Готові списки джерел за темами / Aerospace Structure

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Автор: Grafiati
Опубліковано: 14 березня 2023

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Статті в журналах з теми "Aerospace Structure"

1

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

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2

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

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3

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

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Abstract Carbon-epoxy composite materials, due to their high strength in relation to mass, are increasingly used in the construction of aircraft structures, however, they are susceptible to a number of damages. One of the most common is delamination, which is a serious problem in the context of safe operation of such structures. As part of the TEBUK project, the Institute of Aviation has developed a methodology for forecasting the propagation of delamination. In order to validate the proposed method, an aerial structure demonstrator, modelled on the horizontal stabilizer of the I-23 Manager aircraft, was carried out. However, in order to carry out the validation, it was necessary to "simplify" the demonstrator model. The paper presents a numerical analysis conducted in order to separate from the TEBUK demonstrator model a fragment of the structure, which was used to study the delamination area, as an equivalent of the whole demonstrator. Subcomponent selection was carried out in several stages, narrowing down the analysed area covering delamination in subsequent steps and verifying the compliance of specific parameters with the same parameters obtained in a full demonstrator model. The parameters compared were: energy release rate values on the delamination front line and strain values in the delamination area. The numerical analyses presented in the paper were performed with the use of the MSC.Marc/Mentat calculation package. As a result of the analyses, a fragment of the structure was selected, which allows to significantly reduce the time and labour consumption of the production of the studied object, as well as to facilitate experimental research.
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4

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

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The characteristics of composite materials are of high importance to engineering applications; therefore the increasing use as a substitute for conventional materials, especially in the field of aircraft and space industries. It is a known fact that researchers use finite element programs for the design and analysis of composite structures, use of symmetrical conditions especially in complicated structures, in the modeling and analysis phase of the design, to reduce processing time, memory size required, and simplifying complicated calculations, as well as considering the response of composite structures to different loading conditions to be identical to that of metallic structures. Finite element methods are a popular method used to analyze composite laminate structures. The design of laminated composite structures includes phases that do not exist in the design of traditional metallic structures, for instance, the choice of possible material combinations is huge and the mechanical properties of a composite structure, which are anisotropic by nature, are created in the design phase with the choice of the appropriate fiber orientations and stacking sequence. The use of finite element programs (conventional analysis usually applied in the case of orthotropic materials) to analysis composite structures especially those manufactured using angle ply laminate techniques or a combination of cross and angle ply techniques, as well considering the loading response of the composite structure to be identical to that of structures made of traditional materials, has made the use of, and the results obtained by using such analysis techniques and conditions questionable. Hence, the main objective of this paper is to highlight and present the results obtained when analyzing and modeling symmetrical conditions as applied to commercial materials and that applied to composite laminates. A comparison case study is carried out using cross-ply and angle-ply laminates which concluded that, if the composition of laminate structure is pure cross-ply, the FEA is well suited for predicting the mechanical response of composite structure using principle of symmetry condition. On the other hand that is not the case for angle-ply or mixed-ply laminate structure.
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5

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

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6

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

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7

Horton, B., Y. Song, D. Jegley, F. Collier, and J. Bayandor. "Predictive analysis of stitched aerospace structures for advanced aircraft." Aeronautical Journal 124, no. 1271 (November 18, 2019): 44–54. http://dx.doi.org/10.1017/aer.2019.137.

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ABSTRACTIn recent years, the aviation industry has taken a leading role in the integration of composite structures to develop lighter and more fuel efficient aircraft. Among the leading concepts to achieve this goal is the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept. The focus of most PRSEUS studies has been on developing an hybrid wing body structure, with only a few discussing the application of PRSEUS to a tube-wing fuselage structure. Additionally, the majority of investigations for PRSEUS have focused on experimental validation of anticipated benefits rather than developing a methodology to capture the behavior of stitched structure analytically. This paper presents an overview of a numerical methodology capable of accurately describing PRSEUS’ construction and how it may be implemented in a barrel fuselage platform resorting to high-fidelity mesoscale modeling techniques. The methodology benefits from fresh user defined strategies developed in a commercially available finite element analysis environment. It further proposes a new approach for improving the ability to predict deformation in stitched composites, allowing for a better understanding of the intricate behavior and subtleties of stitched aerospace structures.
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8

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

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Aiming at the problem that the manufacturing process of our aerospace products is relatively discrete and the lack of appropriate quality monitoring and feedback mechanism, a method of coding for aerospace product quality DNA was proposed. Based on the structure of biological DNA and the theory of quality assessment, equipment diagnosis and quality traceability, the biological DNA structure was transformed into the structure of aerospace product quality DNA, and the concept of aerospace product quality DNA was defined, including the genetic and variation characteristics of aerospace product quality DNA. The coding rules of aerospace product quality DNA were designed, and the designed encoding rules are applied to the case of welding of wall panels in the manufacturing process of aerospace products. The results show that the coding method can monitor and feedback the core information related to quality in the manufacturing process of aerospace products.
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9

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

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

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Дисертації з теми "Aerospace Structure"

1

Ahn, Junghyun. "Integrated analysis procedure of aerospace composite structure." Thesis, Massachusetts Institute of Technology, 2008. http://hdl.handle.net/1721.1/43106.

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Thesis (S.M.)--Massachusetts Institute of Technology, System Design and Management Program, 2008.
Includes bibliographical references (p. 50).
The emergence of composite material application in major commercial aircraft design, represented by the Boeing 787 and Airbus A350-XWB, signals a new era in the aerospace industry. The high stiffness to weight ratio of continuous fiber composites (CFC) makes CFCs one of the most important materials to be introduced in modern aircraft industry. In addition to inherent strength (per given weight) of CFCs, they also offer the unusual opportunity to design the structure and material concurrently. The directional properties (and the ability to change these properties through the design process) of composite materials can be used in aeroelastically tailored wings, the fuselage and other critical areas. Due to the longer lifecycle (25-30 years) of a commercial airliner and the tools and processes developed for the airplane of previous product development cycles, new technology often ends up being deployed less effectively because of the mismatch in the technical potential (what can be done) vs. design tools and processes (what was done before). Tools and processes need to be current to take advantage of latest technology, and this thesis will describe one possible approach in primary composite structural design area using integrated structural analysis
by Junghyun Ahn.
S.M.
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2

Key, Ross A. "Automated manufacturing processes for secondary structure aerospace composites." Thesis, University of Nottingham, 2016. http://eprints.nottingham.ac.uk/33572/.

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As projected manufacturing rates for commercial aircraft increase to levels of multiple ship sets per day from individual manufacturing facilities, GE Aviation have expressed the need for a shift in composites secondary structure manufacturing philosophy. Traditional manufacturing processes tend to be touch labour intensive and hence costly. The manual placement of large numbers of individual ply profiles, lengthy debulking operations and complex cure cycles, result in excessive component lead times and manufacturing costs. As a result, direct labour cost is a major factor in the total economies of production processes. The implementation of industrial robotics has proved highly successful in automotive manufacturing, and various methods for automating individual aspects of the composites manufacturing process have been suggested. Technical cost modelling has been used to anticipate the production costs of a prototype secondary structure component, as supplied by GE Aviation, through direct simulation of the existing manufacturing process. This work has clearly highlighted the potential for cost and cycle time reductions if process automation can be successfully introduced. Observation of the existing manufacturing process has allowed three alternative manufacturing scenarios to be considered with respect to cost-effectiveness and feasibility, whilst highlighting long term cost benefits. Investigations have been undertaken to identify and evaluate alternative material and processing methodologies ranging from resin infused woven dry fabrics to UD prepreg tape and tow. In addition, candidate processing routes have been systematically evaluated using design of experiments techniques, which focussed on assessing the feasibility and technology readiness of robotic deposition and consolidation methodologies, including pick and place and debulking. Process automation in these areas has the potential for total component cost and cycle time reductions in the order of 2.8 to 21.6 and 0.6 to 63.4 per cent respectively. The quasi-static mechanical testing of a range of face sheet materials has provided a performance assessment based on tensile, compressive and shear properties and laminate Vf. Findings suggest that materials offering increased suitability for automation typically have reduced mechanical performance when compared to candidate prepregs; tensile modulus and strength reductions of 5 and 34 per cent were reported when comparing a 6k woven 2X2 twill fabric and equivalent prepreg respectively. Furthermore, 26 and 4 per cent reductions in tensile modulus and 38 and 40 per cent reductions in tensile strength were observed for 179 and 318gsm UD NCF, when compared with a candidate UD prepreg. Data has also been presented on the effect of varying the traditional consolidation frequency and methodology. While earlier findings suggest that debulking has little effect on the laminate tensile modulus; ply compaction level varies considerably. Furthermore, it has been shown that on-the-fly consolidation, using a robotically mounted, roller-based end effector has the advantages of mechanical performance retention, cycle time reduction and repeatable laminate post cure thickness. In addition, when compared with candidate woven and UD prepreg laminates manufactured using the traditional vacuum bagging approach; equivalent tensile modulus, strength and fibre volume fraction have been observed and with less variability. Handling characteristics inherent to vacuum and needle grippers, including pickup performance, defined as the pickup or holding force required to overcome fabric weight, shear force performance; the maximum force that can be exerted on the fabric before the onset of slip, and the accuracy with which non-rigid-materials (NRMs) can be handled, have also been considered. The achievable positional accuracy of robotically pick and placed prepreg plies greatly exceeds that of dry fabrics in all cases and with less variability, irrespective of the gripping mechanism used. Vacuum grippers exhibit more uniform positional error and increased positional accuracy when handling dry fabrics, whilst needle grippers outperformed the vacuum alternative when handling prepregs, irrespective of form. Robotic pick and place solutions offer low variability in ply positional error with a guaranteed placement accuracy of ±0.8mm and ±2.3mm for prepregs and dry fabrics respectively. Characterisation of the gap type defect and butt and overlapping joining methodologies has provided a performance trend based on ply positional error. Quasi-static mechanical testing has revealed that laminates with equivalent tensile modulus to an un-spliced control could be achieved. However, significant reductions in the tensile strength and an increase in overall laminate thickness and thickness variation highlighted the negative effect of ply splicing on laminate performance. However, it has been shown that a robotic placement accuracy of ±0.8mm gives rise to acceptable tensile strength reductions in candidate prepreg laminates. The up-scaling of laminate level robotic manipulators has been discussed and addressed in conjunction with the commissioning of a flexible robotic manufacturing cell, facilitating the manufacture of full-scale secondary structure aerospace components. Comparisons have been made between a benchmark prepreg panel, manufactured using traditional manual methods and alternative dry fabric and prepreg panels manufactured using increased levels of process automation. In each case, manufacturing feasibility, mechanical performance and component geometric accuracy have been assessed. It has been shown that there are significant advantages to be gained from the implementation of robotic automation within the traditional manufacturing process. Component cost and cycle time reductions, coupled with the processing and performance advantages and increased suitability to automation of woven dry fibre materials are clear. Findings which support a key driver of this project, which seeks to justify alternative dry fabrics as a viable alternative to traditional prepreg broadgoods for the manufacture of secondary structure aerospace components.
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3

Hu, Zhuopei. "Finite Element Modeling of Aerospace Materials and Structure." University of Akron / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=akron1344224158.

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4

Zheng, LiangKan 1972. "Fluid-structure coupling for aeroelastic computations in the time domain using low fidelity structural models." Thesis, McGill University, 2005. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=99127.

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Flutter analysis plays an important role in the design and development of aircraft wings because of the information it provides regarding the flight envelope of the aircraft. With the coupling of the flow and structural solver, the flutter boundary of wings can be evaluated in the time domain. This study: First, computes the aeroelastic response for a typical sweptback wing section model by coupling a flow solver and a two degree of freedom structural equation of motion solver to predict the flutter boundary of an airfoil at different Mach numbers. The results agree well with previous numerical results, and the transonic-dip phenomenon can be observed. Second, a new coupling approach is introduced to conservatively transfer the load and displacement between the flow solver and the structural solver for 3-D flow. By coupling the flow solver and a low fidelity finite element structural model, the flutter point of AGARD wing 445.6 at Mach number 0.499 is computed. The flutter point agrees well with experimental results and previous numerical results.
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5

Seddon, Caroline Michelle. "Modelling transient dynamic fluid-structure interaction in aerospace applications." Thesis, University of Salford, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.492434.

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Although significant progress has been made in the study of dynamic loading of aircraft structures, several areas have been identified that require further research. In particular, attention is drawn to problems involving transient, dynamic fluid-structure interaction, where fluids play an important role, heavily influencing the response of the structure to the applied dynamic load. In this work the use of existing numerical modelling techniques for the evaluation of such problems is investigated.
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6

Bhatti, Wasim. "Mechanical integration of a PEM fuel cell for a multifunctional aerospace structure." Thesis, Loughborough University, 2016. https://dspace.lboro.ac.uk/2134/21513.

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A multifunctional structural polymer electrolyte membrane (PEM) fuel cell was designed, developed and manufactured. The structural fuel cell was designed to represent the rear rib section of an aircraft wing. Custom membrane electrode assemblies (MEA s) were manufactured in house. Each MEA had an active area of 25cm2.The platinum loading on each electrode (anode and cathode) was 0.5mg/cm2. Sandwiched between the electrodes was a Nafion 212 electrolyte membrane. Additional components of the structural fuel included metallic bipolar plates and end plates. Initially all the components were manufactured from aluminium in order for the structural fuel cell to closely represent an aircraft wing rib. However due to corrosion problems the bipolar plate had to be manufactured from marine grade 361L stainless steel with a protective coating system. A number of different protective coating systems were tried with wood nickel strike, followed by a 5μm intermediate coat of silver and a 2μm gold top coat being the most successful. Full fuel cell experimental setup was developed which included balance of plant, data acquisition and control unit, and a mechanical loading assembly. Loads were applied to the structural fuel cells tip to achieve a static deflection of ±7mm and dynamic deflections of ±3mm, ±5mm, and ±7mm. Static and dynamic torsion induced 1° to 5° of twist to the structural fuel cell tip. Polarisation curves were produced for each load case. Finite element analysis was used to determine the structural fuel cell displacement, and stress/strain over the range of mechanical loads. The structural fuel cells peak power performance dropped 3.9% from 5.5 watts to 5.3 watts during static bending and 2% from 6.2 watts to 6.1 watts during static torsion. During dynamic bending (2000 cycles) the structural fuel cell peak power performance dropped 11% from 6.7 watts to 6 watts (3mm deflection at 190N), 23% from 6.3 watts to 4.8 watts (5mm deflection at 270N), and 41% from 7.2 watts to 5 watts (7mm deflection at 350N). During dynamic torsion (2000 cycles) the structural fuel cell peak power performance dropped 16% from 6 watts to 5.1 watt (3° of torsional loading), and 30% from 6.4 watts to 4.3 watts (5° of torsional loading). The simulated (finite element modelling) displacement of -6.6mm (At maximum bending load of 364.95N) was within 9% of the actual measured displacement of -7.2mm at 364.95N. Furthermore the majority of the simulated strain values were within 10% of the actual measured strain for the structural fuel cell.
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7

Palsule, Sanjay. "Structure and properties of aerospace molecular composites : third generation polymers." Thesis, Heriot-Watt University, 1994. http://hdl.handle.net/10399/1388.

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8

Khataee, Amin. "Structure and properties of some Ti-Al-Ru alloys." Thesis, Imperial College London, 1987. http://hdl.handle.net/10044/1/46915.

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9

Liang, Lijun. "Experimental investigation of an aeroelastic structure with continuous nonlinear stiffness." Thesis, McGill University, 2003. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=80123.

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An experimental investigation is presented for the aeroelastic response of a two-degree-of-freedom airfoil positioned in an incompressible flow. In particular, the effects of cubic structural nonlinearities in the pitch degree-of-freedom are considered. These nonlinearities are introduced via a specially designed pitch cam, which permits different degrees of nonlinearity, as well as a linear system, to be obtained.
Several linear and nonlinear system tests are presented, and the results compared and analyzed. The effects of linear plunge stiffness on the stability of the aeroelastic system are discussed, and the nonlinear system response is studied for different degrees of cubic nonlinearity in pitch.
In several nonlinear system tests, limit cycle oscillations (LCO) are observed when the air speed is above the linear flutter speed. The effects of airfoil initial conditions and air speeds on the LCO amplitude, frequency, and convergence rate are studied.
The effective linear flutter speed is predicted using the so-called "flutter-margin" method for both the linear and nonlinear cases. The prediction results for the nonlinear cases are compared with those for the linear cases and with the actual flutter speed.
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10

Ozsoy, Serhan. "Vibration Induced Stress And Accelerated Life Analyses Of An Aerospace Structure." Master's thesis, METU, 2006. http://etd.lib.metu.edu.tr/upload/2/12606966/index.pdf.

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Fatigue failure of metallic structures operating under dynamic loading is a common occurrence in engineering applications. It is difficult to estimate the response of complicated systems analytically, due to structure&
#8217
s dynamic characteristics and varying loadings. Therefore, experimental, numerical or a combination of both methods are used for fatigue evaluations. Fatigue failure can occur on systems and platforms as well as components to be mounted on the platform. In this thesis, a helicopter&
#8217
s Missile Warning Sensor - Cowling assembly is analyzed. Analytical, numerical and experimental approaches are used wherever necessary to perform stress and fatigue analyses. Operational flight tests are used for obtaining the loading history at the analyzed location by using sensors. Operational vibration profiles are created by synthesizing the data (LMS Mission Synthesis). Numerical fatigue analysis of the assembly is done for determining the natural modes and the critical locations on the assembly by using a finite element model (MSC Fatigue). In addition, numerical multiaxial PSD analysis is performed for relating the experimental results (Ansys). Residual stresses due to riveting are determined (MSC Marc) and included in experimental analysis as mean stresses. Bolt analysis is performed analytically (Hexagon) for keeping the v assembly stresses in safe levels while mounting the experimental prototype to the test fixture. Fatigue tests for determining the accelerated life parameters are done by an electromagnetic shaker and stress data is collected. Afterwards, fatigue test is performed for determining whether the assembly satisfies the required operational life. Resonance test is performed at the frequency in which the critical location is at resonance, since there was no failure observed after fatigue testing. A failure is obtained during resonance test. At the end of the study, an analytical equation is brought up which relates accelerated life test durations with equivalent alternating stresses. Therefore, optimization of the accelerated life test duration can be done, especially in military applications, by avoiding the maximum stress level to reach or exceed the yield limit.
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Книги з теми "Aerospace Structure"

1

Ryzhikova, tamara. Marketing in the aerospace field. ru: INFRA-M Academic Publishing LLC., 2020. http://dx.doi.org/10.12737/1003199.

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The tutorial provides an overview of the main methodological approaches to the analysis of the market of rocket and space technology and services on the basis of its specific features, methods of evaluating competition and its justification, the reinterpretation of basic marketing tools and approaches in combination with innovative ideas and methods of achieving high economic results in the space market. The main aim is to provide future marketers with the necessary material, methods, technologies and tools with which to solve various problems related to the understanding of the structure of the space market, the company's place in the market, its competitive position and overall competitiveness. Meets the requirements of Federal state educational standards of higher education of the last generation. Intended for undergraduates and academics in aerospace orientation, postgraduate students, marketing analysts, marketers, corporate executives and agencies of the military-industrial complex.
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2

H, Laakso John, and Langley Research Center, eds. System integration and demonstration of adhesive bonded high temperature aluminum alloys for aerospace structure: Phase II. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.

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3

Center, Langley Research, ed. NASA-UVa light aerospace alloy and structure technology program supplement: Aluminum-based materials for high speed aircraft. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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4

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. NASA-UVa light aerospace alloy and structure technology program supplement: Aluminum-based materials for high speed aircraft. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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5

Starke, E. A. NASA-UVa Light Aerospace Alloy and Structure Technology Program supplement: aluminum-based materials for high speed aircraft. Hampton, Va: Langley Research Center, 1993.

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6

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. NASA-UVa light aerospace alloy and structure technology program suppleyment: Aluminum-based materials for high speed aircraft. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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7

Craig, J. I. (James I.), 1942- and SpringerLink (Online service), eds. Structural analysis: With applications to aerospace structures. Dordrecht: Springer, 2009.

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8

J, Loughlan, ed. Aerospace structures. London: Elsevier Applied Science, 1990.

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9

L, Regel £. L., and United States. National Aeronautics and Space Administration., eds. Modelling directional soldification: Progress report on grant NAG8-831, 1 May 1991 to 31 October 1992. Potsdam, N.Y: Clarkson University, 1991.

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10

L, Regelʹ L., and United States. National Aeronautics and Space Administration., eds. Modelling directional soldification: Progress report on grant NAG8-831, 1 May 1991 to 31 October 1992. Potsdam, N.Y: Clarkson University, 1991.

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Частини книг з теми "Aerospace Structure"

1

Krumweide, Gary C., and Eddy A. Derby. "Aerospace Equipment and Instrument Structure." In Handbook of Composites, 1004–21. Boston, MA: Springer US, 1998. http://dx.doi.org/10.1007/978-1-4615-6389-1_48.

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2

Zhang, Yipeng, Hai Huang, and Shenyan Chen. "Structure analysis and optimisation of SSS-1 microsatellite." In Aerospace and Associated Technology, 351–56. London: Routledge, 2022. http://dx.doi.org/10.1201/9781003324539-64.

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3

Gunasegeran, Muthukumaran, P. Edwin Sudhagar, and A. Ananda Babu. "Failure of Composite Structure." In Repair of Advanced Composites for Aerospace Applications, 103–11. Boca Raton: CRC Press, 2022. http://dx.doi.org/10.1201/9781003200994-9.

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Arviso, Michael, D. Gregory Tipton, and Patrick S. Hunter. "Preliminary Validation of a Complex Aerospace Structure." In Structural Dynamics, Volume 3, 741–51. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4419-9834-7_64.

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Pironneau, Olivier. "Numerical Study of a Monolithic Fluid–Structure Formulation." In Variational Analysis and Aerospace Engineering, 401–20. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-45680-5_15.

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6

Sanjay, A. V., and B. Sudarshan. "Effect of oblique shocks interaction on the inlet structure in a hypersonic flow." In Aerospace and Associated Technology, 522–27. London: Routledge, 2022. http://dx.doi.org/10.1201/9781003324539-96.

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Bracco, F. V. "Structure of High-Speed Full-Cone Sprays." In Recent Advances in the Aerospace Sciences, 189–212. Boston, MA: Springer US, 1985. http://dx.doi.org/10.1007/978-1-4684-4298-4_10.

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Acharjee, Devjit, Bandyopadhyay, and Debasish Bandyopadhyay. "Numerical study of tilted multi-storied RCC buildings on shallow foundations considering soil-structure interaction." In Aerospace and Associated Technology, 284–89. London: Routledge, 2022. http://dx.doi.org/10.1201/9781003324539-51.

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9

Kerschen, G., L. Soula, J. B. Vergniaud, and A. Newerla. "Assessment of Nonlinear System Identification Methods using the SmallSat Spacecraft Structure." In Advanced Aerospace Applications, Volume 1, 203–19. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4419-9302-1_18.

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Sun, Yixuan, Shikui Luo, Jie Bai, Zijia Liu, and Shaofan Tang. "Design and Optimization of the Flexible Support Structure for Space Mirror." In Aerospace Mechatronics and Control Technology, 119–28. Singapore: Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-6640-7_10.

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Тези доповідей конференцій з теми "Aerospace Structure"

1

Naydenkin, E. V., I. P. Mishin, I. V. Ratochka, and V. A. Vinokurov. "High-strength nanostructured titanium alloy for aerospace industry." In ADVANCED MATERIALS WITH HIERARCHICAL STRUCTURE FOR NEW TECHNOLOGIES AND RELIABLE STRUCTURES. AIP Publishing LLC, 2015. http://dx.doi.org/10.1063/1.4932850.

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2

Joshi, Ashok. "Structure - Control Interactions in Flexible Aerospace Vehicles." In 51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
18th AIAA/ASME/AHS Adaptive Structures Conference
12th. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-2948.

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3

Mariano, Silvio Luiz, Marcelo Gomes da Silva, André Moreno da Costa Moreira, Everaldo de Barros, and Leandro Ribeiro de Camargo. "Modal Correlation of an Aerospace Structure." In 2006 SAE Brasil Congress and Exhibit. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2006. http://dx.doi.org/10.4271/2006-01-2786.

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4

Kawabe, Hiroki, Yuichiro Aoki, and Toshiya Nakamura. "Biological Optimization of Aerospace Shell Structure." In AIAA SCITECH 2022 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2022. http://dx.doi.org/10.2514/6.2022-2602.

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5

Kim, Seung Jo, Ki-Ook Kim, Jungsun Park, Maenghyo Cho, Eui Sup Shin, and Jin Yeon Cho. "Advancements of Aerospace Computational Structure Technology in Korea." In 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-2439.

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6

Blair, Max, and Greg Reich. "A demonstration of CAD/CAM/CAE in a fully associative aerospace design environment." In 37th Structure, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-1630.

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ELLIS, DAVID. "Overview - Design of an efficient lightweight airframe structure forthe National Aerospace Plane." In 30th Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-1406.

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8

Eremenko, A. "Aquarius main structure configuration." In 2013 IEEE Aerospace Conference. IEEE, 2013. http://dx.doi.org/10.1109/aero.2013.6496819.

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9

Zorn, Joshua E., and Roger L. Davis. "Structural Dynamics Solution Procedure for Multi-Discipline Fluid/Structure/Thermal Simulation." In 53rd AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-0281.

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Alexander, Eric, Ben Carey, Michael DiNardo, Herman Gill, Joey Gonzalez, Mike Harry, Alex Isidro, et al. "Validated Aerospace Soft Impact Modeling Platform." In ASME 2012 Fluids Engineering Division Summer Meeting collocated with the ASME 2012 Heat Transfer Summer Conference and the ASME 2012 10th International Conference on Nanochannels, Microchannels, and Minichannels. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/fedsm2012-72459.

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Анотація:
The research has been dedicated to developing a virtual crashworthiness platform for large advanced aircraft structures when subjected to water ditching incidents. A numerical design tool, incorporating fluid-structure interaction analysis module, was created to assess damage tolerance in future aerospace design concepts to help with the prognosis of structural failure. To accomplish this, an experimental water impact set up was used to calibrate and validate the developed detailed virtual model. Specific data acquisition techniques implemented allowed for the capture of strain distribution and impact energy dissipation, used to validate the simulation platform.
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Звіти організацій з теми "Aerospace Structure"

1

Swanson, F., E. Kamykowski, M. Horn, and N. Holden. Neutron radiography of aerospace structure hidden corrosion. Office of Scientific and Technical Information (OSTI), September 1995. http://dx.doi.org/10.2172/10130409.

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2

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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3

Atluri, S. N. AASERT-Structural Integrity of Aging of Aerospace Structures and Repairs. Fort Belvoir, VA: Defense Technical Information Center, December 1996. http://dx.doi.org/10.21236/ada326704.

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4

Venkayya, Vipperla B. Aerospace Structures Design on Computers. Fort Belvoir, VA: Defense Technical Information Center, March 1989. http://dx.doi.org/10.21236/ada208811.

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5

Grandhi, Ramana V., and Geetha Bharatram. Multiobjective Optimization of Aerospace Structures. Fort Belvoir, VA: Defense Technical Information Center, July 1992. http://dx.doi.org/10.21236/ada260433.

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6

Farhat, Charbel. Multidisciplinary Thermal Analysis of Hot Aerospace Structures. Fort Belvoir, VA: Defense Technical Information Center, May 2010. http://dx.doi.org/10.21236/ada564851.

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Grandt, A. F., Farris Jr., Hillberry T. N., and B. H. Analysis of Widespread Fatigue Damage in Aerospace Structures. Fort Belvoir, VA: Defense Technical Information Center, February 1999. http://dx.doi.org/10.21236/ada360820.

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8

Selvam, R. P., and Zu-Qing Qu. Adaptive Navier Stokes Flow Solver for Aerospace Structures. Fort Belvoir, VA: Defense Technical Information Center, May 2004. http://dx.doi.org/10.21236/ada424479.

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9

Atwood, Clinton J., Thomas Eugene Voth, David G. Taggart, David Dennis Gill, Joshua H. Robbins, and Peter Dewhurst. Titanium cholla : lightweight, high-strength structures for aerospace applications. Office of Scientific and Technical Information (OSTI), October 2007. http://dx.doi.org/10.2172/922082.

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10

Webb, Philip. Unsettled Issues on the Viability and Cost-Effectiveness of Automation in Aerospace Manufacturing. SAE International, February 2021. http://dx.doi.org/10.4271/epr2021005.

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Анотація:
The aerospace manufacturing industry is, in many ways, one of the most sophisticated commercial manufacturing systems in existence. It uses cutting-edge materials to build highly complex, safety-critical structures and parts. However, it still relies largely upon human skill and dexterity during assembly. There are increasing efforts to introduce automation, but uptake is still relatively low. Why is this and what needs to be done? Some may point to part size or the need for accuracy. However, as with any complex issue, the problems are multifactorial. There are no right or wrong answers to the automation conundrum and indeed there are many contradictions and unsettled aspects still to be resolved. Unsettled Issues on the Viability and Cost-Effectiveness of Automation in Aerospace Manufacturing builds a comprehensive picture of industry views and attitudes backed by technical analysis to answer some of the most pressing questions facing robotic aerospace manufacturing.
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