TY  - PAT
AU  - Maksimović, Stevan
AU  - Maksimović, Mirko
AU  - Maksimović-Vasović, Ivana
AU  - Maksimović, Katarina
AU  - Jarić, Marko
PY  - 2021
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7204
AB  - Kompozitni segment lopatice glavnog rotora helikoptera HT40
PB  - Glasnik intelektualne svojine
T2  - Glasnik intelektualne svojine
T1  - Composite segment of main rotor blade of the helicopter HT40
VL  - 11
UR  - https://hdl.handle.net/21.15107/rcub_machinery_7204
ER  - 

@misc{
author = "Maksimović, Stevan and Maksimović, Mirko and Maksimović-Vasović, Ivana and Maksimović, Katarina and Jarić, Marko",
year = "2021",
abstract = "Kompozitni segment lopatice glavnog rotora helikoptera HT40",
publisher = "Glasnik intelektualne svojine",
journal = "Glasnik intelektualne svojine",
title = "Composite segment of main rotor blade of the helicopter HT40",
volume = "11",
url = "https://hdl.handle.net/21.15107/rcub_machinery_7204"
}

Maksimović, S., Maksimović, M., Maksimović-Vasović, I., Maksimović, K.,& Jarić, M.. (2021). Composite segment of main rotor blade of the helicopter HT40. in Glasnik intelektualne svojine
Glasnik intelektualne svojine., 11.
https://hdl.handle.net/21.15107/rcub_machinery_7204

Maksimović S, Maksimović M, Maksimović-Vasović I, Maksimović K, Jarić M. Composite segment of main rotor blade of the helicopter HT40. in Glasnik intelektualne svojine. 2021;11.
https://hdl.handle.net/21.15107/rcub_machinery_7204 .

Maksimović, Stevan, Maksimović, Mirko, Maksimović-Vasović, Ivana, Maksimović, Katarina, Jarić, Marko, "Composite segment of main rotor blade of the helicopter HT40" in Glasnik intelektualne svojine, 11 (2021),
https://hdl.handle.net/21.15107/rcub_machinery_7204 .

TY  - CHAP
AU  - Maksimović, Katarina
AU  - Posavljak, S.
AU  - Maksimović, Mirko S.
AU  - Vasovic Maksimović, Ivana
AU  - Balać, Martina
PY  - 2021
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3680
AB  - This work presents total fatigue life prediction methodology of aircraft structural components under general load spectrum. Here is presented an effective computation procedure, that combines the finite element method (FEM) and strain-life methods to predict fatigue crack initiation life and fatigue crack growth model based on the strain energy density (SED) method. To validate computation procedure in this paper has been experimental tested specimens with a central hole under load spectrum in form of blocks. Total fatigue life of these specimens, defined as sum of crack initiation and crack growth life, was experimentally determined. Crack initiation life was computed using the theory of low cycle fatigue. Computation of crack initiation life was realized using Palmgreen-Miner’s linear rule of damage accumulation, applied on Morrow’s curves of low cycle fatigue. Crack growth life was computed using strain energy density (SED) method. The same low cyclic material properties of quenched and tempered steel 13H11N2V2MF, used for crack initiation life computation, were used for crack growth life computation. Residual life estimation of cracked duraluminum aircraft wing skin/plate 2219-T851 under multiple overload/underload load spectrum was considered too. Presented computation results were compared with own and available experimentally obtained results.
PB  - Springer
T2  - Lecture Notes in Networks and Systems
T1  - Total fatigue life estimation of aircraft structural components under general load spectra
EP  - 412
SP  - 394
VL  - 153
DO  - 10.1007/978-3-030-58362-0_23
ER  - 

@inbook{
author = "Maksimović, Katarina and Posavljak, S. and Maksimović, Mirko S. and Vasovic Maksimović, Ivana and Balać, Martina",
year = "2021",
abstract = "This work presents total fatigue life prediction methodology of aircraft structural components under general load spectrum. Here is presented an effective computation procedure, that combines the finite element method (FEM) and strain-life methods to predict fatigue crack initiation life and fatigue crack growth model based on the strain energy density (SED) method. To validate computation procedure in this paper has been experimental tested specimens with a central hole under load spectrum in form of blocks. Total fatigue life of these specimens, defined as sum of crack initiation and crack growth life, was experimentally determined. Crack initiation life was computed using the theory of low cycle fatigue. Computation of crack initiation life was realized using Palmgreen-Miner’s linear rule of damage accumulation, applied on Morrow’s curves of low cycle fatigue. Crack growth life was computed using strain energy density (SED) method. The same low cyclic material properties of quenched and tempered steel 13H11N2V2MF, used for crack initiation life computation, were used for crack growth life computation. Residual life estimation of cracked duraluminum aircraft wing skin/plate 2219-T851 under multiple overload/underload load spectrum was considered too. Presented computation results were compared with own and available experimentally obtained results.",
publisher = "Springer",
journal = "Lecture Notes in Networks and Systems",
booktitle = "Total fatigue life estimation of aircraft structural components under general load spectra",
pages = "412-394",
volume = "153",
doi = "10.1007/978-3-030-58362-0_23"
}

Maksimović, K., Posavljak, S., Maksimović, M. S., Vasovic Maksimović, I.,& Balać, M.. (2021). Total fatigue life estimation of aircraft structural components under general load spectra. in Lecture Notes in Networks and Systems
Springer., 153, 394-412.
https://doi.org/10.1007/978-3-030-58362-0_23

Maksimović K, Posavljak S, Maksimović MS, Vasovic Maksimović I, Balać M. Total fatigue life estimation of aircraft structural components under general load spectra. in Lecture Notes in Networks and Systems. 2021;153:394-412.
doi:10.1007/978-3-030-58362-0_23 .

Maksimović, Katarina, Posavljak, S., Maksimović, Mirko S., Vasovic Maksimović, Ivana, Balać, Martina, "Total fatigue life estimation of aircraft structural components under general load spectra" in Lecture Notes in Networks and Systems, 153 (2021):394-412,
https://doi.org/10.1007/978-3-030-58362-0_23 . .

TY  - JOUR
AU  - Vasić, Zoran M.
AU  - Maksimović, Katarina
AU  - Maksimović, Mirko S.
AU  - Vasović, Ivana
AU  - Vidanović, Nenad
AU  - Simonović, Aleksandar
PY  - 2021
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3578
AB  - The thermo mechanical buckling and post-buckling behavior of layered composite shell type structure are considered with the finite element method under the combination of temperature load and applied mechanical loads. To account for through-thickness shear deformation effects, the thermal elastic, and higher-order shear deformation theory is used in this study. The refined higher order theories, that takes into account the effect of transverse normal deformation, is used to develop discrete finite element models for the thermal buckling analysis of composite laminates. Attention in this study is focused on analyzing the temperature effects on buckling and post-buckling behavior of thin shell structural components. Special attention in this paper is focused on studying of values of the hole in curved panel on thermal buckling behavior and consequently to expend and upgrade previously conducted investigation. Using finite element method, a broader observation of the critical temperature of loss of stability depending on the size of the hole was conducted. The presented numerical results based on higher-order shear deformation theory can be used as versatile and accurate method for buckling and post-buckling analyzes of thin-walled laminated plates under thermo mechanical loads.
PB  - Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd
T2  - Thermal Science
T1  - Buckling and post-buckling behavior of shell type structures under thermo mechanical loads
EP  - 4357
IS  - 6
SP  - 4347
VL  - 25
DO  - 10.2298/TSCI201129079V
ER  - 

@article{
author = "Vasić, Zoran M. and Maksimović, Katarina and Maksimović, Mirko S. and Vasović, Ivana and Vidanović, Nenad and Simonović, Aleksandar",
year = "2021",
abstract = "The thermo mechanical buckling and post-buckling behavior of layered composite shell type structure are considered with the finite element method under the combination of temperature load and applied mechanical loads. To account for through-thickness shear deformation effects, the thermal elastic, and higher-order shear deformation theory is used in this study. The refined higher order theories, that takes into account the effect of transverse normal deformation, is used to develop discrete finite element models for the thermal buckling analysis of composite laminates. Attention in this study is focused on analyzing the temperature effects on buckling and post-buckling behavior of thin shell structural components. Special attention in this paper is focused on studying of values of the hole in curved panel on thermal buckling behavior and consequently to expend and upgrade previously conducted investigation. Using finite element method, a broader observation of the critical temperature of loss of stability depending on the size of the hole was conducted. The presented numerical results based on higher-order shear deformation theory can be used as versatile and accurate method for buckling and post-buckling analyzes of thin-walled laminated plates under thermo mechanical loads.",
publisher = "Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd",
journal = "Thermal Science",
title = "Buckling and post-buckling behavior of shell type structures under thermo mechanical loads",
pages = "4357-4347",
number = "6",
volume = "25",
doi = "10.2298/TSCI201129079V"
}

Vasić, Z. M., Maksimović, K., Maksimović, M. S., Vasović, I., Vidanović, N.,& Simonović, A.. (2021). Buckling and post-buckling behavior of shell type structures under thermo mechanical loads. in Thermal Science
Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd., 25(6), 4347-4357.
https://doi.org/10.2298/TSCI201129079V

Vasić ZM, Maksimović K, Maksimović MS, Vasović I, Vidanović N, Simonović A. Buckling and post-buckling behavior of shell type structures under thermo mechanical loads. in Thermal Science. 2021;25(6):4347-4357.
doi:10.2298/TSCI201129079V .

Vasić, Zoran M., Maksimović, Katarina, Maksimović, Mirko S., Vasović, Ivana, Vidanović, Nenad, Simonović, Aleksandar, "Buckling and post-buckling behavior of shell type structures under thermo mechanical loads" in Thermal Science, 25, no. 6 (2021):4347-4357,
https://doi.org/10.2298/TSCI201129079V . .

TY  - JOUR
AU  - Maksimović, Mirko S.
AU  - Vasović, Ivana
AU  - Maksimović, Katarina
AU  - Trišović, Nataša
AU  - Maksimović, Stevan M.
PY  - 2018
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2793
AB  - Predmet ovog istraživanja je usmeren na uspostavljanje proračunske procedure za analizu čvrstoće elemenata avionskih konstrukcija sa aspekta zamora i mehanike loma. Za tu svrhu ovde će biti uspostavljena proračunska procedura za procenu preostalog veka elemenata avionskih konstrukcija tipa dela oplate krila i uški pod dejstvom cikličnih opterećenja konstantne amplitude i spektra opterećenja. Poseban aspekt istraživanja se odnosi na primenu gustine energije deformacije (GED) za procenu preostalog veka elemenata konstrukcija sa inicijalnim oštećenjima tipa prskotina. Za određivanje analitičkih izraza za faktore intenziteta napona ovde su korišćeni specijalni singularni konačni elementi. Verifikacija proračunskih procedura za procene preostalog veka je podržana sa sa analitičkim i eksperimentalnim rezultatima uključivši i testove na zamor posebno sa aspekta eksperimentalnog određivanja malociklusnih zamornih karakteristika materijala.
AB  - The subject of this investigation is focused on developing computation procedure for strength analysis of damaged aircraft structural components with respect to fatigue and fracture mechanics. For that purpose, here will be defined computation procedures for residual life estimation of aircraft structural components such as wing skin and attachment lugs under cyclic loads of constant amplitude and load spectrum. A special aspect of this investigation is based on using of the Strain Energy Density (SED) method in residual life estimation of structural elements with initial cracks. To determine analytic formulae for the stress intensity factors here singular finite elements are used. Verification of computation procedures for residual life estimations will be supported with corresponding experimental tests for determination of low cyclic fatigue properties of materials and corresponding parameters of fracture mechanics, including fatigue tests of representative aircraft structural elements.
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Procena preostalog veka elemenata avionskih konstrukcija sa inicijalnim prskotinama
T1  - Residual life estimation of cracked aircraft structural components
EP  - 128
IS  - 1
SP  - 124
VL  - 46
DO  - 10.5937/fmet1801124M
ER  - 

@article{
author = "Maksimović, Mirko S. and Vasović, Ivana and Maksimović, Katarina and Trišović, Nataša and Maksimović, Stevan M.",
year = "2018",
abstract = "Predmet ovog istraživanja je usmeren na uspostavljanje proračunske procedure za analizu čvrstoće elemenata avionskih konstrukcija sa aspekta zamora i mehanike loma. Za tu svrhu ovde će biti uspostavljena proračunska procedura za procenu preostalog veka elemenata avionskih konstrukcija tipa dela oplate krila i uški pod dejstvom cikličnih opterećenja konstantne amplitude i spektra opterećenja. Poseban aspekt istraživanja se odnosi na primenu gustine energije deformacije (GED) za procenu preostalog veka elemenata konstrukcija sa inicijalnim oštećenjima tipa prskotina. Za određivanje analitičkih izraza za faktore intenziteta napona ovde su korišćeni specijalni singularni konačni elementi. Verifikacija proračunskih procedura za procene preostalog veka je podržana sa sa analitičkim i eksperimentalnim rezultatima uključivši i testove na zamor posebno sa aspekta eksperimentalnog određivanja malociklusnih zamornih karakteristika materijala., The subject of this investigation is focused on developing computation procedure for strength analysis of damaged aircraft structural components with respect to fatigue and fracture mechanics. For that purpose, here will be defined computation procedures for residual life estimation of aircraft structural components such as wing skin and attachment lugs under cyclic loads of constant amplitude and load spectrum. A special aspect of this investigation is based on using of the Strain Energy Density (SED) method in residual life estimation of structural elements with initial cracks. To determine analytic formulae for the stress intensity factors here singular finite elements are used. Verification of computation procedures for residual life estimations will be supported with corresponding experimental tests for determination of low cyclic fatigue properties of materials and corresponding parameters of fracture mechanics, including fatigue tests of representative aircraft structural elements.",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Procena preostalog veka elemenata avionskih konstrukcija sa inicijalnim prskotinama, Residual life estimation of cracked aircraft structural components",
pages = "128-124",
number = "1",
volume = "46",
doi = "10.5937/fmet1801124M"
}

Maksimović, M. S., Vasović, I., Maksimović, K., Trišović, N.,& Maksimović, S. M.. (2018). Procena preostalog veka elemenata avionskih konstrukcija sa inicijalnim prskotinama. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 46(1), 124-128.
https://doi.org/10.5937/fmet1801124M

Maksimović MS, Vasović I, Maksimović K, Trišović N, Maksimović SM. Procena preostalog veka elemenata avionskih konstrukcija sa inicijalnim prskotinama. in FME Transactions. 2018;46(1):124-128.
doi:10.5937/fmet1801124M .

Maksimović, Mirko S., Vasović, Ivana, Maksimović, Katarina, Trišović, Nataša, Maksimović, Stevan M., "Procena preostalog veka elemenata avionskih konstrukcija sa inicijalnim prskotinama" in FME Transactions, 46, no. 1 (2018):124-128,
https://doi.org/10.5937/fmet1801124M . .

TY  - JOUR
AU  - Janković, D.
AU  - Maksimović, Stevan M.
AU  - Kozić, Mirko
AU  - Stupar, Slobodan
AU  - Maksimović, Katarina
AU  - Vasović, Ivana
AU  - Maksimović, Mirko S.
PY  - 2017
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2574
AB  - This work focuses on defining loads and fatigue life estimation of helicopter tail rotor blades. The original metal construction of these blades was replaced with a new construction of blades made from composite materials. The subject of this investigation is the precise determination of loads of helicopter composite tail rotor blades together with experimental verification of their fatigue strength. In this research to determine loads of tail rotor blades computational fluid dynamics (CFD) numerical simulations are used. To study the fatigue behavior of composite blades, the blades are here tested under static and fatigue load spectra. For determination of aerodynamic loads of tail rotor blades in this investigation, two computation models are used. In first model, an isolated tail rotor blade is considered. In the second computation model, the complete helicopter is modeled, including fuselage together with main and tail rotor blades. The tail rotor hub is not included in these computational models. To verify the strength of the composite structure of the tail rotor blade, it is tested under the static load and fatigue load spectra. The experimental fatigue test results under the load spectrum are included.
PB  - Asce-Amer Soc Civil Engineers, Reston
T2  - Journal of Aerospace Engineering
T1  - CFD Calculation of Helicopter Tail Rotor Airloads for Fatigue Strength Experiments
IS  - 5
VL  - 30
DO  - 10.1061/(ASCE)AS.1943-5525.0000734
ER  - 

@article{
author = "Janković, D. and Maksimović, Stevan M. and Kozić, Mirko and Stupar, Slobodan and Maksimović, Katarina and Vasović, Ivana and Maksimović, Mirko S.",
year = "2017",
abstract = "This work focuses on defining loads and fatigue life estimation of helicopter tail rotor blades. The original metal construction of these blades was replaced with a new construction of blades made from composite materials. The subject of this investigation is the precise determination of loads of helicopter composite tail rotor blades together with experimental verification of their fatigue strength. In this research to determine loads of tail rotor blades computational fluid dynamics (CFD) numerical simulations are used. To study the fatigue behavior of composite blades, the blades are here tested under static and fatigue load spectra. For determination of aerodynamic loads of tail rotor blades in this investigation, two computation models are used. In first model, an isolated tail rotor blade is considered. In the second computation model, the complete helicopter is modeled, including fuselage together with main and tail rotor blades. The tail rotor hub is not included in these computational models. To verify the strength of the composite structure of the tail rotor blade, it is tested under the static load and fatigue load spectra. The experimental fatigue test results under the load spectrum are included.",
publisher = "Asce-Amer Soc Civil Engineers, Reston",
journal = "Journal of Aerospace Engineering",
title = "CFD Calculation of Helicopter Tail Rotor Airloads for Fatigue Strength Experiments",
number = "5",
volume = "30",
doi = "10.1061/(ASCE)AS.1943-5525.0000734"
}

Janković, D., Maksimović, S. M., Kozić, M., Stupar, S., Maksimović, K., Vasović, I.,& Maksimović, M. S.. (2017). CFD Calculation of Helicopter Tail Rotor Airloads for Fatigue Strength Experiments. in Journal of Aerospace Engineering
Asce-Amer Soc Civil Engineers, Reston., 30(5).
https://doi.org/10.1061/(ASCE)AS.1943-5525.0000734

Janković D, Maksimović SM, Kozić M, Stupar S, Maksimović K, Vasović I, Maksimović MS. CFD Calculation of Helicopter Tail Rotor Airloads for Fatigue Strength Experiments. in Journal of Aerospace Engineering. 2017;30(5).
doi:10.1061/(ASCE)AS.1943-5525.0000734 .

Janković, D., Maksimović, Stevan M., Kozić, Mirko, Stupar, Slobodan, Maksimović, Katarina, Vasović, Ivana, Maksimović, Mirko S., "CFD Calculation of Helicopter Tail Rotor Airloads for Fatigue Strength Experiments" in Journal of Aerospace Engineering, 30, no. 5 (2017),
https://doi.org/10.1061/(ASCE)AS.1943-5525.0000734 . .

TY  - JOUR
AU  - Vasović, Ivana
AU  - Maksimović, Stevan M.
AU  - Stamenković, Dragi
AU  - Stupar, Slobodan
AU  - Maksimović, Mirko S.
AU  - Bakić, Gordana
PY  - 2014
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1864
AB  - This paper presents evaluation fracture mechanics parameters in low pressure turbine components. Critical locations such as keyway and dovetail area are experiencing stress concentration leading to crack initiation. Stress intensity factors were evaluated using the J-Integral approach available within ANSYS software code. The finite element method allowed the prediction of the point of crack initiation and the crack propagation using the orientations of the maximum principal stresses. Special attention in this investigation is focused to develop analytic expressions for stress intensity factors at critical location of low pressure steam turbine disc.
PB  - Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd
T2  - Thermal Science
T1  - Fracture mechanics analysis of damaged turbine rotor discs using finite element method
EP  - S112
SP  - S107
VL  - 18
DO  - 10.2298/TSCI121107176V
ER  - 

@article{
author = "Vasović, Ivana and Maksimović, Stevan M. and Stamenković, Dragi and Stupar, Slobodan and Maksimović, Mirko S. and Bakić, Gordana",
year = "2014",
abstract = "This paper presents evaluation fracture mechanics parameters in low pressure turbine components. Critical locations such as keyway and dovetail area are experiencing stress concentration leading to crack initiation. Stress intensity factors were evaluated using the J-Integral approach available within ANSYS software code. The finite element method allowed the prediction of the point of crack initiation and the crack propagation using the orientations of the maximum principal stresses. Special attention in this investigation is focused to develop analytic expressions for stress intensity factors at critical location of low pressure steam turbine disc.",
publisher = "Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd",
journal = "Thermal Science",
title = "Fracture mechanics analysis of damaged turbine rotor discs using finite element method",
pages = "S112-S107",
volume = "18",
doi = "10.2298/TSCI121107176V"
}

Vasović, I., Maksimović, S. M., Stamenković, D., Stupar, S., Maksimović, M. S.,& Bakić, G.. (2014). Fracture mechanics analysis of damaged turbine rotor discs using finite element method. in Thermal Science
Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd., 18, S107-S112.
https://doi.org/10.2298/TSCI121107176V

Vasović I, Maksimović SM, Stamenković D, Stupar S, Maksimović MS, Bakić G. Fracture mechanics analysis of damaged turbine rotor discs using finite element method. in Thermal Science. 2014;18:S107-S112.
doi:10.2298/TSCI121107176V .

Vasović, Ivana, Maksimović, Stevan M., Stamenković, Dragi, Stupar, Slobodan, Maksimović, Mirko S., Bakić, Gordana, "Fracture mechanics analysis of damaged turbine rotor discs using finite element method" in Thermal Science, 18 (2014):S107-S112,
https://doi.org/10.2298/TSCI121107176V . .

TY  - JOUR
AU  - Vasović, Ivana
AU  - Maksimović, Stevan M.
AU  - Maksimović, Katarina
AU  - Stupar, Slobodan
AU  - Bakić, Gordana
AU  - Maksimović, Mirko S.
PY  - 2014
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1863
AB  - An attention in this paper is focused on the stress analysis and the determination of fracture mechanics parameters in low pressure (LP) turbine rotor discs and on developing analytic expressions for stress intensity factors at the critical location of LP steam turbine disc. Critical locations such as keyway and dovetail area experienced stress concentration leading to crack initiation. Major concerns for the power industry are determining the critical locations with one side and fracture mechanics parameters with the other side. For determination of the critical locations in LP turbine rotor disc conventional finite elements are used here. For this initial crack length and during crack growth it is necessary to determine SIFs. In fatigue crack growth process it is necessary to have analytic formulas for the stress intensity factor. To determine analytic formula for stress intensity factor (SIF) of cracked turbine rotor disc special singular finite elements are used. Using discrete values of SIFs which correspond to various crack lengths analytic formula of SIF in polynomial forms is derived here. For determination of SIF in this paper, combined J-integral approach and singular finite elements are used. The interaction of mechanical and thermal effects was correlated in terms of the fracture toughness.
PB  - Hindawi Ltd, London
T2  - Mathematical Problems in Engineering
T1  - Determination of Stress Intensity Factors in Low Pressure Turbine Rotor Discs
VL  - 2014
DO  - 10.1155/2014/304638
ER  - 

@article{
author = "Vasović, Ivana and Maksimović, Stevan M. and Maksimović, Katarina and Stupar, Slobodan and Bakić, Gordana and Maksimović, Mirko S.",
year = "2014",
abstract = "An attention in this paper is focused on the stress analysis and the determination of fracture mechanics parameters in low pressure (LP) turbine rotor discs and on developing analytic expressions for stress intensity factors at the critical location of LP steam turbine disc. Critical locations such as keyway and dovetail area experienced stress concentration leading to crack initiation. Major concerns for the power industry are determining the critical locations with one side and fracture mechanics parameters with the other side. For determination of the critical locations in LP turbine rotor disc conventional finite elements are used here. For this initial crack length and during crack growth it is necessary to determine SIFs. In fatigue crack growth process it is necessary to have analytic formulas for the stress intensity factor. To determine analytic formula for stress intensity factor (SIF) of cracked turbine rotor disc special singular finite elements are used. Using discrete values of SIFs which correspond to various crack lengths analytic formula of SIF in polynomial forms is derived here. For determination of SIF in this paper, combined J-integral approach and singular finite elements are used. The interaction of mechanical and thermal effects was correlated in terms of the fracture toughness.",
publisher = "Hindawi Ltd, London",
journal = "Mathematical Problems in Engineering",
title = "Determination of Stress Intensity Factors in Low Pressure Turbine Rotor Discs",
volume = "2014",
doi = "10.1155/2014/304638"
}

Vasović, I., Maksimović, S. M., Maksimović, K., Stupar, S., Bakić, G.,& Maksimović, M. S.. (2014). Determination of Stress Intensity Factors in Low Pressure Turbine Rotor Discs. in Mathematical Problems in Engineering
Hindawi Ltd, London., 2014.
https://doi.org/10.1155/2014/304638

Vasović I, Maksimović SM, Maksimović K, Stupar S, Bakić G, Maksimović MS. Determination of Stress Intensity Factors in Low Pressure Turbine Rotor Discs. in Mathematical Problems in Engineering. 2014;2014.
doi:10.1155/2014/304638 .

Vasović, Ivana, Maksimović, Stevan M., Maksimović, Katarina, Stupar, Slobodan, Bakić, Gordana, Maksimović, Mirko S., "Determination of Stress Intensity Factors in Low Pressure Turbine Rotor Discs" in Mathematical Problems in Engineering, 2014 (2014),
https://doi.org/10.1155/2014/304638 . .

TY  - JOUR
AU  - Maksimović, Mirko S.
AU  - Nikolić-Stanojević, Vera
AU  - Maksimović, Katarina
AU  - Stupar, Slobodan
PY  - 2012
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1548
AB  - In this investigation fatigue behaviour of damaged structural components under cyclic loads constant amplitude and load spectrum is considered. Primary attention of this investigation is the establishment of computation procedure for the evaluation of the residual life of aircraft attachment lug type structural elements in the presence of initial cracks. In this investigation for residual life estimation and crack growth analysis Strain Energy Density ( SED) method is used. The SED method uses the low-cycle fatigue (LCF) properties of the material in crack growth analysis. In this approach experimentally obtained dynamic properties of the material such as Forman's constants are not required when this method is concerned. The complete computation procedure for the crack propagation analysis using low-cycle fatigue material properties is illustrated with the damaged structural elements. To determine analytic expressions for stress intensity factors (SIF) singular finite elements are used. Results of numerical simulation for crack propagation based on strain density method have been compared with own experimental results.
PB  - Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek
T2  - Tehnički vjesnik
T1  - Damage tolerance analysis of structural components under general load spectrum
EP  - 938
IS  - 4
SP  - 931
VL  - 19
UR  - https://hdl.handle.net/21.15107/rcub_machinery_1548
ER  - 

@article{
author = "Maksimović, Mirko S. and Nikolić-Stanojević, Vera and Maksimović, Katarina and Stupar, Slobodan",
year = "2012",
abstract = "In this investigation fatigue behaviour of damaged structural components under cyclic loads constant amplitude and load spectrum is considered. Primary attention of this investigation is the establishment of computation procedure for the evaluation of the residual life of aircraft attachment lug type structural elements in the presence of initial cracks. In this investigation for residual life estimation and crack growth analysis Strain Energy Density ( SED) method is used. The SED method uses the low-cycle fatigue (LCF) properties of the material in crack growth analysis. In this approach experimentally obtained dynamic properties of the material such as Forman's constants are not required when this method is concerned. The complete computation procedure for the crack propagation analysis using low-cycle fatigue material properties is illustrated with the damaged structural elements. To determine analytic expressions for stress intensity factors (SIF) singular finite elements are used. Results of numerical simulation for crack propagation based on strain density method have been compared with own experimental results.",
publisher = "Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek",
journal = "Tehnički vjesnik",
title = "Damage tolerance analysis of structural components under general load spectrum",
pages = "938-931",
number = "4",
volume = "19",
url = "https://hdl.handle.net/21.15107/rcub_machinery_1548"
}

Maksimović, M. S., Nikolić-Stanojević, V., Maksimović, K.,& Stupar, S.. (2012). Damage tolerance analysis of structural components under general load spectrum. in Tehnički vjesnik
Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek., 19(4), 931-938.
https://hdl.handle.net/21.15107/rcub_machinery_1548

Maksimović MS, Nikolić-Stanojević V, Maksimović K, Stupar S. Damage tolerance analysis of structural components under general load spectrum. in Tehnički vjesnik. 2012;19(4):931-938.
https://hdl.handle.net/21.15107/rcub_machinery_1548 .

Maksimović, Mirko S., Nikolić-Stanojević, Vera, Maksimović, Katarina, Stupar, Slobodan, "Damage tolerance analysis of structural components under general load spectrum" in Tehnički vjesnik, 19, no. 4 (2012):931-938,
https://hdl.handle.net/21.15107/rcub_machinery_1548 .

TY  - JOUR
AU  - Ilić, Ivana
AU  - Petrović, Zlatko
AU  - Maksimović, Mirko S.
AU  - Stupar, Slobodan
AU  - Stamenković, Dragi
PY  - 2012
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1505
AB  - This paper considers a computation method in failure analysis of layered composites containing pin-loaded holes. The investigation is focused on developing a reliable computation procedure to analyze initial failure load for pin-loaded holes at layered composite structures. Finite element method (FEM) is used to determine stress distribution around the fastener hole. Combining Chang-Scott-Springer characteristic curve model and Tsai-Wu initial failure criterion are used to determine joint failure. Special attention in this work is paid to pin-load distributions and its effect on the load level of failure and its location. In previous work initial failure analysis was carried out using cosine distribution between pin/lug mechanically fastened joint. Here contact finite element pin/lug model is analysed. The influence of stacking sequences of layered composites containing pin-loaded holes is also investigated. Special attention is paid to failure load and mode analyses in composites with stacking sequence [0/(+/-45)(3)/90(3)](s). The computation results are compared with available experimental results. Good correlations between computation and experimental results are obtained.
PB  - Assoc Mechanical Engineers Technicians Slovenia, Ljubljana
T2  - Strojniski Vestnik-Journal of Mechanical Engineering
T1  - Computation Method in Failure Analysis of Mechanically Fastened Joints at Layered Composites
EP  - 559
IS  - 9
SP  - 553
VL  - 58
DO  - 10.5545/sv-jme.2011.157
ER  - 

@article{
author = "Ilić, Ivana and Petrović, Zlatko and Maksimović, Mirko S. and Stupar, Slobodan and Stamenković, Dragi",
year = "2012",
abstract = "This paper considers a computation method in failure analysis of layered composites containing pin-loaded holes. The investigation is focused on developing a reliable computation procedure to analyze initial failure load for pin-loaded holes at layered composite structures. Finite element method (FEM) is used to determine stress distribution around the fastener hole. Combining Chang-Scott-Springer characteristic curve model and Tsai-Wu initial failure criterion are used to determine joint failure. Special attention in this work is paid to pin-load distributions and its effect on the load level of failure and its location. In previous work initial failure analysis was carried out using cosine distribution between pin/lug mechanically fastened joint. Here contact finite element pin/lug model is analysed. The influence of stacking sequences of layered composites containing pin-loaded holes is also investigated. Special attention is paid to failure load and mode analyses in composites with stacking sequence [0/(+/-45)(3)/90(3)](s). The computation results are compared with available experimental results. Good correlations between computation and experimental results are obtained.",
publisher = "Assoc Mechanical Engineers Technicians Slovenia, Ljubljana",
journal = "Strojniski Vestnik-Journal of Mechanical Engineering",
title = "Computation Method in Failure Analysis of Mechanically Fastened Joints at Layered Composites",
pages = "559-553",
number = "9",
volume = "58",
doi = "10.5545/sv-jme.2011.157"
}

Ilić, I., Petrović, Z., Maksimović, M. S., Stupar, S.,& Stamenković, D.. (2012). Computation Method in Failure Analysis of Mechanically Fastened Joints at Layered Composites. in Strojniski Vestnik-Journal of Mechanical Engineering
Assoc Mechanical Engineers Technicians Slovenia, Ljubljana., 58(9), 553-559.
https://doi.org/10.5545/sv-jme.2011.157

Ilić I, Petrović Z, Maksimović MS, Stupar S, Stamenković D. Computation Method in Failure Analysis of Mechanically Fastened Joints at Layered Composites. in Strojniski Vestnik-Journal of Mechanical Engineering. 2012;58(9):553-559.
doi:10.5545/sv-jme.2011.157 .

Ilić, Ivana, Petrović, Zlatko, Maksimović, Mirko S., Stupar, Slobodan, Stamenković, Dragi, "Computation Method in Failure Analysis of Mechanically Fastened Joints at Layered Composites" in Strojniski Vestnik-Journal of Mechanical Engineering, 58, no. 9 (2012):553-559,
https://doi.org/10.5545/sv-jme.2011.157 . .