Gotowe bibliografie tematyczne / Aerospace structures

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Gotowa bibliografia na temat „Aerospace structures”

Autor: Grafiati

Data publikacji: 4 czerwca 2021

Data aktualizacji: 23 lutego 2023

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Artykuły w czasopismach na temat "Aerospace structures"

Krebs, Neil E., i Eric W. Rahnenfuehrer. "Aerospace Application of Braided Structures". Journal of the American Helicopter Society 34, nr 3 (1.07.1989): 69–74. http://dx.doi.org/10.4050/jahs.34.69.

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Springer, George S. "Aerospace Composites in Civil Structures". IABSE Symposium Report 92, nr 31 (1.01.2006): 13–19. http://dx.doi.org/10.2749/222137806796168859.

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Hanuska, A. R., E. P. Scott i K. Daryabeigi. "Thermal Characterization of Aerospace Structures". Journal of Thermophysics and Heat Transfer 14, nr 3 (lipiec 2000): 322–29. http://dx.doi.org/10.2514/2.6548.

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Dorey, G., C. J. Peel i P. T. Curtis. "Advanced Materials for Aerospace Structures". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 208, nr 1 (styczeń 1994): 1–8. http://dx.doi.org/10.1243/pime_proc_1994_208_247_02.

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

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Hiraoka, Koichi. "Weight Reduction of Aerospace Structures". Journal of the Society of Mechanical Engineers 96, nr 893 (1993): 285–89. http://dx.doi.org/10.1299/jsmemag.96.893_285.

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

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Jadhav, Prakash. "Passive Morphing in Aerospace Composite Structures". Key Engineering Materials 889 (16.06.2021): 53–58. http://dx.doi.org/10.4028/www.scientific.net/kem.889.53.

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

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Spottswood, S. Michael, Benjamin P. Smarslok, Ricardo A. Perez, Timothy J. Beberniss, Benjamin J. Hagen, Zachary B. Riley, Kirk R. Brouwer i David A. Ehrhardt. "Supersonic Aerothermoelastic Experiments of Aerospace Structures". AIAA Journal 59, nr 12 (grudzień 2021): 5029–48. http://dx.doi.org/10.2514/1.j060403.

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Baldelli, Dario H., i Ricardo S. Sanchez Pena. "Uncertainty Modeling in Aerospace Flexible Structures". Journal of Guidance, Control, and Dynamics 22, nr 4 (lipiec 1999): 611–14. http://dx.doi.org/10.2514/2.7637.

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Rittweger, A., J. Albus, E. Hornung, H. Öry i P. Mourey. "Passive Damping Devices For Aerospace Structures". Acta Astronautica 50, nr 10 (maj 2002): 597–608. http://dx.doi.org/10.1016/s0094-5765(01)00220-x.

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Rozprawy doktorskie na temat "Aerospace structures"

Jenett, Benjamin (Benjamin Eric). "Digital material aerospace structures". Thesis, Massachusetts Institute of Technology, 2015. http://hdl.handle.net/1721.1/101837.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Civil and Environmental Engineering, 2015.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 71-76).
This thesis explores the design, fabrication, and performance of digital materials in aerospace structures in three areas: (1) a morphing wing design that adjusts its form to respond to different behavioral requirements; (2) an automated assembly method for truss column structures; and (3) an analysis of the payload and structural performance requirements of space structure elements made from digital materials. Aerospace structures are among the most difficult to design, engineer, and manufacture. Digital materials are discrete building block parts, reversibly joined, with a discrete set of positions and orientations. Aerospace structures built from digital materials have high performance characteristics that can surpass current technology, while also offering potential for analysis simplification and assembly automation. First, this thesis presents a novel approach for the design, analysis, and manufacturing of composite aerostructures through the use of digital materials. This approach can be used to create morphing wing structures with customizable structural properties, and the simplified composite fabrication strategy results in rapid manufacturing time with future potential for automation. The presented approach combines aircraft structure with morphing technology to accomplish tuned global deformation with a single degree of freedom actuator. Guidelines are proposed to design a digital material morphing wing, a prototype is manufactured and assembled, and preliminary experimental wind tunnel testing is conducted. Seconds, automatic deployment of structures has been a focus of much academic and industrial work on infrastructure applications and robotics in general. This thesis presents a robotic truss assembler designed for space applications - the Space Robot Universal Truss System (SpRoUTS) - that reversibly assembles a truss column from a feedstock of flat-packed components, by folding the sides of each component up and locking onto the assembled structure. The thesis describes the design and implementation of the robot and shows that an assembled truss compares favorably with prior truss deployment systems. Thirds, space structures are limited by launch shroud mass and volume constraints. Digital material space structures can be reversibly assembled on orbit by autonomous relative robots using discrete, incremental parts. This will enable the on-orbit assembly of larger space structures than currently possible. The engineering of these structures, from macro scale to discrete part scale, is presented. Comparison with traditional structural elements is shown and favorable mechanical performance as well as the ability to efficiently transport the material in a medium to heavy launch vehicle. In summary, this thesis contributes the methodology and evaluation of novel applications of digital materials in aerospace structures.
by Benjamin Jenett.
S.M.

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Spendley, Paul R. "Design allowables for composite aerospace structures". Thesis, University of Surrey, 2012. http://epubs.surrey.ac.uk/810072/.

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Recent developments in aircraft design have seen the Airbus A380 and the Boeing Dreamliner employ significant amounts of advanced composite materials. There is some thought however, und the motivation for this current work, that these materials continue to suffer a weight penalty. In this work tests required to generate design allowables which accommodate environmental effects and holes arc performed on Carbon/epoxy quasi-isotropic laminatcs. The test data is treated statistically to provide B-basis allowables for each specimen type and condition. It was seen that the notched specimens (coupons containing a centrally placed through hole) displayed significantly less scatter in strength than unnotched specimens. This is significant when considering the widespread use of deterministic knock-down factors as an alternative route to obtain design allowables which accommodate environmental effects and/or holes. This results in an over-conservative design allowable being employed in subsequent structural design calculations. The possibility for using notched coupons to determine design allowables was explored using the COG (Critical Damage Growth) model. This showed that. given two of the three parameters. the unnotched and notched strength, and fracture toughness the variation in strengths could be reasonable predicted. This leads to a more representative design allowable by maintaining the statistical nature of the B-basis allowable. During the statistical treatment of the test data it was also seen that although current aerospace guidelines recommend a particular distribution model (i.e. the Wcibull distribution) this can also leads to an artificially reduced design allowable. These findings suggest that the use of notched specimens can lead to a reduced development test programme and reduced structural weight.

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Hanuska, Alexander Robert Jr. "Thermal Characterization of Complex Aerospace Structures". Thesis, Virginia Tech, 1998. http://hdl.handle.net/10919/36617.

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Predicting the performance of complex structures exposed to harsh thermal environments is a crucial issue in many of today's aerospace and space designs. To predict the thermal stresses a structure might be exposed to, the thermal properties of the independent materials used in the design of the structure need to be known. Therefore, a noninvasive estimation procedure involving Genetic Algorithms was developed to determine the various thermal properties needed to adequately model the Outer Wing Subcomponent (OWS), a structure located at the trailing edge of the High Speed Civil Transport's (HSCT) wing tip. Due to the nature of the nonlinear least-squares estimation method used in this study, both theoretical and experimental temperature histories were required. Several one-dimensional and two-dimensional finite element models of the OWS were developed to compute the transient theoretical temperature histories. The experimental data were obtained from optimized experiments that were run at various surrounding temperature settings to investigate the temperature dependence of the estimated properties. An experimental optimization was performed to provide the most accurate estimates and reduce the confidence intervals. The simultaneous estimation of eight thermal properties, including the volumetric heat capacities and out-of-plane thermal conductivities of the facesheets, the honeycomb, the skins, and the torque tubes, was successfully completed with the one-dimensional model and the results used to evaluate the remaining in-plane thermal conductivities of the facesheets, the honeycomb, the skins, and the torque tubes with the two-dimensional model. Although experimental optimization did not eliminate all correlation between the parameters, the minimization procedure based on the Genetic Algorithm performed extremely well, despite the high degree of correlation and low sensitivity of many of the parameters.
Master of Science

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White, Caleb, i caleb white@rmit edu au. "Health Monitoring of Bonded Composite Aerospace Structures". RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2009. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20090602.142122.

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Airframe assemblers have long recognised that for a new aircraft to be successful it must use less fuel, have lower maintenance requirements, and be more affordable. One common tactic is the use of innovative materials, such as advanced composites. Composite materials are suited to structural connection by adhesive bonding, which minimises the need for inefficient mechanical fastening. The aim of this PhD project was to investigate the application of existing, yet immature Structural Health Monitoring (SHM) techniques to adhesively bonded composite aerospace structures. The PhD study focused on two emerging SHM technologies - frequency response and comparative vacuum monitoring (CVM). This project aimed to provide missing critical information for each technique. This included determining sensitivity to damage, repeatability of results, and operating limitations for the frequency response method. Study of the CVM technique aimed to address effectiveness of damage detection, manufacture of sensor cavities, and the influence of sensor integration on mechanical performance of bonded structures. Experimental research work is presented examining the potential of frequency response techniques for the detection of debonding in composite-to-composite external patch repairs. Natural frequencies were found to decrease over a discrete frequency range as the debond size increased; confirming that such features could be used to both detect and characterise damage. The effectiveness of the frequency response technique was then confirmed for composite patch and scarf repair specimens for free-free and fixed-fixed boundary conditions. Finally, the viability of the frequency response technique was assessed for a scarf repair of a real aircraft component, where it was found that structural damping limited the maximum useable frequency. The feasibility of CVM technique for the inspection of co-cured stiffener-skin aircraft structures was explored. The creation of sensor cavities with tapered mandrels was found to significantly alter the microstructure of the stiffener, including crimping and waviness of fibres and resin-rich zones between plies. Representative stiffened-skin structure with two sensor cavity configurations (parallel and perpendicular to the stiffener direction) was tested to failure in tension and compression. While tensile failure strength was significantly reduced for both configurations (up to 25%), no appreciable differences in compression properties were found. Two potential sensor cavity configurations were investigated for the extension of the CVM technique to pre-cured and co-bonded scarf repair schemes. The creation of radial and circumferential CVM sensor cavities was found to significantly alter the microstructure of the adhesive bond-line and the architecture of the repair material in the case of the co-bonded repair. These alterations changed the failure mode and reduced the tensile failure strength of the repair. A fibre straightening mechanism responsible for progressive failure (specific to co-bonded repairs with circumferential cavities) was identified, and subsequently supported with acoustic emission testing and numerical analysis. While fatigue performance was generally reduced by the presence of CVM cavities, the circumferential cavities appeared to retard crack progression, reducing sensitivity to the accumulation of fatigue damage. These outcomes have brought forward the implementation of SHM in bonded composite structures, which has great potential to improve the operating efficiency of next generation aircraft.

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Zhang, Haochuan. "Nonlinear aeroelastic effects in damaged composite aerospace structures". Thesis, Georgia Institute of Technology, 1996. http://hdl.handle.net/1853/12150.

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Navarro, Zafra Joaquin. "Computational mechanics of fracture on advanced aerospace structures". Thesis, University of Sheffield, 2016. http://etheses.whiterose.ac.uk/16883/.

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In this thesis, the computational simulation of cracks in advanced composite structures subjected to biaxial loading is studied. A structural integrity analysis using the eXtended Finite Element Method (XFEM) is considered for simulating the crack behaviour of a chopped fibre-glass-reinforced polyester (CGRP) cruciform specimen subjected to a quasi-static tensile biaxial loading [99]. This is the first time this problem is accomplished for computing the stress intensity factors (SIFs) produced in the biaxially loaded area of the cruciform specimen. SIFs are calculated for infinite plates under biaxial loading as well as for the CGRP cruciform specimens in order to review the possible edge effects. A new ratio relating the side of the central zone of the cruciform and the crack length is proposed. Additionally, the initiation and evolution of a three-dimensional crack are successfully simulated. Specific challenges such as the 3D crack initiation, based on a principal stress criterion, and its front propagation, in perpendicular to the principal stress direction, are conveniently addressed. No initial crack location is pre-defined and an unique crack is developed. A three-dimensional progressive damage model (PDM) is implemented within a CGRP cruciform structure for modelling its damage under loading [100]. In order to simulate the computational behaviour of the composite, the constitutive model considers an initial elastic behaviour followed by strain-softening. The initiation criterion defined is based on the maximum principal stress of the composite and once this criterion is satisfied, stiffness degradation starts. For the computation of damage, the influence of the fibre and the matrix are taken into account within the damage rule. This is the first time a three-dimensional PDM is implemented into a composite cruciform structure subjected to biaxial loading. A new approach for dynamic analysis of stationary cracks using XFEM is derived. This approach is capable of addressing dynamic and static fracture mechanics problems. Additionally, by means of this relatively simple approach, it is possible to address correctly the crack pattern of the 10 degrees off-axis laminate manufactured solving the limitation observed with progressive damage modelling. During the whole thesis, the computational outcomes have been validated by means of comparison with theoretical and experimental results.

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Lam, Daniel F. "STRAIN CONCENTRATION AND TENSION DOMINATED STIFFENED AEROSPACE STRUCTURES". University of Akron / OhioLINK, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=akron1145393262.

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Vishwanathan, Aditya. "Uncertainty Quantification for Topology Optimisation of Aerospace Structures". Thesis, University of Sydney, 2020. https://hdl.handle.net/2123/23922.

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The design and optimisation of aerospace structures is non-trivial. There are several reasons for this including, but not limited to, (1) complex problem instances (multiple objectives, constraints, loads, and boundary conditions), (2) the use of high fidelity meshes which impose significant computational burden, and (3) dealing with uncertainties in the engineering modelling. The last few decades have seen a considerable increase in research output dedicated to solving these problems, and yet the majority of papers neglect the effect of uncertainties and assume deterministic conditions. This is particularly the case for topology optimisation - a promising method for aerospace design that has seen relatively little practical application to date. This thesis will address notable gaps in the topology optimisation under uncertainty literature. Firstly, an observation underpinning the field of uncertainty quantification (UQ) is the lack of experimental studies and dealing with non-parametric variability (e.g. model unknowns, experimental and human errors etc.). Random Matrix Theory (RMT) is a method explored heavily in this thesis for the purpose of numerical and experimental UQ of aerospace structures for both parametric and non-parametric uncertainties. Next, a novel algorithm is developed using RMT to increase the efficiency of Reliability-Based topology optimisation, a formulation which has historically been limited by computational runtime. This thesis also provides contributions to Robust Topology optimisation (RTO) by integrating uncertain boundary conditions and providing experimental validation of the results. The final chapter of this thesis addresses uncertainties in multi-objective topology optimisation (MOTO), and also considers treating a single objective RTO problem as a MOTO to provide a more consistent distribution of solutions.

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Pozegic, Thomas R. "Nano-modified carbon-epoxy composite structures for aerospace applications". Thesis, University of Surrey, 2016. http://epubs.surrey.ac.uk/809603/.

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Carbon fibre reinforced plastics (CFRP) have revolutionised industries that demand high specific strength materials. With current advancements in nanotechnology there exists an opportunity to not only improve the mechanical performance of CFRP, but to also impart other functionalities, such as thermal and electrical conductivity, with the aim of reducing the reliance on metals, making CFRP attractive to many other industries. This thesis provides a comprehensive analysis of the nano-phase modification to CFRP by growing carbon nanotubes (CNTs) on carbon fibre (CF) and performing mechanical, electrical and thermal conductivity tests, with comparisons made against standard CFRP. Typical CFs are coated with a polymer sizing that plays a vital role in the mechanical performance of the composite, but as a consequence of CNT growth, it is removed. Therefore, in addition, an ‘intermediate’ composite was fabricated – based on CFs without a polymer sizing – which enabled a greater understanding of how the mechanical properties and processability of the material responds to the CNT modification. A water-cooled chemical vapour deposition system was employed for CNT growth and infused into a composite structure with an industrially relevant vacuum-assisted resin transfer moulding (VARTM) process. High quality CNTs were grown on the CF, resulting in properties not reported to date, such as strong intra-tow binding, leading to the possibility of a polymer sizing-free CFRP. A diverse set of spectroscopic, microscopic and thermal measurements were carried out to aid understanding for this CNT modification. Subsequent electrical conductivity tests performed in three directions showed 300%, 230% and 450% improvements in the ‘surface’, ‘through-thickness’ and ‘through-volume’ directions, for the CNT modified CFRP, respectively. In addition, thermal conductivity measurements performed in the through-thickness direction also gave improvements in excess of 98%, boding well for multifunctional applications of this hybrid material concept. A range of mechanical tests were performed to monitor the effect of the CNT modification, including: single fibre tensile tests, tow pull-out tests (from the polymer matrix), composite tensile tests, in-plane shear tests and interlaminar toughness tests. Single fibre tensile tests demonstrated a performance reduction of only 9.7% after subjecting the fibre to the low temperature CNT growth process, which is significantly smaller than previous reports. A reduction in tensile performance was observed in the composite tensile test however, with a reduction of 33% reduction in the ultimate tensile strength, but a 146% increase in the Young’s modulus suggests that the CNTs may have improved the interfacial interactions between the fibre and the polymer matrix. To support this, improvements of 20% in the in-plane shear stress and 74% and the shear chord modulus, were recorded. Negligible differences were observed using a pull-out test to directly measure the interfacial strength as a consequence of the inherently difficult mechanical test procedure. The fracture toughness was tested under mode-I loading of a double cantilever beam configuration and improvements of 83% for CNT modified composite alluded to CNT pull-out fracture mechanism and crack propagation amongst the microstructures. The changes in the physical properties are correlated to the microstructure modifications ensured by the low temperature CNT growth on the CF substrates used in the CFRP composites. This allows for a new generation of modified multifunctional CFRPs to be produced.

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Sebastian, Christopher. "Towards the validation of thermoacoustic modelling in aerospace structures". Thesis, University of Liverpool, 2015. http://livrepository.liverpool.ac.uk/2012079/.

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The research presented in this thesis has been performed over the course of three years under funding from the European Office of the United States Air Force (EAORD) as a part of a long-term project to collect high quality data for the validation of computational mechanics models of thermoacoustic loading. The focus is on the adaptation of stereoscopic (3D) Digital Image Correlation for use in a combined thermal and high temperature measurements. To that end, a background is provided which highlights the current state of the art in high temperature, vibration experiments and data acquisition. A system is described in which a pulsed laser of duration 4 nanoseconds is used to capture high-quality displacement and strain data from vibrating components (PL- DIC). Based on this a novel method of capturing data from a component subjected to random excitation was developed. A laser vibrometer was used along with a custom LabVIEW program to trigger the pulsed laser relative to points of maximum velocity in the components vibration cycle. A dynamic calibration procedure was performed of both a high speed DIC system and the Pulsed-Laser DIC system to assess and compare the measurement uncertainty from the respective systems. It is crucial to know the uncertainty in experimental data when using it for the validation of computational models. A new way to validate computational models of vibration behavior using full-field DIC data and image decomposition is described. This is a phasic approach in which data from the entire cycle of vibration is used. The validation assessment is performed using the expanded uncertainty calculated and a concordance correlation coefficient. An example is provided using an aerospace component to validate four different simulation conditions of a modal frequency response model. An apparatus was designed and built which uses a 10 kW array of quartz lamps to reproduce some aspects of the heating provided by the Air Force test chambers. Experiments were performed in collaboration with the University of Illinois using induction heating and a small Hastelloy plate. A thermal buckling phenomena was observed using the PL-DIC system, the first full-field results of such.

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Książki na temat "Aerospace structures"

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

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

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American Institute of Aeronautics and Astronautics, red. Morphing aerospace vehicles and structures. Chichester, West Sussex: John Wiley & Sons, 2012.

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Rowe, W. J. Prospects for intelligent aerospace structures. New York: AIAA, 1986.

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Valasek, John. Morphing aerospace vehicles and structures. Chichester, West Sussex: John Wiley & Sons, 2012.

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Valasek, John, red. Morphing Aerospace Vehicles and Structures. Chichester, UK: John Wiley & Sons, Ltd, 2012. http://dx.doi.org/10.1002/9781119964032.

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Thornton, Earl A. Thermal structures for aerospace applications. Reston, VA: American Institute of Aeronautics and Astronautics, 1996.

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American Institute of Aeronautics and Astronautics., red. Standard space systems: Structures, structural components, and structural assemblies. Reston, VA: American Institute of Aeronautics and Astronautics, 2005.

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Kruckenberg, Teresa M. Resin Transfer Moulding for Aerospace Structures. Dordrecht: Springer Netherlands, 1998.

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Soovere, J. Aerospace structures technology damping design guide. Wright-Patterson Air Force Base, Ohio: Air Force Flight Dynamics Laboratory, 1985.

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Części książek na temat "Aerospace structures"

Gialanella, Stefano, i Alessio Malandruccolo. "Alloys for Aircraft Structures". W Aerospace Alloys, 41–127. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-24440-8_3.

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Sabbagh, Harold A., R. Kim Murphy, Elias H. Sabbagh, John C. Aldrin i Jeremy S. Knopp. "Applications to Aerospace Structures". W Computational Electromagnetics and Model-Based Inversion, 337–51. New York, NY: Springer New York, 2013. http://dx.doi.org/10.1007/978-1-4419-8429-6_17.

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Millán, Javier San, i Iñaki Armendáriz. "Delamination and Debonding Growth in Composite Structures". W Springer Aerospace Technology, 63–88. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-04004-2_3.

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Henson, Grant. "Materials for Launch Vehicle Structures". W Aerospace Materials and Applications, 435–504. Reston ,VA: American Institute of Aeronautics and Astronautics, Inc., 2018. http://dx.doi.org/10.2514/5.9781624104893.0435.0504.

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Wanhill, R. J. H. "Fatigue Requirements for Aircraft Structures". W Aerospace Materials and Material Technologies, 331–52. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-2143-5_16.

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Dwibedy, Kartikeswar, i Anup Ghosh. "Damage analysis of multi-layered composite structures". W Aerospace and Associated Technology, 202–5. London: Routledge, 2022. http://dx.doi.org/10.1201/9781003324539-36.

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Peel, C. J. "Advances in Aerospace Materials and Structures". W Materials for Transportation Technology, 183–97. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2005. http://dx.doi.org/10.1002/3527606025.ch30.

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Vargas-Rojas, Erik. "Composite Sandwich Structures in Aerospace Applications". W Sandwich Composites, 293–320. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003143031-15.

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Valasek, John. "Introduction". W Morphing Aerospace Vehicles and Structures, 1–10. Chichester, UK: John Wiley & Sons, Ltd, 2012. http://dx.doi.org/10.1002/9781119964032.ch1.

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Schick, Justin R., Darren J. Hartl i Dimitris C. Lagoudas. "Incorporation of Shape Memory Alloy Actuators into Morphing Aerostructures". W Morphing Aerospace Vehicles and Structures, 231–60. Chichester, UK: John Wiley & Sons, Ltd, 2012. http://dx.doi.org/10.1002/9781119964032.ch10.

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Streszczenia konferencji na temat "Aerospace structures"

Smith, Howard Wesley. "Aerospace Structures Supportability". W General Aviation Aircraft Meeting and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1989. http://dx.doi.org/10.4271/891058.

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MITCHELL, ALAN, SAMUEL BRYAN i MARK HALL. "Design engineering technologies for aerospace vehicles". W 28th Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-715.

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HADJRIA, RAFIK, i OSCAR D’ALMEIDA. "Structural Health Monitoring for Aerospace Composite Structures". W Structural Health Monitoring 2019. Lancaster, PA: DEStech Publications, Inc., 2019. http://dx.doi.org/10.12783/shm2019/32280.

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Ravindra, K. "Aerospace Structures Course Revisited". W 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-979.

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DAYTO, SECTION,. "EVOLUTION OF AIRCRAFT/AEROSPACE STRUCTURES AND MATERIALS SYMPOSIUM". W 26th Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-834.

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SPAIN, CHARLES, THOMAS ZEILER, MICHAEL GIBBONS, DAVID SOISTMANN, PETER POZEFSKY, RAFAEL DEJESUS i CYPRIAN BRANNON. "AEROELASTIC CHARACTER OF A NATIONAL AEROSPACE PLANE DEMOSTRATOR CONCEPT". W 34th Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-1314.

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LEVINE, STANLEY. "Ceramics and ceramic matrix composites - Aerospace potential and status". W 33rd Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-2445.

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Hopkins, Mark, Douglas Dolvin, Donald Paul, Estelle Anselmo i Jeffrey Zweber. "Structures technology for future aerospace systems". W 39th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-1869.

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Ghorbani, K., T. Baum, K. Nicholson i J. Ahamed. "Advances aerospace multifunctional structures with integrated antenna structures". W 2015 Asia-Pacific Microwave Conference (APMC). IEEE, 2015. http://dx.doi.org/10.1109/apmc.2015.7413065.

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Hanuska, A., E. Scott i K. Daryabeigi. "Thermal characterization of aerospace structures". W 37th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-1053.

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Raporty organizacyjne na temat "Aerospace structures"

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

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

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

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

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

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

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

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Soovere, J., i M. L. Drake. Aerospace Structures Technology Damping Design Guide. Volume 3. Damping Material Data. Fort Belvoir, VA: Defense Technical Information Center, grudzień 1985. http://dx.doi.org/10.21236/ada178315.

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Ounaies, Zoubeida, Ramanan Krishnamoorti i Richard Vaia. Active Nanocomposites: Energy Harvesting and Stress Generation Media for Future Multifunctional Aerospace Structures. Fort Belvoir, VA: Defense Technical Information Center, czerwiec 2010. http://dx.doi.org/10.21236/ada547363.

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Selvam, R. P., ZU-Qing QU, Qun Zheng i Uday K. Roy. Predicting the Nonlinear Response of Aerospace Structures Using Aeroelastic NS Solutions on Deforming Meshes. Fort Belvoir, VA: Defense Technical Information Center, listopad 2001. http://dx.doi.org/10.21236/ada399278.

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