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.

scholarly journals Introduction of an Individual Aircraft Tracking Program for the Polish SU-22

2017 ◽  
Vol 2017 (9) ◽  
pp. 101-108
Author(s):  
Piotr Reymer ◽  
Marcin Kurdelski ◽  
Andrzej Leski ◽  
Andrzej Leśniczak ◽  
Michał Dziendzikowski
Keyword(s):  
Service Life ◽  
Air Force ◽  
Monitoring Program ◽  
Load Profile ◽  
Operational Load ◽  
Aircraft Tracking ◽  
Load Monitoring ◽  
Flight Parameters ◽  
The Individual ◽  
National Defence

AbstractThe Su-22 fighter-bomber is a military aircraft used in the Polish Air Force (PLAF) since the mid 1980’s. By decision of the Ministry of National Defence Republic of Poland, the assumed service life for this type of aircraft was prolonged up to 3200 flight hours based on the Full Scale Fatigue Test (FSFT) results. The FSFT was conducted using the real load profile defined during the Operational Load Monitoring Program (OLM) and the 3200 hour service life was also based on this load profile.In order to assure safe operation of all the 18 Su-22 aircraft, the Individual Aircraft Tracking program was introduced. The program was based on the results of the FSFT as well as the analysis of the flight parameters recorded by the THETYS onboard flight recorder.In this paper, the authors present the methodology, assumed fatigue hypothesis and preliminary results of the IAT program for the Polish Su-22.

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.

A Strategy for Design of Marine Pollution Monitoring Studies

1986 ◽  
Vol 18 (4-5) ◽  
pp. 15-26 ◽  
Author(s):  
D. A. Segar ◽  
E. Stamman
Keyword(s):  
Information Needs ◽  
Marine Pollution ◽  
Monitoring Program ◽  
Pollution Monitoring ◽  
Systematic Evaluation ◽  
Management Information ◽  
Different Types ◽  
Management Context ◽  
Definition Of ◽  
Scientific Testing

Most historical marine pollution monitoring has proven useless in a management context. A strategy for development of effective marine pollution monitoring programs is outlined. This strategy is based on the following steps: 1) systematic evaluation of the management information needs, 2) identification of the hypothetical impacts associated with those management concerns, and 3) investigation of the feasibility of monitoring those effects such that the existence, or absence, of a specified level of effects can be established in a statistically-valid manner. There are two fundamentally different types of monitoring program: site-specific and regional. These two types of program differ markedly in scope and approach when designed through application of this strategy. The strategy requires development of null hypotheses which address management concerns and which are amenable to scientific testing. In order for the program to be successful, the null hypotheses selected for inclusion in a marine pollution monitoring program must address levels of effect which are predefined to be environmentally significant. The definition of environmentally significant effect levels is a difficult process which must be primarily the responsibility of the managerial community.

Load Spectrum Compiling and Fatigue Life Estimation of the Automobile Wheel Hub

2020 ◽  
Vol 13 ◽  
Author(s):  
Xintian Liu ◽  
Yang Qu ◽  
Xiaobing Yang ◽  
Yongfeng Shen
Keyword(s):  
Fatigue Life ◽  
High Speed ◽  
Two Dimensional ◽  
Load Spectrum ◽  
One Dimensional ◽  
Life Estimation ◽  
Load Spectra ◽  
Fatigue Life Estimation ◽  
Program Load Spectrum ◽  
Program Load

Background:: In the process of high-speed driving, the wheel hub is constantly subjected to the impact load from the ground. Therefore, it is important to estimate the fatigue life of the hub in the design and production process. Objective:: This paper introduces a method to study the fatigue life of car hub based on the road load collected from test site. Methods:: Based on interval analysis, the distribution characteristics of load spectrum are analyzed. The fatigue life estimation of one - dimensional and two - dimensional load spectra is compared by compiling load spectra. Results:: According to the S-N curve cluster and the one-dimensional program load spectrum, the estimated range fatigue life of the hub is 397,100 km to 529,700 km. For unsymmetrical cyclic loading, each level means and amplitude of load were obtained through the Goodman fatigue empirical formula, and then according to S-N curve clusters in the upper and lower curves and two-dimensional program load spectrum, estimates the fatigue life of wheel hub of the interval is 329900 km to 435200 km, than one-dimensional load spectrum fatigue life was reduced by 16.9% - 17.8%. Conclusion:: This paper lays a foundation for the prediction of fatigue life and the bench test of fatigue durability of auto parts subjected to complex and variable random loads. At the same time, the research method can also be used to estimate the fatigue life of other bearing parts or high-speed moving parts and assemblies.

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