Results 131 to 140 of about 1,563 (157)
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A-37B Fatigue Sensor Evaluation Program - Full Scale Test and Field Aircraft Instrumentation,
1977Abstract : Micro Measurements FM Fatigue Sensors were installed on A-37 aircraft at three CONUS bases to determine the longevity and suitability of this device for field installation. A similar installation on an A-37B full scale fatigue test provided base line data for relative severity comparisons of accumulated fatigue.
John Y. Kaufman, Robert W. Walker
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Solid State Phenomena, 2015
The paper presents an approach to develop a system for fatigue crack growth monitoring and early damage detection in the PZL – 130 ORLIK TC II turbo-prop military trainer aircraft structure. The system functioning is based on elastic waves propagation excited in the structure by piezoelectric PZT transducers.
Michal Dziendzikowski +4 more
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The paper presents an approach to develop a system for fatigue crack growth monitoring and early damage detection in the PZL – 130 ORLIK TC II turbo-prop military trainer aircraft structure. The system functioning is based on elastic waves propagation excited in the structure by piezoelectric PZT transducers.
Michal Dziendzikowski +4 more
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AIP Conference Proceedings, 2009
An in situ ultrasonic angle beam method has been developed to detect and size fatigue cracks emanating from fastener holes. The method employs transducers mounted in a pitch‐catch configuration on each side of the hole, and the modulation of received signals with load is used to detect and size small fatigue cracks.
Thomas E. Michaels +4 more
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An in situ ultrasonic angle beam method has been developed to detect and size fatigue cracks emanating from fastener holes. The method employs transducers mounted in a pitch‐catch configuration on each side of the hole, and the modulation of received signals with load is used to detect and size small fatigue cracks.
Thomas E. Michaels +4 more
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Smart Materials and Structures, 2016
For aerospace application of structural health monitoring (SHM) technology, the problem of reliable damage monitoring under time-varying conditions must be addressed and the SHM technology has to be fully validated on real aircraft structures under realistic load conditions on ground before it can reach the status of flight test.
Lei Qiu +4 more
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For aerospace application of structural health monitoring (SHM) technology, the problem of reliable damage monitoring under time-varying conditions must be addressed and the SHM technology has to be fully validated on real aircraft structures under realistic load conditions on ground before it can reach the status of flight test.
Lei Qiu +4 more
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2019
An optical fiber-based Rayleigh backscattering distributed strain sensing system was adopted as the main structural integrity monitoring tool for airframe Full-Scale fatigue and ultimate tests. The strain signature along all major structural elements, as measured by the optical fibers, at each loading step was recorded and analyzed in real time.
U. Ben-Simon +5 more
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An optical fiber-based Rayleigh backscattering distributed strain sensing system was adopted as the main structural integrity monitoring tool for airframe Full-Scale fatigue and ultimate tests. The strain signature along all major structural elements, as measured by the optical fibers, at each loading step was recorded and analyzed in real time.
U. Ben-Simon +5 more
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Engineering Fracture Mechanics, 1975
Abstract In the case of circumferential cracks in a cylindrical fuselage, the comparison of some analysis and test results shows that the theoretical stress intensity factor is a suitable correlation parameter of fatigue crack propagation rates, both in aircraft fuselages and in plane panels.
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Abstract In the case of circumferential cracks in a cylindrical fuselage, the comparison of some analysis and test results shows that the theoretical stress intensity factor is a suitable correlation parameter of fatigue crack propagation rates, both in aircraft fuselages and in plane panels.
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2002
The reduction in cost of large data acquisition systems and the ease of taking data has encouraged analysts to demand more and more data from full-scale structural tests. However, this can lead to excessive data storage requirements. Furthermore, the amount of data can sometimes result in data handling difficulties, which prevent convenient and timely ...
RL Hewitt, A Nelson
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The reduction in cost of large data acquisition systems and the ease of taking data has encouraged analysts to demand more and more data from full-scale structural tests. However, this can lead to excessive data storage requirements. Furthermore, the amount of data can sometimes result in data handling difficulties, which prevent convenient and timely ...
RL Hewitt, A Nelson
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Experiences with On-Line Data Trend Monitoring on a Full-Scale Aircraft Fatigue Test
20092003 International Committee on Aeronautical Fatigue (ICAF) Conference From 05/05/2003 To 05/09/2003, Lucerne ...
Hewitt, Roy L., Hiscocks, Roger J.
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CALCULATION OF ACTUATOR LOADS FOR FULL-SCALE AIRCRAFT FATIGUE TESTING - ABSTRACT ONLY
200021st Symp of the International Committee on Aeronautical Fatigue, Toulouse ...
Hiscocks, R. J. +2 more
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Calculation of Actuator Loads and Whiffle Tree Geometries for Full Scale Aircraft Fatigue Tests
2009unlimited ...
Hewitt, R. L., Macmartin, D. G.
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