in Aerospace Composite Structures." Key Engineering Materials 889 (June 16, 2021): 53–58. http://dx.doi.org/10.4028/www.scientific.net/kem.889.53.

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Attempts to add the advanced technologies to aerospace composite structures like fan blade have been on in recent times to further improve its performance. As part of these efforts, it has been proposed that the blade morph feasibility could be studied by building and optimizing asymmetric lay up of composite plies inside the blade which will help generate enough passive morphing between max cruise and climb conditions of the flight. This will have a direct efficiency (Specific Fuel Consumption) benefit. This research describes the various ideas that were tried using in house-developed lay-up optimization code and Ansys commercial software to study the possibility of generating enough passive morphing in the blade. In the end, this report concludes that the required degree of passive morphing could not be generated using various ideas with passive morphing technology and only up to some extent of morphing is shown to be feasible using the technologies used here.

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Matsui, Junichi. "Polymer matrix composites (PMC ) in aerospace." Advanced Composite Materials 4, no. 3 (January 1995): 197–208. http://dx.doi.org/10.1163/156855195x00014.

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Journal articles on the topic 'Mechanical and aerospace'

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