Results 161 to 170 of about 40,632 (210)
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Real-time nondestructive evaluation for full-scale aircraft fatigue test
SPIE Proceedings, 2008Damage identification and fatigue crack inspection during the test is a key foundation for full-scale aircraft fatigue test. It is very important to determine the fatigue life and maintenance period of the aircraft structure. The paper presents a brief introduction about a practical engineering method on real-time non-destructive evaluation (NDE) of ...
Quanliang Liu +3 more
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Fatigue Testing of Full-Scale All-Composite Aircraft Wings
SAE Technical Paper Series, 1987<div class="htmlview paragraph">A full scale fatigue test program has been established which will test a sailplane wing set to destruction. A flight loads data acquisition program using the instrumented high performance sailplane owned by the Royal Melbourne Institute of Technology has been conducted to determine the loading cases and spectrum ...
N. Mileshkin +3 more
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A Structural Health Monitoring System for the Full Scale Aircraft Fatigue Test
Applied Mechanics and Materials, 2013A structural health monitoring system especially for the full scale aircraft fatigue test is being developed to monitor, interpret, and make decisions based on the information from sensors during experiment. The functions of the system are achieved by different subsystems including data acquisition subsystem, control and manage subsystem, data ...
Yi Shan Zhang, Zhi Wang, Jia Kun Cai
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Computer Applications in Full-Scale Aircraft Fatigue Tests
1994The development of computerized load processing techniques for application to a full-scale fatigue test of the aft fuselage and empennage of a Canadian Forces CT-114 (Tutor) aircraft is described. The procedures used to select significant end points from the flight loads and to eliminate nondamaging maneuvers are presented together with the development
RL Hewitt, RS Rutledge
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An Inexpensive, Full-Scale Aircraft Fatigue Test System
SAE Technical Paper Series, 1973<div class="htmlview paragraph">The investigation of an inexpensive, full-scale, two-channel fatigue test apparatus for light airplanes is described. The rationale and assumptions made that aided in the development are detailed, and the total system and operating costs are presented.
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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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Development of Load Spectrum for Full Scale Fatigue Test of a Trainer Aircraft
2011PZL-130 “Orlik” is a turbo-propeller engine trainer airplane, entirely designed and build in Poland. This plane is used in Polish Air Force mainly for primary training of polish military pilots.
Andrzej Leski +2 more
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Combined Static and Fatigue Tests of the Full-Scale Structure of a Transport Aircraft
2019The article discusses a non-traditional approach in strength tests of the full-scale structure of a transport aircraft, which consists of combining static and fatigue tests on one object. The test object included a full span wing with installed pylons, the middle part of the fuselage and the main landing gear.
K. S. Shcherban +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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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
openaire +1 more source