Development of Load Spectrum for Full Scale Fatigue Test of a Trainer Aircraft

2011 ◽  
pp. 573-584 ◽  
Author(s):  
Andrzej Leski ◽  
Piotr Reymer ◽  
Marcin Kurdelski
Keyword(s):  
Fatigue Test ◽  
Full Scale ◽  
Load Spectrum

On Development of Load Spectrum for Full Scale Fatigue Test of Trucks in Laboratory

1987 ◽  
Author(s):  
C. Arief ◽  
P. Santika ◽  
B. Prasetio
Keyword(s):  
Fatigue Test ◽  
Full Scale ◽  
Load Spectrum

Introduction of Developing Fatigue Load Spectrum for Full-Scale Fatigue Test of Composite Aircraft

2020 ◽  
Vol 21 (3) ◽  
pp. 681-692
Author(s):  
Young-Sik Joo ◽  
Won-Jun Lee ◽  
Bo-Hwi Seo ◽  
Seung-Gyu Lim
Keyword(s):  
Fatigue Test ◽  
Full Scale ◽  
Load Spectrum ◽  
Fatigue Load

scholarly journals Introduction of Fatigue Markers in Full Scale Fatigue Test of an Aircraft Structure

2012 ◽  
Vol 2012 (4) ◽  
pp. 29-37 ◽  
Author(s):  
Andrzej Leski ◽  
Sylwester Kłysz ◽  
Janusz Lisiecki ◽  
Gabriel Gmurczyk ◽  
Piotr Reymer ◽  
...  
Keyword(s):  
Fatigue Crack ◽  
Crack Propagation ◽  
Fatigue Test ◽  
Crack Propagation Rate ◽  
Propagation Rate ◽  
Full Scale ◽  
Life Assessment ◽  
Load Spectrum ◽  
Preliminary Load ◽  
Different Levels

Abstract Air Force Institute of Technology participates in the service life assessment programme SEWST. The aim of this programme, funded by the Polish Ministry of Defense, is to modify the operation system of PZL-130 "Orlik" TC-II turbo propelled trainer aircraft. The structural part of the programme is focused on the Full Scale Fatigue Test of the whole airframe to be conducted at the VZLU in the Czech Republic. The load spectrum for the test was developed by the AFIT based on the flight test results. The basic load block represents 200 simulated flight hours and consists of 194 flights showing different levels of severity. At the end of the Full Scale Fatigue Test a teardown inspection is planned during which it would be most beneficial to be able to determine crack propagation rate by means of a crack surface inspection. Markers are usually visible on most fatigue crack surfaces, however they occur randomly therefore it is almost impossible to conclude anything about the crack history. Since the preliminary load block consisted of separate flights (flight loads together with landing and taxing loads) showing significantly different levels of severity, the easiest way to modify the load block was to change the order of flights within the block. Hence a pilot programme was started at the AFIT which was focused on the determination of the influence of flight sequence on crack appearance. Several load blocks were determined using various techniques of rearranging the order of flights within the preliminary load spectrum. This approach ensured the preservation of the initial severity of the load block and simultaneously enabled a significant increase in the probability of the markers occurrence introducing neither artificial underloads nor overloads that would most probably affect the crack propagation rate. Fatigue crack surfaces were inspected using Scanning Electron Microscope. As a result of the investigations a series of images were obtained showing the specimen microstructure with visible markers arranged in the desired sequences. Based on the obtained pictures the most promising load block arrangements were chosen for the Full Scale Fatigue Test.

scholarly journals ZL-130TCII Fracture Markers Solution for Full-Scale Fatigue Test

2011 ◽  
Vol 2011 (3) ◽  
pp. 22-27
Author(s):  
Sylwester Kłysz ◽  
Janusz Lisiecki ◽  
Dariusz Zasada ◽  
Gabriel Gmurczyk ◽  
Andrzej Leski
Keyword(s):  
Fracture Surface ◽  
Fatigue Test ◽  
Aluminium Alloys ◽  
Full Scale ◽  
Load Spectrum ◽  
Full Scale Tests ◽  
Change Spectrum ◽  
Pilot Tests

ZL-130TCII Fracture Markers Solution for Full-Scale Fatigue TestIn the context of PZL-130TC-II full-scale fatigue test, several strategies of fatigue loadings that create fracture surface markings were considered. One block of spectrum is made of 200 flights. By reordering those flights, a block which should create a fracture marker, was developed. It was very important that reordering the load spectrum or adding overloads or underloads did not change spectrum severity. Pilot tests of aluminium alloys specimens were carried out to finalise appropriate marker intervals before commencing full-scale tests. The experiment was conducted with the MTS machine with 810.23 system. The results and conclusions are presented within this paper.

scholarly journals The Definition of the Load Spectrum for SU-22 Fighter-Bomber Full Scale Fatigue Test

2015 ◽  
Vol 2015 (7) ◽  
pp. 28-33
Author(s):  
Piotr Reymer ◽  
Marcin Kurdelski ◽  
Andrzej Leski ◽  
Krzysztof Jankowski
Keyword(s):  
Service Life ◽  
Fatigue Test ◽  
Air Force ◽  
Monitoring Program ◽  
Full Scale ◽  
Load Spectrum ◽  
Load Spectra ◽  
Load Monitoring ◽  
Wing Sweep ◽  
Definition Of

Abstract The Su-22 fighter-bomber is a military aircraft used in the Polish Air Force since the mid 1980’s. By the decision of the Polish Ministry of Defense the predicted service life for this type of aircraft will be extended to 3200 flight hours. Due to the fact that some aircraft were nearing the end of the service life guaranteed by the manufacturer, the actual service life, determined based on the flight profile in the Polish Air Force, had to be validated. Consequently, the Full Scale Fatigue Test (FSFT) had to be carried out in order to verify that the required service life was attainable. This article describes the process of preparation of the load spectra used in the Su-22 FSFT. Due to the fact that the Su-22 has a variable sweep wing the whole test was divided into three Stages (landing, flight and flap loads) carried out at different wing sweep angles (30°/45°/30°). The spectra were developed using the historical data gathered from Flight Data Recorders (FDR), strain signals acquired during the Operational Load Monitoring program (OLM) and aerodynamic calculations.

Health Monitoring of the Aircraft Structure during a Full Scale Fatigue Test with Use of an Active Piezoelectric Sensor Network

2015 ◽  
Vol 220-221 ◽  
pp. 328-332
Author(s):  
Michal Dziendzikowski ◽  
Krzysztof Dragan ◽  
Artur Kurnyta ◽  
Sylwester Klysz ◽  
Andrzej Leski
Keyword(s):  
Signal Processing ◽  
Damage Detection ◽  
Crack Growth ◽  
Fatigue Test ◽  
Piezoelectric Sensor ◽  
Full Scale ◽  
Growth Monitoring ◽  
Aircraft Structure ◽  
System Functioning ◽  
Signal Processing Methods

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. In the paper, a built block approach for the system design, signal processing as well as damage detection is presented. Description of damage detection capabilities are delivered in the paper and some issues concerning the proposed signal processing methods and their application to crack growth estimation models are discussed. Selected preliminary results obtained during the Full Scale Fatigue Test thus far are also presented.

The Swiss F/A-18 Full Scale Fatigue Test - Modern and Efficient Testing

2004 ◽  
Author(s):  
Michel Guillaume ◽  
Georges Mandanis ◽  
Ignaz Pfiffner ◽  
Lukas Schmid
Keyword(s):  
Fatigue Test ◽  
Full Scale

scholarly journals Full Scale Fatigue Test of New Undercarriage for Commuter Aircraft

2012 ◽  
Vol 2012 (4) ◽  
Author(s):  
Józef Brzęczek ◽  
Henryk Gruszecki ◽  
Leszek Pieróg ◽  
Janusz Pietruszka
Keyword(s):  
Fatigue Test ◽  
Full Scale

AE monitoring of airframe structure during full scale fatigue test

1992 ◽  
Vol 25 (6) ◽  
pp. 301
Author(s):  
D. Bozzetti ◽  
A. Sala ◽  
G. Borzacchiello ◽  
C. Sabatino
Keyword(s):  
Fatigue Test ◽  
Full Scale
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