DSpace Collection:https://er.nau.edu.ua/handle/NAU/307042024-03-28T05:07:21Z2024-03-28T05:07:21ZComputer aided optical method for aircraft's components fatigue life estimationIgnatovich, S.R.Karuskevich, M.V.Maslak, T.P.https://er.nau.edu.ua/handle/NAU/322802017-12-26T12:26:37Z2008-09-01T00:00:00ZTitle: Computer aided optical method for aircraft's components fatigue life estimation
Authors: Ignatovich, S.R.; Karuskevich, M.V.; Maslak, T.P.
Abstract: The results of numerous tests show that quantitative estimation of accumulated fatigue damage may effectively be conducted by computer-aided optical analysis of the surface state. The method may be applied for alclad alluminium alloys which are used for modern aircraft skin manufacturing. The developed optical system and its software allow to determine the density of the areas with slip bands (damage parameter D), and a set of surface pattern fractal dimensions. These parameters allow to indicate more dangerous points of aircraft structures, predict fatigue crack under full scale test of aircraft structures as well as estimate residual service life.
Description: 17th European Conference on fracture2008-09-01T00:00:00ZA novel algorithm for damage analysis of fatigue sensor by surface deformation relief parametersKonovalenko, I.Maruschak, P.Menou, A.Karuskevich, M.Ignatovich, S.https://er.nau.edu.ua/handle/NAU/317672017-12-10T14:25:26Z2013-05-01T00:00:00ZTitle: A novel algorithm for damage analysis of fatigue sensor by surface deformation relief parameters
Authors: Konovalenko, I.; Maruschak, P.; Menou, A.; Karuskevich, M.; Ignatovich, S.
Abstract: Fatigue damage of metal structures may be estimated by the application of sensors with the surface relief pattern indicating the accumulated fatigue damage. The nature of the deformation relief has been investigated. Digital analysis of the surface patterns based algorithm for the integral evaluation method has proved the efficiency of integral parameters (the general area of damage, mean gradient along the coordinate axes, and the mean amplitude of the histogram function spectrum) application for additional quantitative description of such surface structures. The evolution of deformation relief parameters on the sensors surface is determined by the process of the sensor and construction fatigue damage accumulation.
Description: International symposium on operational research and applications ISORAP 20132013-05-01T00:00:00ZThe evaluation of the crack-like damage parameter of blades at the vibroacoustical diagnosis of the gas-turbine enginesIgnatovich, S.R.Bouraou, N.https://er.nau.edu.ua/handle/NAU/317662017-12-10T14:01:17Z2012-05-01T00:00:00ZTitle: The evaluation of the crack-like damage parameter of blades at the vibroacoustical diagnosis of the gas-turbine engines
Authors: Ignatovich, S.R.; Bouraou, N.
Abstract: This work is devoted to vibroacoustical condition monitoring of the gas-turbine engines (GTE) blades and diagnosis of the crack-like damages at the steady-state and non-steady-state modes of GTE. For detection of the mentioned damages we proposed the application and further development of the low-frequency vibroacoustical diagnostic methods which use vibrating and acoustical noise as diagnostic information. The following amplitude dimensionless characteristics are used as fault features: probability factor, peak factor and factor of background. The evaluation of the crack-like damage of the blades is carried out at the steady-state and non-steady-state modes by using the generalized likelihood method. The statistical quality of the received estimations is investigated.
Description: XXV Symposium Vibrations in Physical Systems2012-05-01T00:00:00ZFatigue cracks growth features in aluminum alloy D16ATIgnatovich, S.R.Krasnopolskii, V.S.https://er.nau.edu.ua/handle/NAU/307062017-10-14T13:24:18Z2016-01-01T00:00:00ZTitle: Fatigue cracks growth features in aluminum alloy D16AT
Authors: Ignatovich, S.R.; Krasnopolskii, V.S.
Abstract: This paper investigates the description of the fatigue cracks growth in sheet aluminum alloy D16AT by exponential dependence. The results show that the propagation of all investigated fatigue cracks can be satisfactorily described by this dependence with grate values of the determination coefficient.
Description: Конгресс Авіація в 21 ст., Безпека авіації та космічні технології2016-01-01T00:00:00Z