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Wyświetlanie 1-15 z 22
Tytuł:
Automation of Aircraft Fatigue Life Estimation
Autorzy:
Gajek, Stanisław
Powiązania:
https://bibliotekanauki.pl/articles/24201179.pdf
Data publikacji:
2022
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
Aircraft Fatigue
Rainflow Cycle Counting
Load Spectra
UAV
Opis:
The fatigue is an important factor in aircraft operation. A correct estimation of structure fatigue life is crucial for user and payload safety. However, due to high amount of data gathered during a typical recording of load spectra for different types of flights, the overall results become prone to human error. The paper describes development of a software able to perform an automated, in-depth analysis of data recorded with onboard accelerometers. Using the Rainflow Cycle Counting method, it transforms received data points into a Markov matrix. The prepared array is then recalculated into a half-cycle matrix, which can be collapsed into scalar value of fatigue level using the Palmgren-Miner rule. The method was tested with loads recorded during a typical flight conducted according to the Polish NSTS-06 flight scenario and simulated camera mounting fixed to a multirotor.
Źródło:
Fatigue of Aircraft Structures; 2022, 14; 83--103
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Review of Aeronautical Fatigue Investigations in Poland (2013-2014)
Autorzy:
Niepokólczycki, A.
Leski, A.
Dragan, K.
Powiązania:
https://bibliotekanauki.pl/articles/97803.pdf
Data publikacji:
2016
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
fatigue of aircraft structures
Opis:
This review was presented on the 34 Conference of the International Committee on Aeronautical Fatigue and Structural Integrity, Helsinki, Finland, June 1-2, 2015. It contains description of main works and investigations in fatigue of aircraft structures performed in Poland during the years 2013 and 2014.
Źródło:
Fatigue of Aircraft Structures; 2016, 8; 5-48
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Preparation of Samples used in Fatigue Testing of Aircraft Materials
Autorzy:
Manaj, W.
Wronicz, W.
Michałowski, A.
Powiązania:
https://bibliotekanauki.pl/articles/98020.pdf
Data publikacji:
2015
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
mechanical processing
stress measurement
X-ray diffraction
Opis:
The application of a new type of alloy requires the evaluation of its properties, which is typically achieved with destructive methods. For this purpose, among others, static and fatigue mechanical tests are performed. Tests are performed on standardized samples in a way which reflects the level of stress occurring in real elements. These tests should limit random errors associated with sample preparation. For this reason the proper preparation of samples is crucial, not only in terms of their geometric dimensions but also in terms of the residual stress level. A sample preparation process was developed, involving checking samples’ surface for cracks, scratches, roughness, and the state of stress. The measurements are performed with nondestructive methods so as not to affect the proceeding research. In this study, the residual stress and features of a mechanically prepared surface were characterized. The specimens were subjected to various surface finishes mainly, lathe turning and grinding surface conditions. The effects of residual surface stress (measured by XRD) were studied after machining and polishing.
Źródło:
Fatigue of Aircraft Structures; 2015, 7; 66-68
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Sensitivity Analysis of the Nasgro Equation Based on the PZL-130 TC-II Orlik Trainer Aircraft Full Scale Fatigue Test
Autorzy:
Reymer, Piotr
Leski, Andrzej
Kurdelski, Marcin
Powiązania:
https://bibliotekanauki.pl/articles/24201173.pdf
Data publikacji:
2022
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
sensitivity analysis
crack propagation
full scale fatigue test
Opis:
The study investigates the sensitivity of numerical crack propagation estimations based on the Nasgro equation. The equation is widely used for crack propagation calculations since it considers the whole range of crack propagation speed from threshold to critical values of stress intensity factor range (∆K). The presented investigation is based on the actual results of the full scale fatigue test (FSFT) of the PZL-130 ‘Orlik’ TC-II aircraft. We provide a brief description of the test and the general approach followed in crack propagation estimations originally carried out after the test. The obtained results are verified in terms of variation of the input data. Overall results are compared and discussed.
Źródło:
Fatigue of Aircraft Structures; 2022, 14; 8--17
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Application of Finite Element Method for Determining Loads for the New Method of Acoustic Fatigue Testing of Aircraft Structures
Autorzy:
Niepokólczycki, A.
Szot, A.
Powiązania:
https://bibliotekanauki.pl/articles/97923.pdf
Data publikacji:
2009
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Opis:
For aircraft structures the failures due to acoustic fatigue are very important, particularly for new supersonic or short take-off aircraft. The majority of acoustic fatigue life test methods are based on the reproduction of noise acting on the structure – in reverberation chambers or progressive wave tubes. The method described in this paper is based on the reproduction of dynamic response of the structure subjected to random acoustic loading.
Źródło:
Fatigue of Aircraft Structures; 2009, 1; 140-149
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Some Comments on Fatigue Life Tests of Aircraft Cable Control Systems
Autorzy:
Brzęczek, Józef
Powiązania:
https://bibliotekanauki.pl/articles/2105148.pdf
Data publikacji:
2020
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
aircraft’s cable control systems
cable service life
cable fatigue tests
Opis:
Cable control systems are widely used in aircraft and gliders.This paper deals with the problem of collecting real loads acting cable control systems and cable tests preparation (load spectrum) and performance. The author proposes a method for defining real loads acting on control systems, preparing and carrying out fatigue tests of cables revealing symptoms of fretting. The fatigue tests results can be used to predict service life, to plan and prepare periodic and details inspections. This method could be used to increase service life of aircraft control cables and could help to replace the commonly used Time-Based Maintenance (TBM) strategy with the Damage Tolerance (DT).
Źródło:
Fatigue of Aircraft Structures; 2020, 12; 102--112
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Full Scale Fatigue Test of New Undercarriage for Commuter Aircraft
Autorzy:
Brzęczek, J.
Gruszecki, H.
Pieróg, L.
Pietruszka, J.
Powiązania:
https://bibliotekanauki.pl/articles/97943.pdf
Data publikacji:
2012
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
fatigue testing
commuter aircraft
undercarriage
Opis:
Fatigue testing of the new main landing gear for the PZL M28 aircraft was conducted in Polskie Zakłady Lotnicze Sp. z o.o. in Mielec using MTS Aero 90-LT system. The test was conducted in a flight-by-flight manner with loads resulting from landing, taxiing, maneuvering and braking. The undercarriage structure is made of high tensile strength low alloy steel. FEM analyses were performed before the tests in order to find critical points and to obtain information about loads which may be neglected. During the test fatigue damage was observed, which led to splitting the test into two separate tests performed in independent rigs: the test of the undercarriage leg and the test of the shock absorber.
Źródło:
Fatigue of Aircraft Structures; 2012, 4; 70-75
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Numerical Simulation of Fatigue Fracture of the Turbine Disc
Autorzy:
Witek, L.
Powiązania:
https://bibliotekanauki.pl/articles/97889.pdf
Data publikacji:
2012
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
aircraft engine
crack propagation analysis
finite element method
fatigue fracture
Opis:
This paper presents the results of the crack propagation analysis of an aircraft engine turbine disc. In the first part of the work the finite element method was used for calculation of the stress state and the stress intensity factor (SIF, KI, K-factor) in the turbine disc with an embedded quarter-elliptical corner crack, subjected to low-cycle thermo-mechanical fatigue. To refine the K-factor calculation, specially degenerated finite elements were used. These elements provide stress singularity suitable for the linear-elastic material of the disc. The performed calculations yielded the stress intensity factor KI for different crack sizes. Subsequently, ΔK parameter was determined as a difference of the KI values calculated for the turbine’s speeds equal to 6373 and 14200 RPM. Based on the Paris-Erdogan equation and the obtained ΔK values, the fatigue crack growth plot for the turbine disc subjected to complex thermo-mechanical loads was determined.
Źródło:
Fatigue of Aircraft Structures; 2012, 4; 114-122
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
The Fatigue Life Assessment of PZL-130 Orlik Structures Based on Historical Usage Data
Autorzy:
Leski, A.
Klimaszewski, S.
Kurdelski, M.
Powiązania:
https://bibliotekanauki.pl/articles/97857.pdf
Data publikacji:
2009
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
aircraft structure
fatigue
usage profile
Opis:
Material fatigue is the basic factor limiting aircraft's durability. It comes from the fact that changing loads affect aircraft structure as well as from the fact that aircraft’s mass restrictions do not allow for diminishing stress to the level when material fatigue does not occur. Estimating fatigue durability of a particular structure as well as its actual fatigue damage degree is possible when the history of loads affecting the structure is known. Accuracy of loads monitoring influences the accuracy of indicated fatigue wear. In case of older structures, which have been maintained according to safe life principle, the number of hours have been commonly used as a fatigue wear indicator. After aircraft structure reaches flying time estimated by the produces, it is considered as fatigue wear and it is no longer in service. In case of a lack of results of loads spectrum measurements, results of tests conducted for other aircraft (of similar structure and assignment) can be used. For this purpose, average loads spectrum has been elaborated for particular aircraft groups, for example, HELIX, FELIX, FALSTAFF, ENSTAFF, TWIST(10). In the case of small aircraft, the data from FAA (2) report have been often used. This article describes the way of fatigue wear estimation for PZL-130 Orlik aircraft on the basis of historical data from flight recorders.
Źródło:
Fatigue of Aircraft Structures; 2009, 1; 131-139
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Strength Testing and Analysis of Fatigue Crack Growth in Selected Aircraft Materials
Autorzy:
Kłysz, S.
Lisiecki, J.
Powiązania:
https://bibliotekanauki.pl/articles/97903.pdf
Data publikacji:
2009
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Opis:
The study has been intended to determine the most essential mechanical and fatigue properties as well as impact strength of the 30HGSNA steel, to gain own data on the above-mentioned characteristics of materials to be used further on in numerical analyses of life estimates of aeronautical structural components. The scope of the study comprised the following assignments:
- determination of the most fundamental mechanical properties and impact strength of materials,
- low-cycle fatigue testing and evaluation of the Manson-Coffin curves,
- high-cycle fatigue testing and evaluation of the Wöhler curves,
- investigation into fatigue crack growth rates at constant and variable load-cycle amplitudes (determination of curves da/dN = f(ΔK, R), coefficients in Paris and NASGRO equations, coefficients in the Wheeler models of delay, the value of Kth(R)),
- crack toughness testing under the plane-state-of-strain conditions at room temperature (determination of the KIc(R)). The strength/fatigue testing was carried out in the Laboratory for Materials Strength Testing of the AFIT’s Division for Aeronautical Systems Reliability and Safety, the lab being accredited by the Polish Centre for Accreditation (Accreditation Certificate No.: AB 430).
Źródło:
Fatigue of Aircraft Structures; 2009, 1; 74-83
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Introduction of Fatigue Markers in Full Scale Fatigue Test of an Aircraft Structure
Autorzy:
Leski, A.
Kłysz, S.
Lisiecki, J.
Gmurczyk, G.
Reymer, P.
Bochenek, D.
Zasada, D.
Powiązania:
https://bibliotekanauki.pl/articles/97777.pdf
Data publikacji:
2012
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
full scale fatigue test
fatigue markers
load block rearrangement
Opis:
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.
Źródło:
Fatigue of Aircraft Structures; 2012, 4; 29-37
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
The Fatigue Life of Cables in Aircraft Flight Control Systems
Autorzy:
Kubryn, M.
Gruszecki, H.
Pieróg, L.
Chodura, J.
Pietruszka, J.
Brzęczek, J.
Powiązania:
https://bibliotekanauki.pl/articles/98016.pdf
Data publikacji:
2018
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
fatigue
cable flight control systems
cable endurance tests
Opis:
The cable flight control systems are commonly used for the control of small airplanes. In these systems, the cables are the only elements transmitting loads from the pilot to the control surfaces. During a flight the cables are moving through pulleys and are subjected to variable loads. A simple analysis of stress in the cable shows that the stress generated by the cyclical bending on the pulleys causes the fatigue of the wires. This phenomenon was noticed on a military aircraft of the M28 family during periodic maintenance inspection in 2007. The endurance tests of KSAN cables of the diameter equal to 3.5 mm and 1.8 mm were performed at the PZL MIELEC. The tests showed the limited fatigue life of the cables due to a progressive increase in the number of broken wires.
Źródło:
Fatigue of Aircraft Structures; 2018, 10; 53-62
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Assessment of Sensor Technologies for Aircraft SHM Systems
Autorzy:
Kurnyta, A.
Dragan, K.
Dziendzikowski, M.
Powiązania:
https://bibliotekanauki.pl/articles/97915.pdf
Data publikacji:
2013
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
SHM
sensor
fatigue crack
crack detection methods
usage monitoring
Opis:
SHM is a monitoring system which uses sensors, actuators and data transmission, acquisition and analysis, permanently integrated with the inspected object. The objective of SHM is to detect, localize, identify and predict development of fatigue fractures, increasing safety and reliability. This paper presents an assessment of sensor technologies used in aircraft SHM system. Due to the fact that most of these measurement methods are relatively new and still under development the present appraisal focuses on a number of parameters with reference to each method, including a sensor’s installation issues, reliability, power consumption, sensor infrastructure, sensitivity and cost and availability. The work is predominantly focused on the assessment of permanently bonded sensors, such as foil strain gages, Comparative Vacuum Monitoring (CVM), Piezo sensors (PZT), Eddy-Current Transducers (ECT). Finally, all these methods are briefly discussed.
Źródło:
Fatigue of Aircraft Structures; 2013, 5; 53-59
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Crack Growth Analysis of the Landing Gear Pull Rod of the Fighter Jet Aircraft
Autorzy:
Kurdelski, M.
Leski, A.
Powiązania:
https://bibliotekanauki.pl/articles/97773.pdf
Data publikacji:
2011
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
crack growth
fatigue
flight tests
landing gear
Opis:
This paper describes the problem of searching for the causes of damage in the form of rupture of a strength member of the main landing gear. There have been two incidents noted which both occurred during hangar storage. It should be pointed out that the two occurrences mentioned concern a particular aircraft currently in operation, and that these incidents occurred a few days after the last flight. This article presents part of the investigation process needed to determine the causes of cracks in the test item. The crack growth analysis of the pull rod was performed using the NASGRO software. In order to perform the calculations, the information was gathered during previously conducted material studies and flight tests.
Źródło:
Fatigue of Aircraft Structures; 2011, 3; 64-73
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Comparative Analysis of the Load Spectra Recorded During Photogrammetric Missions of Lightweight Uavs in Tailless and Conventional Configurations
Autorzy:
Rodzewicz, Mirosław
Głowacki, Dominik
Hajduk, Jaroslaw
Powiązania:
https://bibliotekanauki.pl/articles/24201177.pdf
Data publikacji:
2022
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
load spectra
fatigue life
unmanned aircraft
photogrammetry mission
Opis:
The purpose of this article is to present the results of the investigation regarding the differences of the load spectra of two unmanned fixed-wing aircraft performing photogrammetry missions: X-8 (flying wing) and PW-ZOOM (conventional configuration). The focus was on the analysis of a number of load cycles for various load increments within the range of the operational loads. The load spectra were determined using the acceleration signal recorded in the autopilot logs as an input. This signal was transferred to the chain of local extreme values scaled in the form of discrete load levels, and then the transfer arrays were derived with use of the rainflow counting algorithm. On this basis, the incremental load spectra were determined for each flight. These load spectra were subjected to statistical analyses to determine the load spectra representative of the flight sessions in a few ways between non-conservative (i.e., focused on average load histories) and conservative (i.e., focused on the worst load histories observed during the flight session). Finally, the fatigue life was calculated by having the structural element of the assumed fatigue properties subjected to the load spectra of both airplanes. A large (exceeding one order of magnitude) difference in the number of load cycles for larger load increments in the analyzed load spectra was shown. This difference is related to the different dynamic characteristics of the two aircraft, in particular the gust response. As a result, there is a several-fold difference in fatigue life.
Źródło:
Fatigue of Aircraft Structures; 2022, 14; 114--134
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Wyświetlanie 1-15 z 22

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