Relevant bibliographies by topics / Mechanical and aerospace

Academic literature on the topic 'Mechanical and aerospace'

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Published: 7 September 2023

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Journal articles on the topic "Mechanical and aerospace"

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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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Dissertations / Theses on the topic "Mechanical and aerospace"

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Moore, Gareth Edward. "Electro-mechanical interactions in aerospace gas turbines." Thesis, University of Nottingham, 2013. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.768249.

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The provision of electrical power on modern aircraft is a necessary and growing aspect of a gas turbine's function. The replacement of traditional pneumatic, hydraulic and mechanical systems with electrical equivalents means that electricity is now the dominant means of power distribution on aircraft. However, the electrical loads seen on aircraft present challenges, as they are time varying and are often non-linear. This is particularly true for loads such as radar. The aviation industry has adopted the term More Electric Aircraft (MEA) to describe the latest generation of aircraft with a high reliance on electrical power. There is potential for significant interaction between the transient variation of electrical loading and the gas turbine (both drive-train and engine core). Engine testing and initial simulation work support this view. Understanding of this phenomenon must now be furthered through modelling and testing. This thesis presents simulation models of a transmission system and generator interface, which provides a useful kernel for a modelled system to assess electro-mechanical interaction. This is extended to multi-domain simulation work through the successful interlinking of transmission, generator and an electrical load model. These models have been validated, at a domain level, against analytical expressions, and also as a complete electro-mechanical system against test data. To allow more control over test conditions, an electro-mechanical test rig is designed and constructed. The data from the test rig is analysed and compared to modelled results. This thesis also presents potential mitigation actions for avoiding unwanted electro-mechanical interactions during electrical load transients. A method of extracting transient mechanical torque information from a gas turbine's electrical generator's terminal quantities is included. At a system level, the simulation work in this thesis potentially enables the development of future designs with improved power systems integration throughout the entire airframe. High level control could allow optimisation of the power conversion process between gas turbine spool and electrical systems, with increased intelligence in the movement of power between components.
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Stimac, Andrew K. (Andrew Kenneth) 1977. "Precision navigation for aerospace applications." Thesis, Massachusetts Institute of Technology, 2004. http://hdl.handle.net/1721.1/16676.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2004.
Vita.
Includes bibliographical references (p. 162). Includes bibliographical references (p. 162).
This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
Navigation is important in a variety of aerospace applications, and commonly uses a blend of GPS and inertial sensors. In this thesis, a navigation system is designed, developed, and tested. Several alternatives are discussed, but the ultimate design is a loosely-coupled Extended Kalman Filter using rigid body dynamics as the process with a small angle linearization of quaternions. Simulations are run using real flight data. A bench top hardware prototype is tested. Results show good performance and give a variety of insights into the design of navigation systems. Special attention is given to convergence and the validity of linearization.
by Andrew K. Stimac.
S.M.
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Cauberghs, Julien. "Out-of-autoclave manufacturing of aerospace representative parts." Thesis, McGill University, 2012. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=106593.

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The use of carbon fibre reinforced composites for aerospace structures has seen a high increase in recent years, and is still growing. The high stiffness-to-weight ratio of these materials makes them ideal for primary structures on airplanes, satellites, and spacecrafts. Nevertheless, the manufacturing of composites remains very costly since it requires equipment investment such as an autoclave, and very qualified workers. Out-of-autoclave manufacturing technology is very promising since it only requires a traditional oven, while still aiming at similar part quality. However, the absence of positive pressure compared with an autoclave makes it more difficult to achieve low porosity parts. This research investigates the manufacturing of complex features with out-of autoclave prepreg technology. The features studied are tight-radius corners with a curvature change, and ply drop-offs. Ply drop-offs tests were conducted to identify if porosity is higher at ply terminations. In corners, the bagging arrangement was modified to achieve the most uniform thickness in areas of curvature change, even with small radii. The conclusions from these studies provided us with guidelines to manufacture larger representative parts, which included these features. The representative parts were tested for porosity, thickness uniformity, mechanical performance, and glass transition temperature(Tg). A total of four representative parts were manufactured with out-of-autoclave technology, and one more was manufactured with an autoclave to allow for a proper comparison between the two processes. The materials used were MTM45-1 5 harness satin and CYCOM5320 plain weave for the out-of-autoclave parts,and CYCOM5276-1 plain weave for the autoclave part. The effect of ply dropoffs on porosity was found to be negligible. Thickness deviation in corners was attributed to a combination of consumable bridging, prepreg's bulk factor and inter-ply shear. Overall, out-of-autoclave prepregs showed performance similar to autoclave prepregs.
L'utilisation de matériaux composites en fibres de carbone pour des structures aéronautiques a connu une croissance rapide ces dernières années, et continue de croitre. Le rapport raideur/masse de ce type de matériaux en fait une solution idéale pour les structures primaires d'avions, de satellites, ou de navettes spatiales. Toutefois, la fabrication de ces pièces en composites demeure extrêmement couteuse puisqu'elle nécessite de lourds investissements d'équipement tels que l'acquisition d'un autoclave, ainsi que de la main-d'oeuvre qualifiée. La technologie hors autoclave semble très prometteuse puisqu'elle ne requiert que l'utilisation d'un four traditionnel, tout en visant à obtenir des pièces de qualité similaire. Cependant, l'absence de pression extérieure provenant de l'autoclave rend plus délicate l'obtention de pièces ayant une faible porosité. Cette recherche a pour thème la fabrication d'éléments complexes avec la technologie hors autoclave. Les éléments étudiés sont des angles convexes et concaves ayant de faibles rayons de courbure, ainsi que des plis partiels. Des tests sur les plis partiels ont été réalisés pour déterminer si ils sont associés à une augmentation de la porosité. Dans les angles, l'arrangement des consommables a été modifié pour obtenir l'épaisseur la plus uniforme possible dans les zones de changement de courbure, et cela même pour de faibles rayons. Les conclusions de ces tests nous ont permis de considérer la fabrication de pièces représentatives de plus grande taille, et qui contiennent les éléments précédemment étudiés. Les pièces représentatives ont été testées pour déterminer leur niveau de porosité, l'uniformité de leur épaisseur, leur performance mécanique, et leur température de transition vitreuse. Au total, quatre pièces représentatives ont été fabriquées par technologie hors autoclave, et une a été fabriquée dans un autoclave afin de permettre une comparaison de bon aloi entre ces deux procédés de fabrication. Les matériaux utilisés pour cette recherche étaient du MTM45-1 5 harness satin et du CYCOM5320 plain weave pour les pièces hors autoclave, ainsi que du CYCOM5276-1 plain weave pour la pièce autoclave. La présence de plis partiels n'a pas été associable à une augmentation notable de la porosité. L'uniformité d'épaisseur s'est révélée être une combinaison de pontage des consommables, du facteur de foisonnement du pré-imprégné, et du cisaillement entre les plis de fibre. Globalement, les pré-imprégnés hors autoclave ont montré des performances similaires aux pré-imprégnés autoclave.
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Nill, Scott T. (Scott Thomas). "Aerospace composite manufacturing cost models as geometric programs." Thesis, Massachusetts Institute of Technology, 2018. http://hdl.handle.net/1721.1/118731.

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Thesis: Ph. D., Massachusetts Institute of Technology, Department of Mechanical Engineering, 2018.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 108-110).
The introduction of large, composite transport aircraft, such as the Airbus A350 and the Boeing 787, has been fraught with billions of dollars of production cost overruns. This research develops a novel approach to manufacturing cost modeling during the conceptual design phase using Geometric Programming (GP). A new formulation of a closed queuing network as a GP is presented to capture the crucial cost trade-offs between capacity and inventory. Additionally, GP models are presented for modeling unit processes in composite manufacturing and for modeling cost accounting metrics. Applied to the challenges of conceptual design for composite aircraft, the cost models can be used as a tool to help inform decisions about which manufacturing process to use and what type of supply chain should be deployed. The special sensitivity-analysis properties of the GP solutions can be exploited to explain how different aspects of the design drive manufacturing costs and to find highly sensitive areas of the trade-space that would have a large impact on cost if the design needed to be altered. The framework is demonstrated for fast but informative analyses of process trade-offs in composite fuselage fabrication.
by Scott T. Nill.
Ph. D.
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Kirtley, Aaron L. (Aaron Lloyd) 1977. "Fostering innovation across aerospace supplier networks." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/82696.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering; and, (S.M.)--Massachusetts Institute of Technology, Engineering Systems Division, Technology and Policy Program, 2002.
This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
"June 2002." Page 187 blank.
Includes bibliographical references (p. 180-184).
by Aaron L. Kirtley.
S.M.
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Negri, Christopher Anthony. "Ductile Fracture of Laser Powder Bed Fusion Additively Manufactured Ti-6Al-4V." University of Dayton / OhioLINK, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1627570434852405.

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Chiu, Brendon W. "Additive manufacturing applications and implementation in aerospace." Thesis, Massachusetts Institute of Technology, 2020. https://hdl.handle.net/1721.1/126950.

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Thesis: M.B.A., Massachusetts Institute of Technology, Sloan School of Management, May, 2020
Thesis: S.M., Massachusetts Institute of Technology, Department of Mechanical Engineering, May, 2020
Cataloged from the official PDF of thesis.
Includes bibliographical references (pages 107-108).
Many aerospace companies are turning to additive manufacturing solutions to stream-line current production processes and open opportunities for on-demand producibility. While many OEMs are drawn to the appeal of the benefits that additive manufacturing brings, they are beginning to understand the difficulties in what it takes to realize those benefits. This paper analyzes additive manufacturing from an industry perspective down to a company perspective to develop a deeper understanding of the practical use cases as well as the various challenges a company faces should they choose to enter this market. This study begins with market research on the additive manufacturing and aerospace industry before honing in on a several use-case parts from rotary aircraft. Selection criterion were created and applied to analyze the value that additive manufacturing would bring in comparison to that of conventional methods, ultimately determining its feasibility for additive manufacturing.
This study applied the selection criterion to various parts of differing functions among the aircraft, resulting in a group of candidate parts. An evaluation method was created and applied to provide an objective assessment on the candidate parts. Initial insights show that additive manufacturing favor casted parts with features that can be optimized to increase performance and reduce costs and weight. In addition, aerospace has the best product mix of low volume parts that are advantageous to the economies of scale for additive manufacturing. Additionally, this study analyzes a company's organization and previous additive manufacturing efforts to propose ways to approach future development. Venturing through the various road maps that lead to the final goal of certification and addressing organizational barriers generate momentum for continuous development.
These road maps, selection criterion, and evaluation method can be applied through many applications within the general aerospace industry.
by Brendon W Chiu.
M.B.A.
S.M.
M.B.A. Massachusetts Institute of Technology, Sloan School of Management
S.M. Massachusetts Institute of Technology, Department of Mechanical Engineering
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Mohammed, Mohammed Abdelaziz Elamin. "IMPACT AND POST IMPACT RESPONSE OF COMPOSITE SANDWICH STRUCTURES IN ARCTIC CONDITION." University of Akron / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=akron1518520473027006.

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Frauenberger, Douglas H. "Lean transformation in aerospace assembly operations." Thesis, Massachusetts Institute of Technology, 2007. http://hdl.handle.net/1721.1/39728.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering; and, (M.B.A.)--Massachusetts Institute of Technology, Sloan School of Management; in conjunction with the Leaders for Manufacturing Program at MIT, 2007.
Includes bibliographical references (p. 81-82).
For the past two decades, virtually all manufacturing companies in the United States have adopted or are in the process of adopting lean manufacturing. Globalization has resulted in the increased availability of reliable, low cost sources putting greater pressures on traditional US manufacturing companies to reduce costs. The need to successfully transform to lean has only grown in importance in this new operating environment, resulting in renewed focus on such initiatives in the United States. This thesis discusses various approaches to lean manufacturing with reference to specific examples from both academia and industry. In particular, lean transformation efforts in Mitchell Engine Company's* Final Assembly Plant will be provided as a case study. Focus on the JP-3525 fan case assembly cell provides specific examples on how shop floor improvements, assembly cell redesign, and flow can improve process cycle time and decrease variability. The direct result of this work has been a 15% decrease in cycle time and a 100% decrease in variability in the JP-3525 fan case assembly cell. Finally, the role front-line supervisors play in change initiatives will be introduced, discussing the position from both management and labor perspectives. Based on past research, recommendations will be made on how to improve cell leader effectiveness, recognizing these changes require systemic change within the organization.
by Douglas H. Frauenberger.
M.B.A.
S.M.
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Buettner, Robert W. "Dynamic Modeling and Simulation of a Variable Cycle Turbofan Engine with Controls." Wright State University / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=wright1496179248257409.

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Books on the topic "Mechanical and aerospace"

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J, Inman D., ed. Damage prognosis for aerospace, civil and mechanical systems. Chichester, England: Wiley, 2005.

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Rajendran, Parvathy, Nurul Musfirah Mazlan, Aslina Anjang Ab Rahman, Nurulasikin Mohd Suhadis, Norizham Abdul Razak, and Mohd Shukur Zainol Abidin, eds. Proceedings of International Conference of Aerospace and Mechanical Engineering 2019. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-4756-0.

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Fan, Wu. Mechanical and aerospace engineering: Selected, peer reviewed papers from the 2nd International Conference on Mechanical and Aerospace Engineering (ICMAE) 2011), July 29-31, 2011, Bangkok, Thailand. Durnten-Zurich: Trans Tech Publications, 2012.

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Science, Department of Education &. Kingston Polytechnic: Aspects of mechanical aerospace andmanufacturing engineering provision : a report by HMI. Stanmore: Department of Education and Science, 1990.

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W, Walker S., Boesiger E. A, and John F. Kennedy Space Center., eds. 32nd Aerospace Mechanisms Symposium: Proceedings of a symposium held at the Cocoa Beach Hilton, Cocoa Beach, Florida, and hosted by NASA, John F. Kennedy Space Center and sponsored by Lockheed Martin Missiles and Space, and the Aerospace Mechanisms Symposium Committee, May 13-15, 1998. KSC, Fla: National Aeronautics and Space Administration, John F. Kennedy Space Center, 1998.

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Angelo, Miele, and Salvetti A, eds. Applied mathematics in aerospace science and engineering. New York: Plenum Press, 1994.

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B, Magrab Edward, ed. An engineer's guide to MATLAB: With applications from mechanical, aerospace, electrical, and civil engineering. 2nd ed. Upper Saddle River, NJ: Pearson Prentice Hall, 2005.

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United States. National Aeronautics and Space Administration., ed. Electro-mechanical actuator: DC resonant link controller. [Washington, D.C.]: National Aeronautics and Space Administration, 1996.

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United States. National Aeronautics and Space Administration., ed. Electro-mechanical actuator: DC resonant link controller. [Washington, D.C.]: National Aeronautics and Space Administration, 1996.

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United States. National Aeronautics and Space Administration., ed. Electro-mechanical actuator: DC resonant link controller. [Washington, D.C.]: National Aeronautics and Space Administration, 1996.

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Book chapters on the topic "Mechanical and aerospace"

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Hefazi, Hamid. "Aerospace Engineering." In Springer Handbook of Mechanical Engineering, 1085–137. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-47035-7_24.

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Huliraj, R. V., and H. L. Janardhana. "Aircraft Mechanical Systems." In Aerospace Materials and Material Technologies, 251–78. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-2143-5_13.

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Gopalakrishnan, S. "Smart Materials Technology for Aerospace Applications." In Springer Tracts in Mechanical Engineering, 423–37. New Delhi: Springer India, 2014. http://dx.doi.org/10.1007/978-81-322-1913-2_25.

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Haddad, Yousef, Sandeep Jagtap, Emanuele Pagone, and Konstantinos Salonitis. "Sustainability Assessment of Aerospace Manufacturing: An LCA-Based Framework." In Lecture Notes in Mechanical Engineering, 712–20. Cham: Springer International Publishing, 2023. http://dx.doi.org/10.1007/978-3-031-28839-5_80.

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AbstractIn this paper, a life cycle assessment (LCA)-based sustainability assessment framework is developed to estimate the environmental impact of production processes. The framework provides a methodical, context-independent, approach to carry out LCA studies. The framework sets guiding principles for products and key performance indicators (KPIs) selection and the associated data requirements in a reconfigurable manner that can be applied to any industrial setting. In order to validate and demonstrate the applicability of the framework, a cradle-to-gate case study pertaining to the manufacturing of a real aerospace metallic structural component is carried out. Results revealed that the complexity of aerospace components makes it difficult to improve the environmental impact from manufacturing operations as most of the impact comes from upstream activities that aerospace manufacturers, typically, have no control over, or access to.
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dell’Erba, Ramiro. "How Swarm Robot Dynamic Can Describe Mechanical Systems." In Design Advances in Aerospace Robotics, 148–59. Cham: Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-28447-2_12.

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Meher, Umakanta, Praveen Shakya, and Mohammed Rabius Sunny. "Electro-mechanical Impedance response of a delaminated glass-fibre composite beam." In Aerospace and Associated Technology, 437–41. London: Routledge, 2022. http://dx.doi.org/10.1201/9781003324539-80.

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Franchino, Marco. "Framework for Sustainability in Aerospace: A Proof of Concept on Decision Making and Scenario Comparison." In Lecture Notes in Mechanical Engineering, 659–68. Cham: Springer International Publishing, 2023. http://dx.doi.org/10.1007/978-3-031-28839-5_74.

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AbstractAerospace is a large and growing industry currently dependent on fossil fuels. UK aviation has committed to achieving net zero emissions by 2050.In order for the UK aerospace sector to achieve the sustainability goals, it needs to use the latest technologies while making sure to minimise negative environmental impacts.Ongoing debates claims that the definition of sustainability and its assessment is vague. Companies struggle with quantifying the return on their sustainability investments and necessitate a methodology to aid decision making and quantify improvements against sustainability and profitability. For that reason, this investigation focused on defining a framework to assess sustainability for aerospace manufacturing following a triple bottom line (TBL): profit, people (social responsibility) and planet.The author surveyed a range of major aerospace businesses, including Airbus, BAE Systems, Boeing, GKN, Rolls-Royce and Spirit Aerosystems, who are all industrial partners at the University of Sheffield Advanced Manufacturing Research Centre (AMRC). These businesses are all working together to identify and solve the common challenges associated with sustainable manufacturing and contributed their thoughts to the development of this definition.Collected information has been integrated in a trade study framework that helps scenario comparison and decision making. Discrete Event Simulation (DES) has been used to test the methodology, defining and quantifying alternative scenarios. The framework developed in this study aims to help ensuring that aerospace companies remain profitable whilst also fulfilling the industrial Partners’ environmental and societal obligations.
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Savchuk, Olena. "Legal Support of Aerospace Environmental Monitoring." In Integrated Computer Technologies in Mechanical Engineering - 2021, 690–703. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-94259-5_56.

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Dumont, D., A. Deschamps, Yves Bréchet, and C. Sigli. "Mechanical Properties/Microstructure Relationships in Aerospace Aluminum Alloys." In Microstructures, Mechanical Properties and Processes - Computer Simulation and Modelling, 269–75. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2005. http://dx.doi.org/10.1002/3527606157.ch43.

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Bonnard, Bernard, Mohamed Jabeur, and Gabriel Janin. "3 Control of Mechanical Systems from Aerospace Engineering." In Advanced Topics in Control Systems Theory, 65–113. London: Springer London, 2005. http://dx.doi.org/10.1007/11334774_3.

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Conference papers on the topic "Mechanical and aerospace"

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Batchellor, C. R., J. P. Dakin, and D. A. J. Pearce. "Fibre Optic Mechanical Sensors For Aerospace Applications." In O-E/Fibers '87, edited by Ramon P. DePaula and Eric Udd. SPIE, 1988. http://dx.doi.org/10.1117/12.942503.

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Redding, David C., Mark H. Milman, and Greg Loboda. "Linear analysis of opto-mechanical systems." In Aerospace Sensing, edited by John A. Breakwell. SPIE, 1992. http://dx.doi.org/10.1117/12.138160.

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Jacob, J. "Aerospace engineering education in a mechanical engineering environment." In 38th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-527.

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Nicholson, Elisabeth D., Charles S. J. Pickles, and John E. Field. "Mechanical properties of thin films for aerospace applications." In SPIE's 1994 International Symposium on Optics, Imaging, and Instrumentation, edited by Paul Klocek. SPIE, 1994. http://dx.doi.org/10.1117/12.187349.

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Larsen, Christopher G., and Daniel R. Wade. "Sensing challenges for mechanical aerospace prognostic health monitoring." In 2012 IEEE Conference on Prognostics and Health Management (PHM). IEEE, 2012. http://dx.doi.org/10.1109/icphm.2012.6299530.

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ZIMMERMAN, KRISTIN. "Mechanical fastening of FGRP composites." In 28th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-182.

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BUSECK, R., and H. BENAROYA. "MECHANICAL MODELS FOR SLOSH OF LIQUID FUEL." In Aerospace Design Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-1093.

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Mulvihill, Robert J., and Yunnhon Lo. "Weld Analysis Methods for Aerospace Systems." In ASME 2004 International Mechanical Engineering Congress and Exposition. ASMEDC, 2004. http://dx.doi.org/10.1115/imece2004-59242.

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An example of the application of probabilistic structural analysis to welds is presented below. . The same methodology can be used for probabilistic structural analysis of parent metals in tank structures and other structural components such as supports. The methodology is based on a stress vs. strength model. The results may be used for a comparative analysis of candidate weld process improvements. The model can be incorporated into a probabilistic risk assessment which includes the undesirable impacts of weld failure.
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Reznikov, Lev. "Integrated Eco-Thermal Management for Aerospace." In ASME 2005 International Mechanical Engineering Congress and Exposition. ASMEDC, 2005. http://dx.doi.org/10.1115/imece2005-82865.

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Thermal Management System developed for aerospace carriers (missile, aircraft, space station), bounds processes of generation and dissipation, transfer and conversion of power, refrigeration, and of bio-metabolism related substances. Local ecosystem of the carrier combines technological and biological subsystems, interacting with internal and outer spaces. The conceptual IETM System performs recovery of waste thermal energy, generation of “free” refrigeration, and recovery of byproducts into safe coolants (ammonia - water). Thermal Management solutions include novel technologies of intensification of the heat transfer and of conversion of the waste resources into refrigeration for extension of cooling capabilities for high heat radars, lasers and microwave generators. The IETM includes Vacuum-Evaporative Refrigeration (VER) utilizing “free natural” vacuum and waste heat-activated refrigeration circuits. VER generates ~1000 Btu of “free” cold per pound of wastewater or ammonia. The introduced high performance microstructure of compound electrohydrodynamic (EHD) boundary microsystems intensifies nucleate boiling, preventing dryout. The coils of the microwires adjoin to the boiling surface and form precision microstructure of heat sink with microchannels between the coils and the surface. The microcavities form the active bubbling nucleation sites along the spiral zones of contacts of the microwires and basic surfaces. The fins-microelectrodes develop additional heat transfer surface and evenly distributed spiral zones of the nucleation sites. Like fibers of a fine wick, the electric forces in EHD capillary structures of the microelectrodes retain the liquid and push out generated vapor bubbles from the surface. Good manufacturability and performance of novel MEMS are based on well-developed materials and common winding technology “borrowed” from electrotechnical industry. Conversion of waste resources into refrigeration and EHD activation of boiling allow meeting strong limitations in weight, reliability and consumption of energy. These conceptual approaches provide diversities in refrigeration capabilities for IETM.
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Figueroa, Fernando, and Carolyn R. Mercer. "Advancing Sensor Technology for Aerospace Propulsion." In ASME 2002 International Mechanical Engineering Congress and Exposition. ASMEDC, 2002. http://dx.doi.org/10.1115/imece2002-33180.

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NASA’s Stennis Space Center (SSC) and Glenn Research Center (GRC) participate in the development of technologies for propulsion testing and propulsion applications in air and space transportation. Future transportation systems and the test facilities needed to develop and sustain them are becoming increasingly complex. Sensor technology is a fundamental pillar that makes possible development of complex systems that must operate in automatic mode (closed loop systems), or even in assisted-autonomous mode (highly self-sufficient systems such as planetary exploration spacecraft). Hence, a great deal of effort is dedicated to develop new sensors and related technologies to be used in research facilities, test facilities, and in vehicles and equipment. This paper describes sensor technologies being developed and in use at SSC and GRC, including new technologies in integrated health management involving sensors, components, processes, and vehicles.
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Reports on the topic "Mechanical and aerospace"

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Freeman, Arthur J., Oleg Y. Kontsevoi, Yuri N. Gornostyrev, and Nadezhda I. Medvedeva. Fundamental Electronic Structure Characteristics and Mechanical Behavior of Aerospace Materials. Fort Belvoir, VA: Defense Technical Information Center, April 2008. http://dx.doi.org/10.21236/ada480633.

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Harvey, Dustin Yewell, Eric Brian Flynn, Stuart Glynn Taylor, Charles Reed Farrar, Octavio Jr Ramos, and Kelly Lynn Parker. SHMTools: Structural Health Monitoring Software for Aerospace, Civil, and Mechanical Infrastructure. Office of Scientific and Technical Information (OSTI), April 2015. http://dx.doi.org/10.2172/1178315.

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Hayes, Michael. Introduction of Continuous Fiber-reinforced Polymer: A New Additive Manufacturing Path for Aerospace. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, August 2023. http://dx.doi.org/10.4271/epr2023019.

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<div class="section abstract"><div class="htmlview paragraph">To grow the application space of polymer additive manufacturing (AM), the industry must provide an offering with improved mechanical properties. Several entities are working towards introducing continuous fibers embedded into either a thermoplastic or thermoset resin system. This approach can enable significant improvement in mechanical properties and could be what is needed to open new and exciting applications within the aerospace industry.</div><div class="htmlview paragraph"><b>Introduction of Continuous Fiber Reinforced Polymer: A New Additive Manufacturing Path for Aerospace</b> examines a couple of unsettled issues that are beginning to come to light regarding these materials and focuses on the ability to design and provide robust structural analysis for continuous fiber reinforced polymer AM—unsung aspects that can make or break this new technology as it finds its way into the aerospace market. Without solutions to them, adoption by the aerospace industry will be limited to point design applications, thus constraining the technology to being nothing more than a specialized tool.</div><div class="htmlview paragraph"><a href="https://www.sae.org/publications/edge-research-reports" target="_blank">Click here to access the full SAE EDGE</a><sup>TM</sup><a href="https://www.sae.org/publications/edge-research-reports" target="_blank"> Research Report portfolio.</a></div></div>
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Tomar, Vikas. Understanding Nanoscale Thermal Conduction an Mechanical Strength Correlation in High Temperature Ceramics with Improved Thermal Shock Resistance for Aerospace Applications. Fort Belvoir, VA: Defense Technical Information Center, August 2012. http://dx.doi.org/10.21236/ada581368.

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Jenkins, Jerry E., Gregory A. Addington, Phillip S. Beran, Deborah S. Grismer, and Ernest S. Hanff. Dynamics of Aerospace Vehicles -- Nonlinear Flight Mechanics. Fort Belvoir, VA: Defense Technical Information Center, May 2000. http://dx.doi.org/10.21236/ada380300.

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Mracek Dietrich, Anna, and Ravi Rajamani. Unsettled Issues Regarding the Certification of Electric Aircraft. SAE International, March 2021. http://dx.doi.org/10.4271/epr2021007.

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The aerospace industry is beginning to grapple with the reality of certifying electric aircraft (EA), signaling the maturing of the field. Many players are ramping up their activities to respond to imminent technical, safety, and regulatory requirements. While there are gaps in EA knowledge as well as the processes for certifying them, some leading standards development organizations (SDOs) such as SAE International, ASTM International, and RTCA—ably supported by representatives from regulatory agencies—are stepping in to address many of these issues. Of special importance are the new rule changes in the normal category (14 CFR Part 23, Amendment 64) that shift from a prescriptive philosophy to “performance-based rules.” Regarding system knowledge, there has been a trend in the use electrical energy to power systems that have long employed mechanical hydraulics. In the new EA paradigm, these components will be employed at criticality levels not previously witnessed in conventional aircraft, calling for a specific set of certification demands. Unsettled Issues Regarding the Certification of Electric Aircraft tackles the certification challenges faced by EA manufacturers in both the small (normal) and large (transport) categories, addressing technical, business, and process issues.
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