Relevant bibliographies by topics / Expensive aerospace

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  2. Books
  3. Book chapters
  4. Conference papers

Academic literature on the topic 'Expensive aerospace'

Author: Grafiati
Published: 1 April 2023

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Journal articles on the topic "Expensive aerospace"

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Shi, Renhe, Teng Long, Nianhui Ye, Yufei Wu, Zhao Wei, and Zhenyu Liu. "Metamodel-based multidisciplinary design optimization methods for aerospace system." Astrodynamics 5, no. 3 (September 2021): 185–215. http://dx.doi.org/10.1007/s42064-021-0109-x.

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AbstractThe design of complex aerospace systems is a multidisciplinary design optimization (MDO) problem involving the interaction of multiple disciplines. However, because of the necessity of evaluating expensive black-box simulations, the enormous computational cost of solving MDO problems in aerospace systems has also become a problem in practice. To resolve this, metamodel-based design optimization techniques have been applied to MDO. With these methods, system models can be rapidly predicted using approximate metamodels to improve the optimization efficiency. This paper presents an overall survey of metamodel-based MDO for aerospace systems. From the perspective of aerospace system design, this paper introduces the fundamental methodology and technology of metamodel-based MDO, including aerospace system MDO problem formulation, metamodeling techniques, state-of-the-art metamodel-based multidisciplinary optimization strategies, and expensive black-box constraint-handling mechanisms. Moreover, various aerospace system examples are presented to illustrate the application of metamodel-based MDOs to practical engineering. The conclusions derived from this work are summarized in the final section of the paper. The survey results are expected to serve as guide and reference for designers involved in metamodel-based MDO in the field of aerospace engineering.
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Ong, Yew S., Prasanth B. Nair, and Andrew J. Keane. "Evolutionary Optimization of Computationally Expensive Problems via Surrogate Modeling." AIAA Journal 41, no. 4 (April 2003): 687–96. http://dx.doi.org/10.2514/2.1999.

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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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Cai, Xiwen, Haobo Qiu, Liang Gao, Li Wei, and Xinyu Shao. "Adaptive Radial-Basis-Function-Based Multifidelity Metamodeling for Expensive Black-Box Problems." AIAA Journal 55, no. 7 (July 2017): 2424–36. http://dx.doi.org/10.2514/1.j055649.

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He, Youwei, Jinju Sun, Peng Song, and Xuesong Wang. "Dual Kriging assisted efficient global optimization of expensive problems with evaluation failures." Aerospace Science and Technology 105 (October 2020): 106006. http://dx.doi.org/10.1016/j.ast.2020.106006.

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Jiang, Ping, Ji Cheng, Qi Zhou, Leshi Shu, and Jiexiang Hu. "Variable-Fidelity Lower Confidence Bounding Approach for Engineering Optimization Problems with Expensive Simulations." AIAA Journal 57, no. 12 (December 2019): 5416–30. http://dx.doi.org/10.2514/1.j058283.

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Long, Teng, Zhao Wei, Renhe Shi, and Yufei Wu. "Parallel Adaptive Kriging Method with Constraint Aggregation for Expensive Black-Box Optimization Problems." AIAA Journal 59, no. 9 (September 2021): 3465–79. http://dx.doi.org/10.2514/1.j059915.

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Long, Teng, Xin Li, Renhe Shi, Jian Liu, Xiaosong Guo, and Li Liu. "Gradient-Free Trust-Region-Based Adaptive Response Surface Method for Expensive Aircraft Optimization." AIAA Journal 56, no. 2 (February 2018): 862–73. http://dx.doi.org/10.2514/1.j054779.

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Parkinson, R. C. "Why Space is Expensive—Operational/Economic Aspects of Space Transport." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 205, no. 1 (January 1991): 45–52. http://dx.doi.org/10.1243/pime_proc_1991_205_236_02.

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Roux, Maxime, Nicolas Eguémann, Clemens Dransfeld, Frédéric Thiébaud, and Dominique Perreux. "Thermoplastic carbon fibre-reinforced polymer recycling with electrodynamical fragmentation." Journal of Thermoplastic Composite Materials 30, no. 3 (August 4, 2016): 381–403. http://dx.doi.org/10.1177/0892705715599431.

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The end of life of carbon fibre-reinforced polymer (CFRP) structures represents a major challenge to the aerospace industry, as new European regulations are demanding recycling solutions that can be complicated and expensive to apply. This study aims to address new practical ways to recycle CFRP materials. CFRP materials with a polyether ether ketone (PEEK) matrix were fragmented via electrodynamical fragmentation, which exhibits several benefits compared to mechanical shredding processes, especially for composites commonly found in the aerospace industry. The fragments are characterized and reused to produce new CFRP aerospace parts. Structural testing of recycled composite parts revealed a 17% decrease of the mechanical properties compared to the novel material. The combination of these manufacturing and recycling techniques closes the cradle to cradle loop of thermoplastic CFRP.
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Books on the topic "Expensive aerospace"

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DTBooks, Elmo. Aerospace Engineer Monthly Budget Planner Organizer: Financial Planning Journal, Monthly Budgeting Workbook, Calendar Expense Tracker Organizer for Budget Planner, 120 Pages, 8. 5 X 11, Red Gold Color, Checklist Organizer Goals and Expenses. Independently Published, 2021.

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Book chapters on the topic "Expensive aerospace"

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Sadiku, Emmanuel Rotimi, Oluranti Agboola, Mokgaotsa Jonas Mochane, Victoria Oluwaseun Fasiku, Shesan John Owonubi, Idowu David Ibrahim, Babul Reddy Abbavaram, et al. "The Use of Polymer Nanocomposites in the Aerospace and the Military/Defence Industries." In Polymer Nanocomposites for Advanced Engineering and Military Applications, 316–49. IGI Global, 2019. http://dx.doi.org/10.4018/978-1-5225-7838-3.ch011.

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Previously, applications of composites were limited to the military aerospace. This is because civilian aircraft with composites inclusions was considered to be too expensive. The use of composite in aircrafts, instead of steel, has resulted in lightweight aircraft structures and has consequently reduced the level of fuel consumption and costs of fuel, thereby reducing CO2 emissions. Undoubtedly, nanocomposites applications abound in several aspects of human life and the use of nanoparticle in materials dates back to the understanding of the nature of these materials. This chapter will focus on the use of nanopolymers in the aerospace and in the military. Particular attention will be given to nano military weapons, nanocoating for military applications, nanotechnology for military drones, nanotechnology in military suits, gloves, boots and nanotechnology in armored military vehicles, aircraft, and military ships and in military medicine.
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Sadiku, Emmanuel Rotimi, Oluranti Agboola, Mokgaotsa Jonas Mochane, Victoria Oluwaseun Fasiku, Shesan John Owonubi, Idowu David Ibrahim, Babul Reddy Abbavaram, et al. "The Use of Polymer Nanocomposites in the Aerospace and the Military/Defence Industries." In Research Anthology on Military and Defense Applications, Utilization, Education, and Ethics, 323–56. IGI Global, 2021. http://dx.doi.org/10.4018/978-1-7998-9029-4.ch018.

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Previously, applications of composites were limited to the military aerospace. This is because civilian aircraft with composites inclusions was considered to be too expensive. The use of composite in aircrafts, instead of steel, has resulted in lightweight aircraft structures and has consequently reduced the level of fuel consumption and costs of fuel, thereby reducing CO2 emissions. Undoubtedly, nanocomposites applications abound in several aspects of human life and the use of nanoparticle in materials dates back to the understanding of the nature of these materials. This chapter will focus on the use of nanopolymers in the aerospace and in the military. Particular attention will be given to nano military weapons, nanocoating for military applications, nanotechnology for military drones, nanotechnology in military suits, gloves, boots and nanotechnology in armored military vehicles, aircraft, and military ships and in military medicine.
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Rivolta, Barbara, and R. Gerosa. "Quench Sensitivity of Aluminum Alloys." In Encyclopedia of Aluminum and Its Alloys. Boca Raton: CRC Press, 2019. http://dx.doi.org/10.1201/9781351045636-140000337.

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The demand of alloys with high strength-to-density ratio is continuously increasing in the engineering world. Beside very expensive materials, such as the titanium alloys and the high strength reinforced polymers, the aluminum alloys represent an excellent alternative to satisfy the challenging requirements of many mechanical and aerospace applications. Among these alloys, the heat treatable grades are much appreciated for the possibility to increase the mechanical resistance significantly after solution treatment and aging. The former aims to create a supersaturated solution that is later modified during the latter by the formation of metastable precipitates involving all or some of the alloying elements. In the technical literature, it is well known that the corrosion resistance and the mechanical properties of these alloys, especially the 7xxx grades, strongly depend on the quenching conditions after the solution treatment. This phenomenon is known as “quench sensitivity.” The main aim of this entry is to discuss the influence of the cooling rate during quenching of different commercial aluminum alloys from mechanical and corrosion points of view. The influence of the rolling direction and of the alloy temper will be considered to focusing the attention on some experimental data obtained on the 7075 aluminum alloy.
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Xu, Xun. "CAD Data Exhange and CAD Standards." In Integrating Advanced Computer-Aided Design, Manufacturing, and Numerical Control, 32–53. IGI Global, 2009. http://dx.doi.org/10.4018/978-1-59904-714-0.ch002.

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Today, more companies than ever before are involved in manufacturing various parts of their end products using different subcontractors, many of whom are often geographically diverse. The rise of such global efforts has created the need for sharing information among vendors involved in multi-disciplinary projects. Transfer of data is necessary so that, for example, one organization can be developing a CAD model, while another performs analysis work on the same model; at the same time a third organization is responsible for manufacturing the product. Data transfer fills the need to satisfy each of these functions in a specific way. Accurate transmission is of paramount importance. Thus, a mechanism for good data transfer is needed. The CAD interoperability issue - using one CAD system in-house, yet needing to deliver designs to, or receive designs from, another system, poses a challenge to industries such as automotive, aerospace, shipbuilding, heavy equipment, and high-tech original equipment manufacturers and their suppliers. It is worth studying the issue and determining how engineering model data is delivered today to manufacturers and suppliers, how CAD conversion, geometric translation, and/or feature-based CAD interoperability are handled, at what expense, and under whose authority. This chapter explores the various ways to make this vital transfer possible. The attention will be directed towards data exchange and standards for 3-D CAD systems. Since CAD data formats have a lot to do with CAD kernels that govern the data structure and therefore the data formats, some popular CAD kernels are discussed. The data interoperability section covers different types of data translations and conversions. The use of neutral or standardized data exchange protocols is one of the natural methods for data exchange and sharing. This topic is covered at the end of this chapter.
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Conference papers on the topic "Expensive aerospace"

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Tenne, Yoel, Shigeru Obayashi, and S. W. Armfield. "Airfoil Shape Optimization by Minimization of an Expensive and Discontinuous Black-box Function." In AIAA Infotech@Aerospace 2007 Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-2874.

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Eckersley, Steven, Josef Schalk, and Martin Kluge. "The EADS Micropack Project: An Intelligent Microsystem Demonstrator for Small Mission Applications." In CANEUS 2006: MNT for Aerospace Applications. ASMEDC, 2006. http://dx.doi.org/10.1115/caneus2006-11024.

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The global Micro-electromechanical (MEMS) or Microsystems Technology (MST) market is forecast to keep growing at a phenomenal rate. EADS recognises the potential for this technology to revolutionise the space industry, where it can dramatically reduce mass, size and power requirements and therefore launch costs. This can enable missions that would otherwise have been unfeasibly expensive. Therefore EADS has been developing a novel modular approach to packaging integrated microsystems for space applications called ‘micropacks’. The micropacks include suites of COTS MST sensors, packaged and integrated into a 3D modular multi-layer ceramic package. This introduces flexibility and means that this impressively light and compact micropack technology can be adapted to form the basis as a solution for a range of exciting future mission concepts. In addition, EADS Astrium Ltd. is ensuring that the micropack has the capability to be integrated into a cubesat, should a potential flight opportunity arise. This in turn helps develop the necessary knowhow of MEMS payload integration for future missions.
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Lankarani, Hamid M., C. S. Koshy, and C. K. Thorbole. "Design and Validation of a Component Head Injury Criteria Tester for Aerospace Applications." In ASME 2005 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/detc2005-84436.

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The compliance with Head Injury Criteria (HIC) specified in 14 CFR 23.562 [1] and CFR 25.562 [2] poses a significant problem for many segments of the aerospace industry. The airlines and the manufacturers of jet transports have made claims of high costs and significant schedule overruns during the development and certification of 16G seats because of the difficulties encountered in meeting this requirement. The current practice is to conduct Full Scale Sled Tests (FSST) on impact sleds. This approach can be expensive, since a new seat may be needed for each test. Moreover, some consider the HIC sensitive to changes in the test conditions, such as sled pulse, seat belt elongation, etc., resulting in HIC results from FSSTs showing poor repeatability. These difficulties make it desirable to devise a cheaper, faster, and more repeatable alternative to FSSTs. This paper describes an attempt to address these issues by designing a device, the National Institute for Aviation Research (NIAR) HIC Component Tester (NHCT) using various multibody tools. This device was then fabricated and its performance evaluated against FSSTs conducted under similar test conditions for some typical impact events that occur in an aircraft cabins e.g. impact with bulkheads. The factors compared for this evaluation are the head impact angle, head impact velocity, HIC, HIC window, peak head C.G. resultant acceleration, average head C.G. resultant acceleration, and head C.G. resultant acceleration profiles. The results of these evaluations show that the NHCT already produces test results that correlate significantly with FSST results for impact targets such as bulkheads and its target envelope is expected eventually to include objects such as seat backs.
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Nguyen, Bao, Khulood Faruqui, Luis R. Robles, Johnny Ho, Geoffrey Wagner, Jeremy Surmi, Ashley Carter, et al. "Overview of Current Hybrid Propulsion Research and Development." In ASME 2017 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/imece2017-72429.

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As dwindling federal funding continues to constrict the national space program, private entities have carried the torch of innovation in the aerospace industry. While the concept of hybrid rocket engines, systems where solid fuels and fluid oxidizers are used for combustion, was conceived during the mid-20th century, the aerospace industry only recently has substantially increased research and development of these engines. According to the literature, hybrids are safer and cheaper than their liquid counterparts due to the utilization of solid fuel and generally provide greater values of specific impulse, density specific impulse, and fuel energy density than traditional solid-fuel engines. This paper provides an overview of the design principles used to develop hybrid engines and discusses limitations currently faced by industry. Furthermore, development of hybrid engines to allow for both scalability and reusability are explored as private aerospace companies continue to demonstrate that reusable rockets are the future of rocket technology. With applications catering from low-payload cargo delivery to the increasing interest in space tourism and exploration, hybrid engines can provide a safer, less expensive solution than traditional and well-established engine selections. Suggestions for future design opportunities and methods are proposed and discussed to make the concept of hybrid engines a viable innovation in the future of rocketry.
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Meluso, John, and Jesse Austin-Breneman. "Gaming the System: An Agent-Based Model of Estimation Strategies and Their Effects on System Performance." In ASME 2017 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/detc2017-68202.

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Parameter estimates in large-scale complex engineered systems affect system evolution yet can be difficult and expensive to test. Systems engineering uses analytical methods to reduce uncertainty, but a growing body of work from other disciplines indicates that cognitive heuristics also affect decision-making. Interviews with several expert aerospace practitioners suggest that engineers bias estimation strategies. Practitioners reaffirmed known system features and posited that engineers may bias estimation methods as a negotiation and resource conservation strategy. Specifically, participants reported that some systems engineers “game the system” by biasing requirements to counteract subsystem estimation biases. An agent-based model simulation which recreates these characteristics is presented. Model results suggest that the systems engineers’ “gaming” strategy of counteracting subsystem bias may decrease system-level estimate accuracy and increase uncertainty.
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Karibeeran, Shanmuga Sundaram, and Rajiv Selvam. "Experimental Study on Electromagnetic Forming of Copper Sheets." In ASME 2013 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/imece2013-63433.

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The sheet metal forming of copper, aluminum alloys using conventional stamping processes posses various problems, because of the lower formability limits, spring back and the tendency to wrinkle compared to steel. The principle of electromagnetism using attractive force is adopted to modify the conventional stamping process, to form thin sheets of 0.05 mm thickness. Further, this process can be used to form many sheet metal components with less expensive tooling and lesser number of operations. This process ultimately leads to light weight, cost effective and better strength-to-weight ratio components required for aerospace applications. In this study, a maximum of 30.77 % reduction in diameter was observed at 2.75A using electromagnetic forming which leads to the absence of spring back.
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Fricke, So¨ren, Alois Friedberger, Thomas Ziemann, Eberhard Rose, Gerhard Mu¨ller, Dimitri Telitschkin, Stefan Ziegenhagen, Helmut Seidel, and Ulrich Schmid. "High Temperature (800°C) MEMS Pressure Sensor Development Including Reusable Packaging for Rocket Engine Applications." In CANEUS 2006: MNT for Aerospace Applications. ASMEDC, 2006. http://dx.doi.org/10.1115/caneus2006-11042.

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For aircraft and rocket engines there is a strong need to measure the pressure in the propulsion system at high temperature (HT) with a high local resolution. Miniaturized sensor elements commercially available show decisive disadvantages. With piezoelectric-based sensors working clearly above 500°C static pressures can not be measured. Optical sensors are very expensive and require complex electronics. SiC sensor prototypes are operated up to 650°C, but require high technological efforts. The present approach is based on resistors placed on top of a 2 mm diameter sapphire membrane (8 mm chip diameter). The strain gauges are made either of antimony doped tin oxide (SnO2:Sb) or platinum (Pt). This material combination allows for matching the thermal coefficients of expansion (TCE) of the materials involved. The morphology of the SnO2:Sb layer can be optimized to reduce surface roughness on the nanometer scale and hence, gas sensitivity. Antimony doping increases conductivity, but decreases the gauge factor. With this nanotechnological knowledge it is possible to adjust the material properties to the needs of our aerospace applications. Tin oxide was shown to be very stable at HT. We also measured a 2.5% change in electrical resistivity at room temperature at maximum membrane deflection. The maximum temperature coefficient of resistivity (TCR) is less than 3.5·10−4 K−1 in the temperature range between 25°C and 640°C. In addition to the device related research work, a novel reusable packaging concept is developed as housing is the main cost driver. After the chip is destroyed the functional device can simply be replaced — housing and contacts can be reused. The MEMS device is electrically contacted with a miniaturized spring mechanism. It is loaded from the harsh environment side into the HT stable metal housing. A cap is screwed into the housing and compresses the inserted seal ring against the chip. The part for electrical contacting on the opposite housing side is not disassembled. The MEMS device is not in direct contact with the housing material, but embedded between two adaptive layers of the same material as the device (sapphire) to decrease thermally induced mechanical stress. Overall weight is 46 g. This packaging concept has been successfully optimized so that the whole assembly can withstand 800°C and simultaneously provides sealing up to 250 bar! After testing in such harsh environment, the small packaging can still be unscrewed to exchange the MEMS device. Due to the reutilization, the packaging can be used far beyond the lifetime of HT MEMS devices.
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Reed, John A., and Abdollah A. Afjeh. "Computational Simulation of Gas Turbines: Part I — Foundations of Component-Based Models." In ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/99-gt-346.

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Designing and developing new aerospace propulsion systems is time-consuming and expensive. Computational simulation is a promising means for alleviating this cost, but requires a flexible software simulation system capable of integrating advanced multidisciplinary and multifidelity analysis methods, dynamically constructing arbitrary simulation models, and distributing computationally complex tasks. To address these issues, we have developed Onyx, a Java-based object-oriented domain framework for aerospace propulsion system simulation. This paper presents the design of a common engineering model formalism for use in Onyx. This approach, which is based on hierarchical decomposition and standardized interfaces, provides a flexible component-based representation for gas turbine systems, subsystems and components. It allows new models to be composed programmatically or visually to form more complex models. Onyx’s common engineering model also supports integration of a hierarchy of models which represent the system at differing levels of abstraction. Selection of a particular model is based on a number of criteria, including the level of detail needed, the objective of the simulation, the available knowledge, and given resources. The common engineering model approach is demonstrated by developing gas turbine component models which will be used to compose a gas turbine engine model in Part II of this paper.
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GAO, ZHENJIA, HARI K. ADLURU, WEI-TSEN LU, KEVIN H. HOOS, and ENDEL V. IARVE. "TWO-WAY GLOBAL-LOCAL COUPLED FAILURE MODELING WITH RX-FEM." In Proceedings for the American Society for Composites-Thirty Seventh Technical Conference. Destech Publications, Inc., 2022. http://dx.doi.org/10.12783/asc37/36439.

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Fiber-reinforced composites are widely used in aerospace structures because of their high specific strength. However, the failure prediction in these heterogeneous engineered materials presents significant challenges due to the multiscale nature and interaction of the damage modes. The computational cost increases dramatically moving from coupon to element to subcomponent and higher levels of the building block ladder. Fine meshes and high-fidelity numerical models are necessary in order to achieve local accuracy but at the same time make the computations prohibitively expensive. The present work focuses on a practical approach, two-way global-local tight coupling, to allow users to setup the modeling easily and reduce the computational cost. This method can capture the global failure. Penalty connection method is used for tight coupling of the local and global regions. Multiple discrete damage modes are allowed in the local region. Two numerical examples are provided to illustrate that the two-way global-local tight coupling can effectively predict the local damage and the global response.
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Daneji, Ali, Salman Pervaiz, and Sathish Kannan. "Study of Tapping Process of Ti6Al4V Using Finite Element (FE) Simulation." In ASME 2020 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/imece2020-24462.

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Abstract Finite element (FE) assisted numerical modeling approach is known as a popular approach to predict the machining performance of different machining operations. Tapping operation is a well-known manufacturing process that is used to cut threads efficiently. In the automotive and aerospace applications, precisely machined tapped holes are required in the small size deep holes. Tapping process creates thread in the hole and make it ready for fastening with other mating components. Tapping operation is considered as one of the most complex machining operations due to the presence of multi-flutes and multi-land involvement between the workpiece and cutter materials. The outcome of the tapping process results in the generation of threads and accepted as one of the most commonly employed in fastening methods for the joining of different machine components. Literature revealed that tapping process has been very rarely investigated using computational modeling approaches, as most of the available studies are experimental in nature. The experimental work for tapping operation can be very time and cost consuming because of the expensive fabrication of the cutting tools. It has also been observed experimentally that minor change in the threading profiles can generate significant difference in the cutting torque. A possible solution is to analyse the whole tapping operation using finite element (FE) assisted numerical simulation. Similarly, there will be limitation towards experiments if the workpiece material is expensive and difficult to cut. It is a common observation in metal cutting industry that most of the times cutting tap results in breakage when exposed to the higher magnitude of torque. The current study is aimed on the finite element based computational investigations on the tapping process using Ti6Al4V as a workpiece material. High hot hardness and low thermal conductivity of the Ti6Al4V also plays a significant role towards the poor machining performance of the threading tool. Ti6Al4V is most commonly employed in the engineering applications where high strength to weight ratio and ability of operate at higher temperatures is required. Ti6Al4V is mainly utilized in the automotive, aerospace, biomedical and petrochemical industries. It has been identified that tapping operation is very rarely studied machining operation in the metal cutting scientific community. Different tapping process conditions were investigated computationally using finite element (FE) approach and as a result cutting forces, torques and power consumed were observed. The study provides a useful understanding towards the tapping process mechanics with respect to different cutting parameters.
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