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

Leski, Andrzej; Reymer, Piotr; Kurdelski, Marcin

doi:10.1007/978-94-007-1664-3_46

Cited by 9 publications

(11 citation statements)

References 3 publications

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“…The proposed concept is based on AFIT's previous experience [1][2][3] as well as the experience of the test staff.…”

Section: Test Stages Definitionmentioning

confidence: 99%

“…Based on the previous experience [1][2][3], the Air Force Institute of Technology (AFIT) proposed the Full Scale Fatigue Test (FSFT) concept of the Mi-24 helicopter structure as well as the implementation of the onboard loads and vibration monitoring system (SMST) in order to extend the service life and Structural Health Monitoring at the same time.…”

Section: Introductionmentioning

confidence: 99%

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Mi-24 Helicopter Full Scale Fatigue Test Concept

Reymer

Zieliński

Piątkowski

et al. 2019

Fatigue of Aircraft Structures

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This paper presents a general concept of the Full Scale Fatigue Test of the Mi-24 helicopter including the test layout and load distribution, as well as describes the milestones to be achieved. Additionally, some initial work conducted in order to determine both the mass and load distribution in the structure is described. The main goal of the test is to verify the low cycle fatigue life of the helicopter structure (fuselage, tail boom, wings and landing gear). The test will be divided into two main stages at which flight and landing loads will be applied. The authors demonstrate the general test concept, the helicopter’s structure fixture and the arrangement of the hydraulic actuators at both stages in order to achieve representative loads during the test. The proposed concept is based on AFIT’s previous experience in full scale structural testing, available literature and the experience of the test staff.

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“…The proposed concept is based on AFIT's previous experience [1][2][3] as well as the experience of the test staff.…”

Section: Test Stages Definitionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Mi-24 Helicopter Full Scale Fatigue Test Concept

Reymer

Zieliński

Piątkowski

et al. 2019

Fatigue of Aircraft Structures

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“…5. Green colour indicates an adequate fit to the equation (11). Red curves indicate extrapolation with the use the exponential function:…”

Section: Reliability Analysis -Input Datamentioning

confidence: 99%

Reliability at the checkpoints of an aircraft supporting structure

Woch

Kurdelski

Matyjewski

2015

EiN

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Article citation info: (*) Tekst artykułu w polskiej wersji językowej dostępny w elektronicznym wydaniu kwartalnika na stronie www.ein.org.pl IntroductionThis contribution presents a reliability prediction as well as sustainability methods for selected areas of the airframe in terms of fatigue processes and the aging process. Supporting structure may be classified as an element with a high correlation between the airworthiness parameter values and adequate fatigue life of the aircraft [27].One of the most important issues associated with aircraft maintenance is analysing durability of their structure components [10,20]. The previous experience in operation confirms that exhaustion of aircraft service life cannot be unambiguously identified with its unserviceability for further, reliable flights. Not always does the service life exhaustion result in the loss of aircraft technical condition and in the reliability parameters exceedance. The inadequacies of the traditional (service life) approach to aircraft maintenance used were the reason for developing new methods for assessing the durability of the aircraft structure, which are presented in the new study [21,22].The presented mathematical model is implemented with the use of specialized software known as PRobability Of Fracture (PROF) [13] and is commonly used by United States Air Force [4,6]. National Research Council Canada [12,24] uses a similar mathematical approach for reliability analysis of aircraft structure in its ProDTA (PRObabilistic Damage Tolerance Anylisis) software.The presented method and the research results make it possible to extend aircraft service life. Discussed procedures are not performed for aircraft owned by Polish Air Force, particularly for PZL-130 TC II ORLIK aircrafts. The exceptions are the F-16, for which such analyses are performed by Lockheed Martin. The reliability prediction method of support structure pointsFailure rate function [5, 9] is defined as the limit, if it exists, of the ratio of the conditional probability that the instant of time, T, of a failure of an item falls within a given time interval t t + ∆ and the length of this interval, t ∆ , when t ∆ leads to zero, given that the item is in an up state at the beginning of the time interval, which can be described as:where T is a continuous positive random variable of device operation time.If T has a density f(t) and the distribution F(t) equation (1) will take the form [1÷3]:whereGiven the failure rate λ(t) the life distribution can be calculated by the equation:Woch M, KurdelsKi M, MATyjeWsKi M. reliability at the checkpoints of an aircraft supporting structure. eksploatacja i NiezawodnoscMaintenance and reliability 2015; 17 (3): 457-462, http://dx

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“…7. Green colour indicates an adequate fit to the equation (11). Red curves indicate extrapolation with the use of exponential function:…”

Section: Reliability Analysis -Input Datamentioning

confidence: 99%

“…During these flights one utilizes KAM 500 data recorder [11,17]. The next step of the calculation was to obtain a transfer function relat- The initial crack size distribution was adopted pursuant to the article [5] (fig.…”

Section: Reliability Analysis -Input Datamentioning

confidence: 99%

Reliability analysis of the PZL-130 Orlik TC-II aircraft structural component under real operating conditions

Woch¹

2017

EiN

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

Cited by 9 publications

References 3 publications

Mi-24 Helicopter Full Scale Fatigue Test Concept

Mi-24 Helicopter Full Scale Fatigue Test Concept

Reliability at the checkpoints of an aircraft supporting structure

Reliability analysis of the PZL-130 Orlik TC-II aircraft structural component under real operating conditions

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