A Method for Reliability Assessment of Structural Components of Aircraft and Sea-Going Ships with Taking into Account a Given Failure Generation Model

Tomaszek, H.; Zieja, Mariusz; Ważny, M.

doi:10.1515/pomr-2016-0024

Cited by 4 publications

(3 citation statements)

References 12 publications

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“…In the literature on predicting the service life of commutator machines [11], the prediction method of the remaining service life of bearings based on a non-linear model of the Wiener process was described. Firstly, the service life of bearings is divided into two stages in terms of the operating state.…”

Section: Literature Reviewmentioning

confidence: 99%

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Reliability Assessment of Aircraft Commutators

Wawrzyński

Zieja

Michalski³

2021

Energies

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The article describes the method of predicting the reliability and durability of an aircraft commutator, which is a primary source of electric energy in helicopters. Tests were conducted for 10 starter-generators. From this research it follows that the technical condition of brushes and bearings has a significant impact on the reliability of starter-generators. The reliability of starter-generators was determined based on the method consisting of two stages that was adopted: the first stage involved determining the density function of changes in diagnostic parameter depending on the operating time, but the second stage included the assessment of the reliability of bearings of the starter-generator taking into account the real flight profile. The first stage of the adopted method consisted of defining the dynamic model of changing the length of the starter-generator’s brush, which became the probabilistic model. Subsequently, based on differential equations, Fokker–Planck partial differential equation was derived, which describes the process of increasing the brush wear in a probabilistic way. This method enables the prediction of the residual durability of the helicopter’s starter-generator due to the change in a diagnostic parameter which is the wear of brushes during starter-generator operation. The second stage of this method allows determining the durability of starter-generator’s bearings building upon the average helicopter’s flight profile. Owing to the difficulty in measuring the wear of bearings, the relation between the durability of bearings and the temperature of surroundings can be applied by replacing the flight altitude with temperature. The reliability of the helicopter’s starter-generator was determined based on the serial-type reliability structure.

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Section: Literature Reviewmentioning

confidence: 99%

“…It follows from Equation ( 8) that it is probable that in the instant t value of deviation is s − ∆s and in the time interval with length ∆t increased by value ∆s [30,36]. Thus, Equation ( 8) can be written in the following form [11,30,36]:…”

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Reliability Assessment of Aircraft Commutators

Wawrzyński

Zieja

Michalski³

2021

Energies

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“…Due to the specificity of obtaining and processing the input signal (waveform of the generator voltage) on the instantaneous frequency waveform, Figure 2 illustrates the methods of electronic signal processing, taking into account the systematic and apparatus errors committed during secondary sampling. Secondary sampling is carried out with indirect frequency measurement [11][12][13][14][15]23] by counting the number of n pulses of the time base clock f z during the period or halfperiod of the sinusoidal voltage signal (generator-converter). The generator-converter (in primary sampling, e.g., in electrical machinery) earlier discretized the spectrum of changes in mechanical modulation of the tested power unit and coded them as changes in time increments of passing through the zero level.…”

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Non-Invasive Monitoring of the Technical Condition of Power Units Using the FAM-C and FDM-A Electrical Methods

et al. 2021

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This article presents the selected results of analytical and structural work conducted at the Air Force Institute of Technology (pl. ITWL) in the field of building a measuring apparatus for non-invasive monitoring of the technical condition of aircraft power units. Presented innovative FAM-C and FDM-A methods allow for observation of frequency modulation parameters as well as identification and diagnostic classification of particular mechanical subassemblies supplying the on-board generator and thus enable non-invasive monitoring of technical condition of the aircraft power unit and the aircraft propulsion system. The main purpose of this article is to present the measurement apparatus errors that occur in the signal conditioning system in the FAM-C and FDM-A methods. In spite of the fact that the measuring instrument was built on the basis of digital technology and that it uses typical solutions of electronic frequency measurement, due to the specificity of the applied diagnostic method there occur specific measuring errors which are presented in this article.

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

Woch¹

2017

EiN

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A Method for Reliability Assessment of Structural Components of Aircraft and Sea-Going Ships with Taking into Account a Given Failure Generation Model

Abstract: This paper presents a metod for reliability assessment of structural components on the basis of diagnostic parameters

Cited by 4 publications

References 12 publications

Reliability Assessment of Aircraft Commutators

Reliability Assessment of Aircraft Commutators

Non-Invasive Monitoring of the Technical Condition of Power Units Using the FAM-C and FDM-A Electrical Methods

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

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