Relevant bibliographies by topics / Airframes Inspection

Academic literature on the topic 'Airframes Inspection'

Author: Grafiati
Published: 10 December 2022
Last updated: 29 January 2023

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Journal articles on the topic "Airframes Inspection"

1

Buckingham, Rob. "Snake arm robots." Industrial Robot: An International Journal 29, no. 3 (June 1, 2002): 242–45. http://dx.doi.org/10.1108/01439910210425531.

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Bringing a new robot to market is an exciting venture. When that robot is a new type of robot the venture takes on new proportions – it becomes an adventure. Dr Rob Buckingham, managing director of OCRobotics Ltd, describes the principles of a new snake arm robot that has applications in a number of industries including aerospace (engines and airframes), nuclear, space and surgery as well as a whole range of general inspection and maintenance tasks.
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Smotrova, S. A., V. I. Ivanov, A. V. Smotrov, A. N. Kuskova, and Yu V. Mantrova. "OPERATING RANGE RESPONSIVENESS DEFINITION OF LUMINESCENT SMART COATING BY RESULTS OF IMPACT DAMAGES PARAMETERS ULTRASONIC MEASUREMENTS." Kontrol'. Diagnostika, no. 267 (September 2020): 26–33. http://dx.doi.org/10.14489/td.2020.09.pp.026-033.

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One of the characteristic aircraft damages is impact by foreign object. In subsequent operation, the presence of impact damages to airframes made of polymer composite materials (PCM) leads to a violation of their structures and integrities. To avoid accidents it is necessary to identify and measure the parameters of such damages. The paper analyzes literature data, impact tests results and ultrasonic control of PCM samples. PCM samples represent plates. Dependences of PCM samples defect size on impact energy are revealed. It is shown that at energy of effect in a range 10…45 J damages with the linear sizes 25…70 mm are formed. The difference of the damages sizes on facing and turnaround surfaces of PCM samples is noted. The largest number of procedures in aviation is visual inspection with the naked eye or using any additional equipment. Its main disadvantage in relation to composite products is the fundamental inability to detect barely visible impact damage and internal defects that do not extend to the surface. The technology of impact damage detection using special impact -sensitive luminescent smart coatings with optical properties allows to improve the visual inspection procedure qualitatively. The result of the research is to define the permissible range of coating sensitivity. The luminescent smart coating operating range is determined: 10…20 J. Luminescent smart coating is developed for detection of barely visible impact damage on composite airframes.
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Smotrova, S. A., V. I. Ivanov, A. V. Smotrov, A. N. Kuskova, and Yu V. Mantrova. "OPERATING RANGE RESPONSIVENESS DEFINITION OF LUMINESCENT SMART COATING BY RESULTS OF IMPACT DAMAGES PARAMETERS ULTRASONIC MEASUREMENTS." Kontrol'. Diagnostika, no. 267 (September 2020): 26–33. http://dx.doi.org/10.14489/td.2020.09.pp.026-033.

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One of the characteristic aircraft damages is impact by foreign object. In subsequent operation, the presence of impact damages to airframes made of polymer composite materials (PCM) leads to a violation of their structures and integrities. To avoid accidents it is necessary to identify and measure the parameters of such damages. The paper analyzes literature data, impact tests results and ultrasonic control of PCM samples. PCM samples represent plates. Dependences of PCM samples defect size on impact energy are revealed. It is shown that at energy of effect in a range 10…45 J damages with the linear sizes 25…70 mm are formed. The difference of the damages sizes on facing and turnaround surfaces of PCM samples is noted. The largest number of procedures in aviation is visual inspection with the naked eye or using any additional equipment. Its main disadvantage in relation to composite products is the fundamental inability to detect barely visible impact damage and internal defects that do not extend to the surface. The technology of impact damage detection using special impact -sensitive luminescent smart coatings with optical properties allows to improve the visual inspection procedure qualitatively. The result of the research is to define the permissible range of coating sensitivity. The luminescent smart coating operating range is determined: 10…20 J. Luminescent smart coating is developed for detection of barely visible impact damage on composite airframes.
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4

Liu, Wen Lin, Wei Han, Zhi Tao Mu, Xiu Xia Wang, and Da Zhao Yu. "Research on Crack Growth Life and Sensibility Analysis of Influence Parameters in Crack Growth Life." Advanced Materials Research 317-319 (August 2011): 207–10. http://dx.doi.org/10.4028/www.scientific.net/amr.317-319.207.

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It requires a damage tolerance assessment for all airframes and engines to set the inspection windows for safe operation. A certain rotorcraft main rotor yoke were analyzed with NASGRO model. The sensibility analysis of influence parameters in crack growth life has been done. In order to calculate the sensibility index of influence factors to crack growth life, the factors were divided into input parameters and crack growth model parameters. The results show that the input parameters have the following precedence ordering: fatigue crack growth threshold, fracture spectrum, initial crack, fracture toughness, the sensibility values are 11.25, 8.5417, 0.8333, 0.1125, respectively. The NASGRO model parameters have the following precedence ordering: n, p, C, q. the sensibility values are 6.0417, -3.9583, 1.25, 0.1812, respectively.
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Suzuki, Satoshi, and Kenzo Nonami. "Special Issue on Novel Technology of Autonomous Drone." Journal of Robotics and Mechatronics 33, no. 2 (April 20, 2021): 195. http://dx.doi.org/10.20965/jrm.2021.p0195.

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In the past three years, there has been rapid progress in the use of drones in society. Drones, which were previously used only experimentally in various industrial fields, are now being used in earnest in everyday operations. Drones are becoming indispensable tools in several industrial fields, such as surveying, inspection, and agriculture. At the same time, there has also been dramatic progress in autonomous drone technology. With the advancement of image processing, simultaneous localization and mapping (SLAM), and artificial intelligence technologies, many intelligent drones that apply these technologies are being researched. At the same time, our knowledge of multi-rotor helicopters, the main type of drones, has continued to deepen. As the strengths and weaknesses of multi-rotor helicopters have gradually become clearer, drones with alternate structures, such as flapping-wing drones, have come to attract renewed attention. In addition, the range of applications for drones, including passenger drones, has expanded greatly, and research on unprecedented drone operations, as well as research on systems and controls to ensure operational safety, is actively being conducted. This special issue contains the latest review, research papers, and development reports on autonomous drones classified as follows from the abovementioned perspectives. · Research on drone airframes and structures · Research on drone navigation and recognition with a focus on image processing · Research on advanced drone controls · Research and development of drone applications We hope that the readers will actively promote the use of drones in their own research and work, based on the information obtained from this special issue.
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6

Wahab, M. Shujauddin, and Yuri M. Paramonov. "THE INFLUENCE OF CORROSION ON RELIABILITY AND INSPECTION PROGRAM FOR FATIGUE‐PRONE AIRFRAME STRUCTURES." Aviation 8, no. 3 (September 30, 2004): 10–17. http://dx.doi.org/10.3846/16487788.2004.9635876.

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This paper is devoted to a discussion and solution of the following problems: Determination of mean value and variance of estimates of parameters of fatigue crack growth model for both the corroded and non‐corroded types of specimens; Inspection modeling with the use of the Monte Carlo method for calculation of probability of fatigue failure as a function of inspection number; Determination of the number of inspections required for the limitation of fatigue failure probability; Comparison of required reliability for corroded and non‐corroded cases. Special programs have been developed for necessary calculations. It was confirmed that the influence of corrosion has a great impact on the required number of inspections.
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7

Jones, M. R. "Civil Airframe Structural Integrity—Some Probabilistic Aspects of Risk Assessment." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 210, no. 1 (January 1996): 19–25. http://dx.doi.org/10.1243/pime_proc_1996_210_341_02.

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Fatigue is the mechanism of progressive damage which may ultimately limit the economic life of an airframe. However, there is an intrinsic variability in the life of nominally identical structures subjected to alternating loads. Currently, the uncertainty in the estimated fatigue lives is accounted for in design by applying ‘scatter factors’ to the results of full-scale fatigue tests or to deterministically calculated lives. An alternative approach is to perform a reliability analysis to ensure that the weaker members of an aircraft fleet will meet the design aims with a pre-defined level of reliability. This paper aims to develop and apply analytical models required to: determine the safe-life or inspection threshold for a given fleet size with a prescribed reliability and review and revise the inspection programme based on the results of in-service inspections.
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8

Drury, Colin G., Floyd W. Spencer, and Donald L. Schurman. "Measuring Human Detection Performance in Aircraft Visual Inspection." Proceedings of the Human Factors and Ergonomics Society Annual Meeting 41, no. 1 (October 1997): 304–8. http://dx.doi.org/10.1177/107118139704100168.

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In airworthiness assurance, while there is a long tradition of measuring inspection reliability for machine-aided Non-Destructive Inspection (NDI), the more common visual inspection has received little attention. Yet inspection reliability measurements are needed if we are to set appropriate inspection intervals for airframe components. Visual inspection of aircraft is characterized as using multiple senses (despite its name) and having to inspect for multiple fault types, in contrast to NDI which is used for single specific fault types. The study here used 12 professional inspectors to perform nine visual inspection tasks on a long-service Boeing 737 aircraft. Each inspector worked over two days. Measures were taken of performance, strategy and individual differences. Only a fraction of the results are presented here, with a major finding that aircraft visual inspection has approximately the same reliability as industrial inspection. Individual differences were found, as well as correlations between certain aspects of performance and individual characteristics such as Field Independence and Peripheral Visual Acuity. However, there was little correlation between an individual inspector's performance on the different tasks, showing the difficulty of designing selection and placement procedures for such a wide-ranging job.
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9

Bowkett, T. "Dry Coupling Ultrasonic Inspection of Bonded Airframe Structures." Aircraft Engineering and Aerospace Technology 58, no. 3 (March 1986): 7–9. http://dx.doi.org/10.1108/eb036250.

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10

Gramopadhye, Anand K., Colin G. Drury, and Joseph Sharit. "Training for Decision Making in Aircraft Inspection." Proceedings of the Human Factors and Ergonomics Society Annual Meeting 37, no. 18 (October 1993): 1267–71. http://dx.doi.org/10.1177/154193129303701814.

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Research on civil aircraft inspection and maintenance has shown the potential for employing human factor interventions in improving performance. A series of training experiments was developed to understand the effects of different training interventions in the visual inspection domain. This paper reports on preliminary results obtained in applying a combined active and progressive part training scheme in improving the decision making performance for a visual inspection task. The task was a computer simulated airframe visual inspection task.
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Books on the topic "Airframes Inspection"

1

Staszewski, Wiesław Jerzy. Wavelets for mechanical and structural damage identification. Gdańsk: Wydawn. Instytutu Maszyn Przepływowych, 2000.

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2

Workshop on Intelligent NDE Sciences for Aging and Futuristic Aircraft (1997 University of Texas at El Paso). Workshop on Intelligent NDE Sciences for Aging and Futuristic Aircraft: Proceedings, September 30 - October 2, 1997. [El Paso, Tex.?]: Texas Western Press, 1998.

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3

J, Staszewski W., Boller C, and Tomlinson Geoffrey R, eds. Health monitoring of aerospace structures: Smart sensor technologies and signal processing. West Sussex, England: Hoboken, NJ, 2004.

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4

Miller, James G. Application of linear array imaging techniques to the real-time inspection of airframe structures and substuctures: Annual progress report, March 15, 1995 - October 31, 1995. St. Louis, Mo: Washington University, Dept. of Physics, Laboratory for Ultrasonics, 1995.

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NASA/FAA/DOD Conference on Aging Aircraft (2nd 1998 Williamsburg, Va.). The second joint NASA/FAA/DoD conference on aging aircraft. Edited by Harris Charles E. 1950-, Langley Research Center, and United States. National Aeronautics and Space Administration. Washington, DC: NASA STI Program Office, 1999.

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6

Research and Technology Organization. Applied Vehicle Technology Panel. Workshop. Airframe inspection reliability under field/depot conditions =: Degre de fiabilite des visites d'inspection des cellules en depot et en conditions operationnelles : papers presented at the Workshop of the RTO Applied Vehicle Technology Panel (AVT), organised by the former AGARD Structures and Materials Panel, held in Brussels, Belgium, 13-14 May 1998. Neuilly-sur-Seine: Research and Technology Organization, 1998.

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7

Board, United States National Transportation Safety. Aircraft accident report: Zantop International Airlines, Inc., Lockheed L-188A Electra, Chalkhill, Pennsylvania, May 30, 1984. Washington, D.C: The Board, 1985.

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United States. National Transportation Safety Board. Aircraft accident report: Piper PA-23-150, N2185P and Pan American World Airways Boeing 727-235, N4743, Tampa, Florida, November 6, 1986. Washington, D.C: The Board, 1987.

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United States. National Transportation Safety Board. Aircraft accident report: United Airlines flight 663, Boeing 727-222, N7647U, Denver, Colorado, May 31, 1984. Washington, D.C: The Board, 1985.

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United States. National Transportation Safety Board. Aircraft accident report: In-flight icing encounter and loss of control, Simmons Airlines, d.b.a. American Eagle flight 4184, Avions de Transport Regional (ATR) model 72-212, N401AM, Roselawn, Indiana, October 31, 1994. Washington, D.C: National Transportation Safety Board, 1996.

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Book chapters on the topic "Airframes Inspection"

1

Wincheski, Buzz, Jim Fulton, Ron Todhunter, and John Simpson. "Development and Testing of Rotating Probe Method for Airframe Rivet Inspection." In Review of Progress in Quantitative Nondestructive Evaluation, 2133–40. Boston, MA: Springer US, 1996. http://dx.doi.org/10.1007/978-1-4613-0383-1_280.

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Conference papers on the topic "Airframes Inspection"

1

Guo, Wenjiang, Anthony J. P. Mannion, and Stephen O'Brien. "Novel methods for inspection of damage on airframes." In Optical Metrology and Inspection for Industrial Applications V, edited by Sen Han, Toru Yoshizawa, and Song Zhang. SPIE, 2018. http://dx.doi.org/10.1117/12.2500379.

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Hagemaier, Donald, Bill Jappe, and Nancy Wood. "Improved NDI Techniques for Aircraft Inspection." In SAE Airframe/Engine Maintenance & Repair Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1998. http://dx.doi.org/10.4271/983105.

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Adair, Terri L., Mike G. Kindrew, Herbert I. Winter, Brian MacCracken, and David H. Wehener. "Automated Fluorescent Penetrant Inspection (FPI) System Is Triple A." In SAE Airframe/Engine Maintenance & Repair Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1998. http://dx.doi.org/10.4271/983124.

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Adair, Terri L., Jim L. Owens, Glen Grady, Herbert I. Winter, and Richard C. Grant. "Blending Borescope Inspection (BBI) Maintenence Service Equates to Cost Savings." In SAE Airframe/Engine Maintenance & Repair Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1998. http://dx.doi.org/10.4271/983108.

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Roach, Dennis, Larry Dorrell, Jeff Kollgaard, and Tom Dreher. "Improving Aircraft Composite Inspections Using Optimized Reference Standards." In SAE Airframe/Engine Maintenance & Repair Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1998. http://dx.doi.org/10.4271/983120.

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Willie, David J. "The Role of D Sight in Military Aircraft Inspection." In SAE Airframe/Engine Maintenance and Repair Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1997. http://dx.doi.org/10.4271/972623.

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Drury, Colin G., and Floyd W. Spencer. "Human Factors and the Reliability of Airframe Visual Inspection." In SAE Airframe/Engine Maintenance and Repair Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1997. http://dx.doi.org/10.4271/972592.

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8

Harris, Charles E., James H. Starnes, and Joseph S. Heyman. "Advanced Analysis Methods and Nondestructive Inspection Technology Under Development in the NASA Airframe Structural Integrity Program." In Airframe Finishing, Maintenance & Repair Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1994. http://dx.doi.org/10.4271/941247.

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Wincheski, Buzz. "Development of Giant Magnetoresistive inspection system for detection of deep fatigue cracks under airframe fasteners." In QUANTITATIVE NONDESTRUCTIVE EVALUATION. AIP, 2002. http://dx.doi.org/10.1063/1.1472906.

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Arelt, Rainer, Jan-Christoph Arent, Stefan Goerlich, Benjamin Hailer, and Mathias Dambaur. "The Application of Sandwich Technology to the Airframe Structure of Helicopters." In Vertical Flight Society 78th Annual Forum & Technology Display. The Vertical Flight Society, 2022. http://dx.doi.org/10.4050/f-0078-2022-17615.

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The H160-B is the latest helicopter design from AIRBUS HELICOPTERS with the extensive use of sandwich technology in the airframe. A sandwich with face sheets from CFRP and honeycomb cores is a robust outer skin of a helicopter. Furthermore it shows a very good tolerance to impact damages and a very good reparability. At Airbus Helicopters great experience is available which is required to understand and to control all manufacturing parameters, that are driving the quality of such parts. Powerful inspection technologies are in place to maintain the high level of manufacturing quality. In this paper an overview of the parts on this Helicopter made with sandwich technology will be given. These are cowlings and structural parts as well as principal structural elements (PSE) on main load paths. The respective certification requirements and related means of compliance demonstrations will be explained in detail. Special attention is paid to the applied methods for the damage tolerance demonstration of sandwich. The design and strength analysis was done with a combination of FEM analysis and analytical method, using basic allowable derived and validated by tests.
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