Готові списки джерел за темами / Airframes Corrosion

Добірка наукової літератури з теми "Airframes Corrosion"

Автор: Grafiati

Опубліковано: 10 грудня 2022

Оновлено: 28 січня 2023

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Статті в журналах з теми "Airframes Corrosion"

Petrovic, Zoran. "Corrosion in airframes." Vojnotehnicki glasnik 64, no. 1 (2016): 130–50. http://dx.doi.org/10.5937/vojtehg64-8573.

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Cole, Ivan S., P. Corrigan, W. D. Ganther, and Steve C. Galea. "Recent Progress in Intelligent Vehicle Health Monitoring." Key Engineering Materials 558 (June 2013): 357–63. http://dx.doi.org/10.4028/www.scientific.net/kem.558.357.

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Boeing, CSIRO and DSTO are collaborating on research into Intelligent Health Monitoring for Aerospace Vehicles (IHMAV). The system has the ability both to predict the probable development of corrosion and to elucidate the environmental factors that are promoting corrosion. The paper discusses the system capabilities, data output including the data derived from previous monitoring programs on B-707. In particular this data established the connection between local microclimate and corrosion events and highlights variations in microclimate and corrosion that can occur for different spaces in an airframe and different airframes.

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Cajani,, Maurizio. "AGEING AIRFRAMES AND CORROSION MAINTENANCE." Corrosion Reviews 25, no. 3-4 (August 2007): 263–74. http://dx.doi.org/10.1515/corrrev.2007.25.3-4.263.

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Venancio, P. G., R. A. Cottis, R. Narayanaswamy, and J. C. S. Fernandes. "Optical sensors for corrosion detection in airframes." Sensors and Actuators B: Chemical 182 (June 2013): 774–81. http://dx.doi.org/10.1016/j.snb.2013.03.059.

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Wanhill, Russell J. H., and Stefanie E. Stanzl-Tschegg. "Short/small fatigue crack growth, thresholds and environmental effects: a tale of two engineering paradigms." Corrosion Reviews 39, no. 2 (March 8, 2021): 165–75. http://dx.doi.org/10.1515/corrrev-2020-0096.

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Abstract This paper results from mutual discussions on the review ‘When do small fatigue cracks propagate and when are they arrested?’ in Corrosion Reviews, 2019; 37(5): 397–418. These discussions have arisen from the two engineering paradigms characterizing our fatigue research: (i) an aerospace research and technology remit for metallic airframes, and (ii) a materials science research programme supporting a methodology for steam turbine low pressure (LP) blade operations. In our opinion, this paper is of interest for other investigators of metal fatigue with respect to design requirements, life predictions and assessments. In more detail, the paper considers the fatigue design methodologies for airframes and steam turbine LP blades. This includes short/small fatigue cracks, fatigue crack growth thresholds, high-cycle fatigue (HCF) and very-high-cycle fatigue (VHCF), and the relevance of environmental effects (corrosion and corrosion fatigue).

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Janardhana, Madabhushi, Charles Davies, Adam Bowler, and David Zemel. "Influence of Advances in Technologies for the Management of Aircraft Structural Integrity within RAAF." Advanced Materials Research 41-42 (April 2008): 455–61. http://dx.doi.org/10.4028/www.scientific.net/amr.41-42.455.

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The basic concept of an Aircraft Stuctural Integrity Program is to ensure that airframes are adequately managed to ensure safe operation without catastrophic failure, to maximise fleet availibilty and to minimise cost of ownership. In managing these three aspects, a number of conventional and advanced technologies are being adopted and applied within the RAAF. Composites and bonding technology has been developed and transitioned onto various RAAF aircraft over many years in the form of Bonded Patch Repairs to airframe structures (wing and fuselage). Based upon conventional heat treatment behaviour of aluminium alloys, Retrogressive Re-Ageing technology is being transitioned to minimise stress corrosion cracking. From structural mechanics and FEA technologies, Geometric Shape Optimisation methods have been applied to minimise peak stress thresholds within aged airframe structures. To manage structural degredation (fatigue and corrosion) a number sensor-based monitors are being developed and applied on RAAF aircraft. Finally, using the reliability methodology, a proactive management program to assess the extent of corrosion degradation within a whole aircraft is being instituted. This methodology is being articulated through a new paradigm known as “Environmental Degradation Management System – Tool Box” (EDMS-TB). Within RAAF it can be demonstrated that candidate technologies which are adopted have direct and in-direct positive influences within ASIPs to address the key structural integrity parameters of Safety, Availability and Cost of Ownership.

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Nickerson, William C. "U.S. Naval Aviation: operational airframe experience with combined environmental and mechanical loading." Corrosion Reviews 33, no. 6 (November 1, 2015): 285–91. http://dx.doi.org/10.1515/corrrev-2015-0067.

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AbstractAirframe structure is the core capability for all aviation operations, whether fixed or rotary wing, manned or unmanned, or ship-based or shore-based. Airframe materials are the underlying enabling technology for all air vehicle structures. Airframe maintainability is the primary availability and readiness driver for U.S. Naval Aviation. Traditionally, airframe structures are designed for immediate mechanical performance and loads-only structural response, and the degradation of properties over the life cycle and sustainment during operations are often an afterthought. Galvanic management and corrosion-resistant materials selection have never been done systematically as part of the structural analysis and lifing process. Additionally, the lack of true failure mechanism understanding of load path effects, crack initiation and growth behaviors, and nonuniform material response has often resulted in underdesign/overdesign, limits on new material insertion, costly life extension programs, and unexpected early in-service failures. Advances in structural and materials science for airframes offer significant opportunity for improvements in availability, readiness, reduced sustainment requirements, fatigue life enhancement, reduced weight and improved range, and enhanced design tools and standard practices. These science and technology advances would be realized in large part through the engineering and operational communities by facilitating mission profile-specific life prediction and operational requirement-tailored functionality, increasing operational readiness, reducing life-cycle costs, reducing logistics footprint, and lowering the maintenance burden on uniformed personnel. Durability can therefore be incorporated into the design and construction phase, where the largest return can be realized.

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Kumar, Anish, Vinod Kumar, and Jatinder Kumar. "An Investigation into Machining Characteristics of Commercially Pure Titanium (Grade-2) Using CNC WEDM." Applied Mechanics and Materials 159 (March 2012): 56–68. http://dx.doi.org/10.4028/www.scientific.net/amm.159.56.

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Titanium is present in the earth’s crust at a level about 0.6% and is therefore the fourth most abundant structural metal after aluminum, iron, and magnesium. High strength, low density, and excellent corrosion resistance are the main properties that make titanium attractive for a variety of applications. The major application of the material is in the aerospace industry, both in airframes,engine components,steam turbine blades, superconductors, missiles etc. or corrosion resistance, for example marine services, chemical, petrochemical, electronics industry, biomedical instruments etc.In this study, wire electrical discharge machining (WEDM) is adopted in machining of commercially pure titanium (Grade-2). During experiments, parameters such as Pulse on time, Pulse off time, Peak current, Spark Gap set Voltage, Wire Feed and Wire Tension were changed to explore their effect on the cutting rate, gap current and surface roughness of the machined specimens. The ranges of process parameters for the experiments were decided on the basis of literature survey and the pilot experiments conducted using one factor at a time approach(OFTA). It is found that the intensity of the process energy does affect the cutting rate, gap current and surface roughness as well as, the wire speed, wire tension and dielectric fluid pressure not seeming to have much of an influence.

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Shunmugesh, K., and K. Panneerselvam. "Optimization of Drilling Process Parameters Via Taguchi, TOPSIS and RSA Techniques." Archives of Metallurgy and Materials 62, no. 3 (September 26, 2017): 1803–12. http://dx.doi.org/10.1515/amm-2017-0273.

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AbstractCarbon Fiber Reinforced Polymer (CFRP) is the most preferred composite material due to its high strength, high modulus, corrosion resistance and rigidity and which has wide applications in aerospace engineering, automobile sector, sports instrumentation, light trucks, airframes. This paper is an attempt to carry out drilling experiments as per Taguchi’s L27(313) orthogonal array on CFRP under dry condition with three different drill bit type (HSS, TiAlN and TiN). In this research work Response Surface Analysis (RSA) is used to correlate the effect of process parameters (cutting speed and feed rate) on thrust force, torque, vibration and surface roughness. This paper also focuses on determining the optimum combination of input process parameter and the drill bit type that produces quality holes in CFRP composite laminate using Multi-objective Taguchi technique and TOPSIS. The percentage of contribution, influence of process parameters and adequacy of the second order regression model is carried out by analysis of variance (ANOVA). The results of experimental investigation demonstrates that feed rate is the pre-dominate factor which affects the response variables.

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Zhou, X., Y. Younes, D. Wadeson, T. Hashimoto, and George E. Thompson. "Corrosion Control of Friction Stir Welded Aluminium Airframe Alloy." Advanced Materials Research 38 (March 2008): 298–305. http://dx.doi.org/10.4028/www.scientific.net/amr.38.298.

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In the present study, microstructure and its influence on corrosion behaviour of friction stir welded aluminium airframe alloy have been investigated. Further, the effect of laser surface treatment on the microstructure and the corrosion behaviour was also assessed. The welded AA2024 alloy showed the expected zones associated with friction stir welding. Corrosion testing showed that modified microstructure reduced its corrosion resistance to localized corrosion, with the regions immediately outside TMAZ being most susceptible to corrosion. Laser treatment resulted in a melted near-surface layer, up to 5 (m thick, where normal constituent particles are absent. Scrutiny of the melted near-surface layer revealed continuous segregation bands, approximately 10 nm thick, containing mainly copper. Corrosion testing showed that laser treatment increases the short term resistance to localized corrosion due to the removal constituent particles. However, prolonged testing revealed corrosion within the melted near-surface layer and delamination of the melted near-surface layer from underlying bulk alloy. The corrosion is associated with copper rich segregation bands that promote local microgalvanic action.

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Дисертації з теми "Airframes Corrosion"

Kersten, Stephanie M. "UH-1 corrosion monitoring." Thesis, Georgia Institute of Technology, 2010. http://hdl.handle.net/1853/37312.

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As the UH-1 aircraft continue to age, there is growing concern for their structural integrity. With corrosion damage becoming a bigger part of the sustainment picture with increasing maintenance burden and cost, it is becoming increasingly important for corrosion management to be updated with more advanced techniques. The current find-and-fix technique for handling corrosion has many shortfalls, spurring the recent interest in early detection through structural health monitoring. This condition based technique is becoming more prevalent and is recognized for the potential to greatly reduce maintenance cost. Through corrosion monitoring, structural and environmental conditions can be closely observed, preventing excessive maintenance action and saving cost. Searches for corrosion monitoring system designs revealed several commercial companies with prototype systems installed on commercial aircraft, however, details on system design and data analysis were scarce. This study attempted to bridge the gap in literature by providing insight into the development of a corrosion damage prediction model and the design of a corrosion monitoring system. This study attempted to use aircraft maintenance data to make prediction models for determining what corrosion damage an aircraft can expect, given varying operating conditions. Although a reliable prediction model could not be created, trends observed in the data were still valuable for identifying problematic areas of the aircraft. In order to create reliable models, more accurate corrosion data is needed. This can be accomplished through the implementation of a corrosion monitoring system. A custom corrosion monitoring system was designed for the UH-1 aircraft. Commercial off-the-shelf products were fit to the design and a benefits-to-cost analysis was performed for the monitoring system, evaluating the system based on criteria developed from user requirements. The system proved to meet and exceed expectation, making it an ideal choice for the UH-1 aircraft.

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Morgans, Christopher. "Defect tolerant lifing of airframe components and the influence of corrosion damage." Thesis, Swansea University, 2007. https://cronfa.swan.ac.uk/Record/cronfa42774.

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The present thesis describes a programme of research into corrosion pitting in the airframe aluminium alloy AA 7010-T7651 and its subsequent influence on fatigue performance. The alloy is employed extensively in airframe structures, most commonly as wing spars and skins of the BAE SYSTEMS Hawk Mkl27 lead-in fighter aircraft. The research programme followed from the major international project SICAS (Structural Integrity assessment of pitting Corrosion in Aircraft Structures), which was instigated as an attempt to minimise the costs associated with in-service corrosion damage. Existing corrosion management techniques are time consuming and expensive, typically involving grinding and mechanical blending of corrosion damaged areas. However, by adopting damage tolerant fatigue lifing procedures in partnership with corrosion detection, a reduction in the cost of corrosion management and safe extensions to aircraft operation lives may be achievable. Flat plate specimens were subjected to pitting damage via a laboratory based corrosion protocol. Secondly, a centre hole plate specimen was employed, in this case incorporating end grain corrosion within the root of central hole. Detailed characterisation of the pits demonstrated the critical role of microstructure on pit geometry. Both forms of pre-corroded specimen were subjected to a comprehensive matrix of constant amplitude load controlled fatigue testing under controlled humidity and room temperature. Multiple repeat tests were performed at specific stress levels to produce data sets corresponding to fatigue lives of approximately 1x104, 7x104 and 3x105 cycles. Post testing, LEFM based modelling was performed to describe test specimen performance. This proved successful for the relatively large scale corrosion pitting under consideration.

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Книги з теми "Airframes Corrosion"

Development, North Atlantic Treaty Organization Advisory Group for Aerospace Research and. Corrosion detection and management of advanced airframe materials. Neuilly sur Seine, France: AGARD, 1995.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Corrosion detection and management of advanced airframe materials: Papers presented at the 79th Meeting of the AGARD Structures and Materials Panel, held in Seville, Spain 5-6 October 1994. Neuilly sur Seine, France: AGARD, 1995.

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Aircraft corrosion control. Casper, WY: IAP, 1994.

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Corrosion detection and management of advanced airframe materials: Papers presented at the 79th Meeting of the AGARD Structures and MaterialsPanel, held in Seville, Spain, 5-6 October 1994. Neuilly sur Seine: Agard, 1995.

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Частини книг з теми "Airframes Corrosion"

Spicer, J. W. M., W. D. Kerns, L. C. Aamodt, and J. C. Murphy. "Characterization of Hidden Airframe Corrosion by Time-Resolved Infrared Radiometry (TRIR)." In Review of Progress in Quantitative Nondestructive Evaluation, 2027–34. Boston, MA: Springer US, 1993. http://dx.doi.org/10.1007/978-1-4615-2848-7_260.

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Тези доповідей конференцій з теми "Airframes Corrosion"

DelGrande, Nancy, and Philip F. Durbin. "Dual-band infrared imaging to detect corrosion damage within airframes and concrete structures." In SPIE's International Symposium on Optical Engineering and Photonics in Aerospace Sensing, edited by John R. Snell, Jr. SPIE, 1994. http://dx.doi.org/10.1117/12.171181.

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Restis, Jude, and Mike Dubberly. "Bolt Hole Corrosion and Fatigue Damage Repair in Hybrid Vertical Lift Structure." In Vertical Flight Society 78th Annual Forum & Technology Display. The Vertical Flight Society, 2022. http://dx.doi.org/10.4050/f-0078-2022-17598.

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Cold expansion has been successfully used in aerospace structures, including vertical lift airframes to repair and prevent fatigue damage for more than 50 years. PartWorks is innovating the cold expansion process, parts and tooling for use in repairing corroded fastener holes (U.S. Patent 11,255,371). PartWorks is participating in a two phase development and demonstration program, first for the US Navy (Office of Naval Research/ONR) starting in 2017, and more recently for the United States Air Force (Air Force Research Lab/AFRL) for repairs to bolt holes on aerospace structures with metal/carbon-fiber composite skins. These locations in aerospace structures for vertical lift or fixed wing have demonstrated greater levels of corrosion when compared to all-metal structural skin due to galvanic corrosion between metal and carbon fiber composites. Existing repair methods for these metal/carbon fiber composite skin bolt hole/fastener sites often involve extensive removal of corrosion, non-standard or oversized holes, and extensive modeling/validation to prove repair effectiveness. Existing repairs can also lead to premature structural component replacement. This project is evaluating a new repair method that uses cold expansion with thin wall bushings and/or a rivetless nut plate (RNP) to restore fatigue life to the metal bolt hole if damage is missed or potentially without having to remove all the damage/corrosion.

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Diepart, Claude P., E. Roger Thompson, and James Harrison. "Exfoliation Corrosion Located by Search Peening." In Airframe Finishing, Maintenance & Repair Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1995. http://dx.doi.org/10.4271/951147.

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Willie, David J., and Frank Karpala. "Proactive Aircraft Lap Joint Corrosion Maintenance Scheduling." In Airframe Finishing, Maintenance & Repair Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1996. http://dx.doi.org/10.4271/961247.

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Rich, Chris, and Paul Soley. "Hot End Cleaning - Corrosion Pitting of Turbine Discs." In Airframe Finishing, Maintenance & Repair Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1992. http://dx.doi.org/10.4271/920930.

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Willie, David J. "Applying D Sight Technology to Aging Aircraft Corrosion NDI." In Airframe Finishing, Maintenance & Repair Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1995. http://dx.doi.org/10.4271/951140.

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Rokhlin, S. I., B. Zoofan, J. Y. Kim, and W. Dai. "Nondestructive Characterization of Pitting Corrosion Damage and Fatigue Life." In SAE Airframe/Engine Maintenance & Repair Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1998. http://dx.doi.org/10.4271/983127.

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Mosser, Mark F. "New Processes for Corrosion Control of Active Metals in Severe Environments." In Airframe Finishing, Maintenance & Repair Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1991. http://dx.doi.org/10.4271/910922.

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Smith, Cheryl Ann. "Investigation of Four Wear-Resistant Topcoat Materials with Zinc Nickel as the Corrosion-Resistant Undercoat." In Airframe Finishing, Maintenance & Repair Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1993. http://dx.doi.org/10.4271/931051.

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Skluzak, Dell, and Yuji Tajima. "The Use of Improved Corrosion Resistant Aluminum Alloy 6013 on the Navy's P-7A Aircraft." In Airframe Finishing, Maintenance & Repair Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1990. http://dx.doi.org/10.4271/900959.

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