TY  - JOUR
AU  - Rašuo, Boško
AU  - Dinulović, Mirko
AU  - Trninić, Marta
AU  - Stamenović, Marina
AU  - Milošević, Novak
AU  - Ćurčić, Nebojša
PY  - 2021
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3612
AB  - Buka je jedan od problema u mnogim industrijama. U ovom radu prikazana je analiza aerodinamički nastale buke koja se javlja pri strujanjima vazduha preko usmerivača vazduha oblika aeroprofila u vazdušnim kanalima. Na osnovu Proudmanove jednačine i Lajthilove akustične analogije širokopojasni nivo buke u vazdušnom kanalu može biti izračunat. Za modeliranje turbulentnog modela, k - e turbulentni model je korišćen a potrebne konstante su eksperimentalno određene merenjem u aerotunelu za podzvučne brzine, nakon kojih su vršena merenja buke za u neposrednoj blizini usmerivača vazduha oblika aeroprofila. Nekoliko rešenja je analizirano, kanal sa unutrašnjim aeroprofilom, kanal sa centralnim aeroprofilom, kanal sa spoljašnjim aeroprofilom kao i kombinacija prethodnih slučajeva. Analizom dobijenih rezultata, a u cilju ispunjavanja svih zakonskih propisa koji se tiču industrijske buke, koji postaju sve striktniji, akustična analiza i projektovanje moraju biti primenjeni u većini industrijskih sistema jer buka predstavlja opasnost po zdravlje radnika u radnom okruženju.
AB  - Noise is becoming one of the problems in many industrial applications. In this paper the aerodynamic noise in air duct system that arises from air flow passing over a surface of turning vanes is investigated. Based on Proudman's formula using Lighthill's acoustic analogy broadband acoustic noise model can be predicted. To model the turbulent flow in an air duct k - e turbulent model is used and required constants are obtained experimentally in a low speed wind tunnel followed by noise measurement in the vicinity of deflected airfoil. Several designs are investigated: Inner airfoil in the duct elbow, center positioned air foil, outer positioned and the overall combination of all previous cases. It was found that in order to satisfy all noise requirements and regulation, which are becoming more strict nowadays, the acoustic analysis and design must be performed in most industrial systems since the noise levels arising from the operating industrial equipment may represent occupational and health hazard.
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Analiza aerodinamičke buke u ventilacionim kanalima sa umerivačima vazduha
T1  - A study of aerodynamic noise in air duct systems with turning vanes
EP  - 314
IS  - 2
SP  - 308
VL  - 49
DO  - 10.5937/fme2102308R
ER  - 

@article{
author = "Rašuo, Boško and Dinulović, Mirko and Trninić, Marta and Stamenović, Marina and Milošević, Novak and Ćurčić, Nebojša",
year = "2021",
abstract = "Buka je jedan od problema u mnogim industrijama. U ovom radu prikazana je analiza aerodinamički nastale buke koja se javlja pri strujanjima vazduha preko usmerivača vazduha oblika aeroprofila u vazdušnim kanalima. Na osnovu Proudmanove jednačine i Lajthilove akustične analogije širokopojasni nivo buke u vazdušnom kanalu može biti izračunat. Za modeliranje turbulentnog modela, k - e turbulentni model je korišćen a potrebne konstante su eksperimentalno određene merenjem u aerotunelu za podzvučne brzine, nakon kojih su vršena merenja buke za u neposrednoj blizini usmerivača vazduha oblika aeroprofila. Nekoliko rešenja je analizirano, kanal sa unutrašnjim aeroprofilom, kanal sa centralnim aeroprofilom, kanal sa spoljašnjim aeroprofilom kao i kombinacija prethodnih slučajeva. Analizom dobijenih rezultata, a u cilju ispunjavanja svih zakonskih propisa koji se tiču industrijske buke, koji postaju sve striktniji, akustična analiza i projektovanje moraju biti primenjeni u većini industrijskih sistema jer buka predstavlja opasnost po zdravlje radnika u radnom okruženju., Noise is becoming one of the problems in many industrial applications. In this paper the aerodynamic noise in air duct system that arises from air flow passing over a surface of turning vanes is investigated. Based on Proudman's formula using Lighthill's acoustic analogy broadband acoustic noise model can be predicted. To model the turbulent flow in an air duct k - e turbulent model is used and required constants are obtained experimentally in a low speed wind tunnel followed by noise measurement in the vicinity of deflected airfoil. Several designs are investigated: Inner airfoil in the duct elbow, center positioned air foil, outer positioned and the overall combination of all previous cases. It was found that in order to satisfy all noise requirements and regulation, which are becoming more strict nowadays, the acoustic analysis and design must be performed in most industrial systems since the noise levels arising from the operating industrial equipment may represent occupational and health hazard.",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Analiza aerodinamičke buke u ventilacionim kanalima sa umerivačima vazduha, A study of aerodynamic noise in air duct systems with turning vanes",
pages = "314-308",
number = "2",
volume = "49",
doi = "10.5937/fme2102308R"
}

Rašuo, B., Dinulović, M., Trninić, M., Stamenović, M., Milošević, N.,& Ćurčić, N.. (2021). Analiza aerodinamičke buke u ventilacionim kanalima sa umerivačima vazduha. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 49(2), 308-314.
https://doi.org/10.5937/fme2102308R

Rašuo B, Dinulović M, Trninić M, Stamenović M, Milošević N, Ćurčić N. Analiza aerodinamičke buke u ventilacionim kanalima sa umerivačima vazduha. in FME Transactions. 2021;49(2):308-314.
doi:10.5937/fme2102308R .

Rašuo, Boško, Dinulović, Mirko, Trninić, Marta, Stamenović, Marina, Milošević, Novak, Ćurčić, Nebojša, "Analiza aerodinamičke buke u ventilacionim kanalima sa umerivačima vazduha" in FME Transactions, 49, no. 2 (2021):308-314,
https://doi.org/10.5937/fme2102308R . .

TY  - JOUR
AU  - Dinulović, Mirko
AU  - Rašuo, Boško
AU  - Trninić, Marta
AU  - Adžić, Vuk M.
PY  - 2020
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3258
AB  - Kompozitne ploče sa saćastom ispunom se sve više koriste pri izradi primarnih vazduhoplovnih struktura. Ovi materijali koriste se pri konstrukciji oplata trupova letelica, centralnih i spoljnih torzionih kutija krila, oplata pogonskih grupa, vrata stajnih trapova, komandnih površina kao što su spojleri i eleroni. Da bi se odredila polja napona i deformacija opterećene strukture neophodno je poznavanje svih elastičnih koeficijenata. U ovom radu, metod za određivanje svih potrebnih elastičnih koeficijenata ispune i ploča je predstavljen. Koristeći se eksperimentalno dobijenim rezultatima za papir NOMEH (tip 410 ) kao i fenolnu matricu materijalni model je predstavljen, izrađen je model konačnih elemenata kompozitne ploče sa saćastom ispunom i numerički je simuliran test savijanja u tri tačke. Dobijeni rezultati upoređeni su sa rezultatima dobijenim eksperimentom. Primećeno je dobro slaganje između predloženog modela materijala i eksperimentalno dobijenih vrednosti.
AB  - Honeycomb core composite plates are becoming more important in the construction of primary aerospace structures. Nowadays, these types of materials are used for construction of fuselage skins, central and outer wing boxes, engine tail cones, landing gear doors, command surfaces like spoilers and ailerons etc. To determine the stress strain field in loaded honeycomb plates elastic coefficients are required. In the present work, a method for determining all required elastic coefficients for the core and plates is presented. Using experimentally obtained values for Nomex paper (type 410) and phenolic resin material model is presented and FEA model of composite plate with honeycomb core is created and three point bend test is simulated. Numerically obtained stress and strain values are compared to the experiment. Good agreement between proposed material model and experimentally obtained values is observed.
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Numeričko modeliranje kompozitnih ploča sa NOMEH saćastom ispunom na mezo nivou
T1  - Numerical modeling of Nomex honeycomb core composite plates at meso scale level
EP  - 881
IS  - 4
SP  - 874
VL  - 48
DO  - 10.5937/fme2004874D
ER  - 

@article{
author = "Dinulović, Mirko and Rašuo, Boško and Trninić, Marta and Adžić, Vuk M.",
year = "2020",
abstract = "Kompozitne ploče sa saćastom ispunom se sve više koriste pri izradi primarnih vazduhoplovnih struktura. Ovi materijali koriste se pri konstrukciji oplata trupova letelica, centralnih i spoljnih torzionih kutija krila, oplata pogonskih grupa, vrata stajnih trapova, komandnih površina kao što su spojleri i eleroni. Da bi se odredila polja napona i deformacija opterećene strukture neophodno je poznavanje svih elastičnih koeficijenata. U ovom radu, metod za određivanje svih potrebnih elastičnih koeficijenata ispune i ploča je predstavljen. Koristeći se eksperimentalno dobijenim rezultatima za papir NOMEH (tip 410 ) kao i fenolnu matricu materijalni model je predstavljen, izrađen je model konačnih elemenata kompozitne ploče sa saćastom ispunom i numerički je simuliran test savijanja u tri tačke. Dobijeni rezultati upoređeni su sa rezultatima dobijenim eksperimentom. Primećeno je dobro slaganje između predloženog modela materijala i eksperimentalno dobijenih vrednosti., Honeycomb core composite plates are becoming more important in the construction of primary aerospace structures. Nowadays, these types of materials are used for construction of fuselage skins, central and outer wing boxes, engine tail cones, landing gear doors, command surfaces like spoilers and ailerons etc. To determine the stress strain field in loaded honeycomb plates elastic coefficients are required. In the present work, a method for determining all required elastic coefficients for the core and plates is presented. Using experimentally obtained values for Nomex paper (type 410) and phenolic resin material model is presented and FEA model of composite plate with honeycomb core is created and three point bend test is simulated. Numerically obtained stress and strain values are compared to the experiment. Good agreement between proposed material model and experimentally obtained values is observed.",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Numeričko modeliranje kompozitnih ploča sa NOMEH saćastom ispunom na mezo nivou, Numerical modeling of Nomex honeycomb core composite plates at meso scale level",
pages = "881-874",
number = "4",
volume = "48",
doi = "10.5937/fme2004874D"
}

Dinulović, M., Rašuo, B., Trninić, M.,& Adžić, V. M.. (2020). Numeričko modeliranje kompozitnih ploča sa NOMEH saćastom ispunom na mezo nivou. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 48(4), 874-881.
https://doi.org/10.5937/fme2004874D

Dinulović M, Rašuo B, Trninić M, Adžić VM. Numeričko modeliranje kompozitnih ploča sa NOMEH saćastom ispunom na mezo nivou. in FME Transactions. 2020;48(4):874-881.
doi:10.5937/fme2004874D .

Dinulović, Mirko, Rašuo, Boško, Trninić, Marta, Adžić, Vuk M., "Numeričko modeliranje kompozitnih ploča sa NOMEH saćastom ispunom na mezo nivou" in FME Transactions, 48, no. 4 (2020):874-881,
https://doi.org/10.5937/fme2004874D . .

TY  - JOUR
AU  - Trninić, Marta
AU  - Rašuo, Boško
AU  - Dinulović, Mirko
PY  - 2020
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3255
AB  - U ovom radu prikazana je metodologija proračuna strujanja vazduha u vazdušnim kanalima koji su modifikovani dodavanjem specijalnih usmerivača vazduha segmentnog oblika poprečnog preseka aeroprofila. Modifikacija vazdušnog kanala izvršena u cilju smanjenja pada pritiska na izlazu samog kanala kao i u cilju smanjenja vibracija koje se javljaju tokom strujanja radnog fluida kroz kanal. Predstavljena metodologija proračuna strujanja zasnovana je na savremenim numeričkim metodama proračuna strujanja (CFD) odnosno metodi konačnih elemenata (FEA) za proračun vibracija i čvrstoće konstrukcije.
AB  - In this work complete methodology for calculation and analysis of fluid flow in air ducts is presented. In order to minimize outlet pressure drop and to reduce the duct vibrations the plates with airfoil cross sections are added to duct critical zones. It was observed that airfoil stream plates efficiently contribute to outlet pressure drop, duct vibration and noise reduction. Modern methods such as CFD and FEA can be efficiently deployed in numerical treatise of flow and vibration analysis in air ducts.
PB  - Savez inženjera i tehničara Srbije, Beograd
T2  - Tehnika
T1  - Modifikacija vazdušnog kanala u cilju smanjenja vibracija i postizanja manjeg pada pritiska
T1  - Air duct modification towards outlet pressure drop and vibration level reduction
EP  - 466
IS  - 4
SP  - 457
VL  - 75
DO  - 10.5937/tehnika2004457T
ER  - 

@article{
author = "Trninić, Marta and Rašuo, Boško and Dinulović, Mirko",
year = "2020",
abstract = "U ovom radu prikazana je metodologija proračuna strujanja vazduha u vazdušnim kanalima koji su modifikovani dodavanjem specijalnih usmerivača vazduha segmentnog oblika poprečnog preseka aeroprofila. Modifikacija vazdušnog kanala izvršena u cilju smanjenja pada pritiska na izlazu samog kanala kao i u cilju smanjenja vibracija koje se javljaju tokom strujanja radnog fluida kroz kanal. Predstavljena metodologija proračuna strujanja zasnovana je na savremenim numeričkim metodama proračuna strujanja (CFD) odnosno metodi konačnih elemenata (FEA) za proračun vibracija i čvrstoće konstrukcije., In this work complete methodology for calculation and analysis of fluid flow in air ducts is presented. In order to minimize outlet pressure drop and to reduce the duct vibrations the plates with airfoil cross sections are added to duct critical zones. It was observed that airfoil stream plates efficiently contribute to outlet pressure drop, duct vibration and noise reduction. Modern methods such as CFD and FEA can be efficiently deployed in numerical treatise of flow and vibration analysis in air ducts.",
publisher = "Savez inženjera i tehničara Srbije, Beograd",
journal = "Tehnika",
title = "Modifikacija vazdušnog kanala u cilju smanjenja vibracija i postizanja manjeg pada pritiska, Air duct modification towards outlet pressure drop and vibration level reduction",
pages = "466-457",
number = "4",
volume = "75",
doi = "10.5937/tehnika2004457T"
}

Trninić, M., Rašuo, B.,& Dinulović, M.. (2020). Modifikacija vazdušnog kanala u cilju smanjenja vibracija i postizanja manjeg pada pritiska. in Tehnika
Savez inženjera i tehničara Srbije, Beograd., 75(4), 457-466.
https://doi.org/10.5937/tehnika2004457T

Trninić M, Rašuo B, Dinulović M. Modifikacija vazdušnog kanala u cilju smanjenja vibracija i postizanja manjeg pada pritiska. in Tehnika. 2020;75(4):457-466.
doi:10.5937/tehnika2004457T .

Trninić, Marta, Rašuo, Boško, Dinulović, Mirko, "Modifikacija vazdušnog kanala u cilju smanjenja vibracija i postizanja manjeg pada pritiska" in Tehnika, 75, no. 4 (2020):457-466,
https://doi.org/10.5937/tehnika2004457T . .

TY  - JOUR
AU  - Monticeli, Francisco Maciel
AU  - Daou, David
AU  - Dinulović, Mirko
AU  - Cornelis Voorwald, Herman Jacobus
AU  - Hilario Cioffi, Maria Odila
PY  - 2019
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3097
AB  - Considering aeronautics requirements, academies and industries are developing matrixes and reinforcements with higher mechanical performance. The same occurs with the process where new studies focus on obtaining composites with suitable matrix/reinforcement interface. The use of epoxy resin and carbon fiber with high mechanical performance does not guarantee a composite with high mechanical properties, considering imperfections and void formation along the laminate in case of inappropriate processing parameters. The aim of this article was to analyze and quantify the mechanical behavior of polymer composite reinforced with continuous fibers using finite element methodology and postprocessing software simulation. In addition, the classical laminate theory and finite elements were used to simulate flexural and tensile tests of composite specimens. Simulation results were compared with experimental test results using a carbon fiber noncrimp fabric quadriaxial/epoxy resin composite processed by resin transfer molding. Although void volume fraction for structural materials presenting results under aeronautics requirements regarding of 2%, imperfections like lack of resin and impregnation discontinuity showed an influence in tensile and flexural experimental results. Experimental mechanical behavior decreased 10% of strength, in comparison with simulation results due to imperfection on impregnation measured by C-Scan map. Improvement in processing procedures could able to provide greater impregnation continuity, reducing defect formation and ensuring better matrix/reinforcement interface. As a final conclusion, the process plays a role as important as the characteristics of reinforcement and matrix and, consequently, the mechanical properties.
PB  - Sage Publications Ltd, London
T2  - Polymers & Polymer Composites
T1  - Mechanical behavior simulation: NCF/epoxy composite processed by RTM
EP  - 75
IS  - 2
SP  - 66
VL  - 27
DO  - 10.1177/0967391118817174
ER  - 

@article{
author = "Monticeli, Francisco Maciel and Daou, David and Dinulović, Mirko and Cornelis Voorwald, Herman Jacobus and Hilario Cioffi, Maria Odila",
year = "2019",
abstract = "Considering aeronautics requirements, academies and industries are developing matrixes and reinforcements with higher mechanical performance. The same occurs with the process where new studies focus on obtaining composites with suitable matrix/reinforcement interface. The use of epoxy resin and carbon fiber with high mechanical performance does not guarantee a composite with high mechanical properties, considering imperfections and void formation along the laminate in case of inappropriate processing parameters. The aim of this article was to analyze and quantify the mechanical behavior of polymer composite reinforced with continuous fibers using finite element methodology and postprocessing software simulation. In addition, the classical laminate theory and finite elements were used to simulate flexural and tensile tests of composite specimens. Simulation results were compared with experimental test results using a carbon fiber noncrimp fabric quadriaxial/epoxy resin composite processed by resin transfer molding. Although void volume fraction for structural materials presenting results under aeronautics requirements regarding of 2%, imperfections like lack of resin and impregnation discontinuity showed an influence in tensile and flexural experimental results. Experimental mechanical behavior decreased 10% of strength, in comparison with simulation results due to imperfection on impregnation measured by C-Scan map. Improvement in processing procedures could able to provide greater impregnation continuity, reducing defect formation and ensuring better matrix/reinforcement interface. As a final conclusion, the process plays a role as important as the characteristics of reinforcement and matrix and, consequently, the mechanical properties.",
publisher = "Sage Publications Ltd, London",
journal = "Polymers & Polymer Composites",
title = "Mechanical behavior simulation: NCF/epoxy composite processed by RTM",
pages = "75-66",
number = "2",
volume = "27",
doi = "10.1177/0967391118817174"
}

Monticeli, F. M., Daou, D., Dinulović, M., Cornelis Voorwald, H. J.,& Hilario Cioffi, M. O.. (2019). Mechanical behavior simulation: NCF/epoxy composite processed by RTM. in Polymers & Polymer Composites
Sage Publications Ltd, London., 27(2), 66-75.
https://doi.org/10.1177/0967391118817174

Monticeli FM, Daou D, Dinulović M, Cornelis Voorwald HJ, Hilario Cioffi MO. Mechanical behavior simulation: NCF/epoxy composite processed by RTM. in Polymers & Polymer Composites. 2019;27(2):66-75.
doi:10.1177/0967391118817174 .

Monticeli, Francisco Maciel, Daou, David, Dinulović, Mirko, Cornelis Voorwald, Herman Jacobus, Hilario Cioffi, Maria Odila, "Mechanical behavior simulation: NCF/epoxy composite processed by RTM" in Polymers & Polymer Composites, 27, no. 2 (2019):66-75,
https://doi.org/10.1177/0967391118817174 . .

TY  - JOUR
AU  - Sghayer, Abulgasem
AU  - Grbović, Aleksandar
AU  - Sedmak, Aleksandar
AU  - Dinulović, Mirko
AU  - Grozdanović, Ines
AU  - Sedmak, Simon
AU  - Petrovski, Blagoj
PY  - 2018
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2758
AB  - Experimental and numerical analysis of fatigue crack growth in integral skin-stringer panels, produced by means of laser beam welding (LBW), is performed. Since this type of panel is used in airframe construction, fatigue and damage tolerance is of paramount importance, since aircrafts must be tolerant to relatively large fatigue cracks. Firstly, using extended finite element method (XFEM), the fatigue crack growth on the simple flat plate made of AL-AA 6156T6/ 2.8 mm was simulated, and results were compared with values obtained in the experiment. The same approach was taken to simulate the fatigue behaviour and crack propagation of the real skinstringer panel (four stringers, laser beam welded). It was found that the results obtained for stress intensity factors (SIFs) KI, KII, KIII and Keff along the crack front, are close to the experimental results, leading to conclusion that the XFEM method can be successfully used in prediction of fatigue life of complex airframe structures, such as laserbeam welded skin-stringer panels.
PB  - Univ Osijek, Tech Fac, Slavonski Brod
T2  - Tehnički vjesnik
T1  - Experimental and Numerical Analysis of Fatigue Crack Growth in Integral Skin-Stringer Panels
EP  - 791
IS  - 3
SP  - 785
VL  - 25
DO  - 10.17559/TV-20170308110329
ER  - 

@article{
author = "Sghayer, Abulgasem and Grbović, Aleksandar and Sedmak, Aleksandar and Dinulović, Mirko and Grozdanović, Ines and Sedmak, Simon and Petrovski, Blagoj",
year = "2018",
abstract = "Experimental and numerical analysis of fatigue crack growth in integral skin-stringer panels, produced by means of laser beam welding (LBW), is performed. Since this type of panel is used in airframe construction, fatigue and damage tolerance is of paramount importance, since aircrafts must be tolerant to relatively large fatigue cracks. Firstly, using extended finite element method (XFEM), the fatigue crack growth on the simple flat plate made of AL-AA 6156T6/ 2.8 mm was simulated, and results were compared with values obtained in the experiment. The same approach was taken to simulate the fatigue behaviour and crack propagation of the real skinstringer panel (four stringers, laser beam welded). It was found that the results obtained for stress intensity factors (SIFs) KI, KII, KIII and Keff along the crack front, are close to the experimental results, leading to conclusion that the XFEM method can be successfully used in prediction of fatigue life of complex airframe structures, such as laserbeam welded skin-stringer panels.",
publisher = "Univ Osijek, Tech Fac, Slavonski Brod",
journal = "Tehnički vjesnik",
title = "Experimental and Numerical Analysis of Fatigue Crack Growth in Integral Skin-Stringer Panels",
pages = "791-785",
number = "3",
volume = "25",
doi = "10.17559/TV-20170308110329"
}

Sghayer, A., Grbović, A., Sedmak, A., Dinulović, M., Grozdanović, I., Sedmak, S.,& Petrovski, B.. (2018). Experimental and Numerical Analysis of Fatigue Crack Growth in Integral Skin-Stringer Panels. in Tehnički vjesnik
Univ Osijek, Tech Fac, Slavonski Brod., 25(3), 785-791.
https://doi.org/10.17559/TV-20170308110329

Sghayer A, Grbović A, Sedmak A, Dinulović M, Grozdanović I, Sedmak S, Petrovski B. Experimental and Numerical Analysis of Fatigue Crack Growth in Integral Skin-Stringer Panels. in Tehnički vjesnik. 2018;25(3):785-791.
doi:10.17559/TV-20170308110329 .

Sghayer, Abulgasem, Grbović, Aleksandar, Sedmak, Aleksandar, Dinulović, Mirko, Grozdanović, Ines, Sedmak, Simon, Petrovski, Blagoj, "Experimental and Numerical Analysis of Fatigue Crack Growth in Integral Skin-Stringer Panels" in Tehnički vjesnik, 25, no. 3 (2018):785-791,
https://doi.org/10.17559/TV-20170308110329 . .

TY  - JOUR
AU  - Sghayer, Abulgasem
AU  - Grbović, Aleksandar
AU  - Sedmak, Aleksandar
AU  - Dinulović, Mirko
AU  - Doncheva, Elisaveta
AU  - Petrovski, Blagoj
PY  - 2017
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2711
AB  - Fatigue life of integral skin-stringer panels produced by laser beam welding (LBW) is analysed. This type of panel is used in airframe construction where fatigue and damage tolerance are of paramount importance, since aircrafts must be designed to tolerate relatively large fatigue cracks. The analysed integral skin-stringer panel is made of AL-AA 6156T6/2.8 mm, where stringers are laser beam welded to the airframe skin. By using the extended finite element method (XFEM), fatigue life of simple flat plate, as well of the skin-stringer panel, are numerically simulated in order to investigate the effect of stringers.
PB  - Institut za ispitivanje materijala, Beograd
T2  - Structural Integrity and Life
T1  - Fatigue life analysis of the integral skin-stringer panel using xfem
EP  - 10
IS  - 1
SP  - 7
VL  - 17
UR  - https://hdl.handle.net/21.15107/rcub_machinery_2711
ER  - 

@article{
author = "Sghayer, Abulgasem and Grbović, Aleksandar and Sedmak, Aleksandar and Dinulović, Mirko and Doncheva, Elisaveta and Petrovski, Blagoj",
year = "2017",
abstract = "Fatigue life of integral skin-stringer panels produced by laser beam welding (LBW) is analysed. This type of panel is used in airframe construction where fatigue and damage tolerance are of paramount importance, since aircrafts must be designed to tolerate relatively large fatigue cracks. The analysed integral skin-stringer panel is made of AL-AA 6156T6/2.8 mm, where stringers are laser beam welded to the airframe skin. By using the extended finite element method (XFEM), fatigue life of simple flat plate, as well of the skin-stringer panel, are numerically simulated in order to investigate the effect of stringers.",
publisher = "Institut za ispitivanje materijala, Beograd",
journal = "Structural Integrity and Life",
title = "Fatigue life analysis of the integral skin-stringer panel using xfem",
pages = "10-7",
number = "1",
volume = "17",
url = "https://hdl.handle.net/21.15107/rcub_machinery_2711"
}

Sghayer, A., Grbović, A., Sedmak, A., Dinulović, M., Doncheva, E.,& Petrovski, B.. (2017). Fatigue life analysis of the integral skin-stringer panel using xfem. in Structural Integrity and Life
Institut za ispitivanje materijala, Beograd., 17(1), 7-10.
https://hdl.handle.net/21.15107/rcub_machinery_2711

Sghayer A, Grbović A, Sedmak A, Dinulović M, Doncheva E, Petrovski B. Fatigue life analysis of the integral skin-stringer panel using xfem. in Structural Integrity and Life. 2017;17(1):7-10.
https://hdl.handle.net/21.15107/rcub_machinery_2711 .

Sghayer, Abulgasem, Grbović, Aleksandar, Sedmak, Aleksandar, Dinulović, Mirko, Doncheva, Elisaveta, Petrovski, Blagoj, "Fatigue life analysis of the integral skin-stringer panel using xfem" in Structural Integrity and Life, 17, no. 1 (2017):7-10,
https://hdl.handle.net/21.15107/rcub_machinery_2711 .

TY  - JOUR
AU  - Fotev, Vasko
AU  - Dinulović, Mirko
PY  - 2017
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2627
AB  - Rad izlaže realizovanu 3D CFD simulaciju faze paljenja gasnog gorionika sa ciljem određivanja maksimalne temperaturske razlike koja u njemu izaziva maksimalne termičke napone. Proces je nestacionaran. Simulacije je realizovana za minimalnu snagu jer je taj slučaj kritičan.
AB  - This paper presents performed 3D CFD simulation of burner start-up and finding the maximal temperature difference through mantle thickness which induces maximal thermal stress. The process is unsteady, beginning from the mantle room temperature and ending with its steady state condition. The behavior of burner is simulated for minimal thermal power, i.e., for critical conditions from the mantle temperature standpoint.
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Prenos toplote i termomehaničko ponašanje atmosmosferskog gorionika kućne gasne grejalice
T1  - Heat transfer and thermo-mechanical behavior of the domestic heater atmospheric burner
EP  - 68
IS  - 1
SP  - 65
VL  - 45
DO  - 10.5937/fmet1701065F
ER  - 

@article{
author = "Fotev, Vasko and Dinulović, Mirko",
year = "2017",
abstract = "Rad izlaže realizovanu 3D CFD simulaciju faze paljenja gasnog gorionika sa ciljem određivanja maksimalne temperaturske razlike koja u njemu izaziva maksimalne termičke napone. Proces je nestacionaran. Simulacije je realizovana za minimalnu snagu jer je taj slučaj kritičan., This paper presents performed 3D CFD simulation of burner start-up and finding the maximal temperature difference through mantle thickness which induces maximal thermal stress. The process is unsteady, beginning from the mantle room temperature and ending with its steady state condition. The behavior of burner is simulated for minimal thermal power, i.e., for critical conditions from the mantle temperature standpoint.",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Prenos toplote i termomehaničko ponašanje atmosmosferskog gorionika kućne gasne grejalice, Heat transfer and thermo-mechanical behavior of the domestic heater atmospheric burner",
pages = "68-65",
number = "1",
volume = "45",
doi = "10.5937/fmet1701065F"
}

Fotev, V.,& Dinulović, M.. (2017). Prenos toplote i termomehaničko ponašanje atmosmosferskog gorionika kućne gasne grejalice. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 45(1), 65-68.
https://doi.org/10.5937/fmet1701065F

Fotev V, Dinulović M. Prenos toplote i termomehaničko ponašanje atmosmosferskog gorionika kućne gasne grejalice. in FME Transactions. 2017;45(1):65-68.
doi:10.5937/fmet1701065F .

Fotev, Vasko, Dinulović, Mirko, "Prenos toplote i termomehaničko ponašanje atmosmosferskog gorionika kućne gasne grejalice" in FME Transactions, 45, no. 1 (2017):65-68,
https://doi.org/10.5937/fmet1701065F . .

TY  - JOUR
AU  - Rebhi, Lamine
AU  - Dinulović, Mirko
AU  - Dunjić, Momčilo
AU  - Grbović, Aleksandar
AU  - Krstić, Branimir
PY  - 2017
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2615
AB  - U radu je predstavljena metoda proračuna efektivnog modula smicanja kompozitnih panela sa sendvič ispunom. Ovaj koeficijent elastičnosti predstavlja vrlo važnu karakteristiku materijala, posebno kod konstrukcija koje su izložene čistoj torziji ili kombinaciji savijanja i torzije. Strukture koje su ispitivane u ovom istraživanju su ravne ploče načinjene od gornjeg i donjeg kompozitnog lica i ispunom (jezgrom) od šestougaonog kompozitnog sendvič materijala. Polazeći od klasične teorije laminata određen je efektivni modul smicanja gornje i donje ploče za svaki sloj u stoku (laminatu). Ovi slojevi platana se svode u jedan kompozitni sloj sa različitim orijentacijama vlakana i debljine. Da bi se verifikovao ovaj prilaz korišćen je Metod konačnih elemenata da bi se odredila pomeranja, deformacije i naponi u kompozitnim pločama i sendvič ispuni. Dva tipa numeričkih modela su upoređivani: početni model, gde su svi spojevi ploče modelirani sa svojim karakteristikama i drugi model kod kojeg su spojeni u jednu celinu sa svojim ekvivalentnim karakteristikama.
AB  - Calculation Method for the effective shear modulus of composite plates with sandwich cores is presented. This elastic coefficient represents one very important material property especially in constructions subjected to pure torsion and combined bending - torsion. The structures investigated in this research are flat plates made of top and bottom composite facesheets and hexagonal composite material sandwich core. Starting from classical Lamination theory the effective shear modulus of top and bottom plates was determined for each ply in the stack up sequence. These plies were 'lumped into a single composite layer for different fiber orientations and plies thicknesses. To verify this approach Finite element method was used to determine the displacement, stress and strain field on Composite plates with Sandwich Cores. Two types of models were compared: The initial model where all the material components, plates and the core were modeled with their intrinsic properties and 'lumped' model with calculated effective elastic coefficients.
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Proračun efektivnog modula smicanja kompozitnih sendvič panela
T1  - Calculation of the effective shear modulus of composite sandwich panels
EP  - 542
IS  - 4
SP  - 537
VL  - 45
DO  - 10.5937/fmet1704537R
ER  - 

@article{
author = "Rebhi, Lamine and Dinulović, Mirko and Dunjić, Momčilo and Grbović, Aleksandar and Krstić, Branimir",
year = "2017",
abstract = "U radu je predstavljena metoda proračuna efektivnog modula smicanja kompozitnih panela sa sendvič ispunom. Ovaj koeficijent elastičnosti predstavlja vrlo važnu karakteristiku materijala, posebno kod konstrukcija koje su izložene čistoj torziji ili kombinaciji savijanja i torzije. Strukture koje su ispitivane u ovom istraživanju su ravne ploče načinjene od gornjeg i donjeg kompozitnog lica i ispunom (jezgrom) od šestougaonog kompozitnog sendvič materijala. Polazeći od klasične teorije laminata određen je efektivni modul smicanja gornje i donje ploče za svaki sloj u stoku (laminatu). Ovi slojevi platana se svode u jedan kompozitni sloj sa različitim orijentacijama vlakana i debljine. Da bi se verifikovao ovaj prilaz korišćen je Metod konačnih elemenata da bi se odredila pomeranja, deformacije i naponi u kompozitnim pločama i sendvič ispuni. Dva tipa numeričkih modela su upoređivani: početni model, gde su svi spojevi ploče modelirani sa svojim karakteristikama i drugi model kod kojeg su spojeni u jednu celinu sa svojim ekvivalentnim karakteristikama., Calculation Method for the effective shear modulus of composite plates with sandwich cores is presented. This elastic coefficient represents one very important material property especially in constructions subjected to pure torsion and combined bending - torsion. The structures investigated in this research are flat plates made of top and bottom composite facesheets and hexagonal composite material sandwich core. Starting from classical Lamination theory the effective shear modulus of top and bottom plates was determined for each ply in the stack up sequence. These plies were 'lumped into a single composite layer for different fiber orientations and plies thicknesses. To verify this approach Finite element method was used to determine the displacement, stress and strain field on Composite plates with Sandwich Cores. Two types of models were compared: The initial model where all the material components, plates and the core were modeled with their intrinsic properties and 'lumped' model with calculated effective elastic coefficients.",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Proračun efektivnog modula smicanja kompozitnih sendvič panela, Calculation of the effective shear modulus of composite sandwich panels",
pages = "542-537",
number = "4",
volume = "45",
doi = "10.5937/fmet1704537R"
}

Rebhi, L., Dinulović, M., Dunjić, M., Grbović, A.,& Krstić, B.. (2017). Proračun efektivnog modula smicanja kompozitnih sendvič panela. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 45(4), 537-542.
https://doi.org/10.5937/fmet1704537R

Rebhi L, Dinulović M, Dunjić M, Grbović A, Krstić B. Proračun efektivnog modula smicanja kompozitnih sendvič panela. in FME Transactions. 2017;45(4):537-542.
doi:10.5937/fmet1704537R .

Rebhi, Lamine, Dinulović, Mirko, Dunjić, Momčilo, Grbović, Aleksandar, Krstić, Branimir, "Proračun efektivnog modula smicanja kompozitnih sendvič panela" in FME Transactions, 45, no. 4 (2017):537-542,
https://doi.org/10.5937/fmet1704537R . .

TY  - JOUR
AU  - Marković, Zoran J.
AU  - Stupar, Slobodan
AU  - Dinulović, Mirko
AU  - Peković, Ognjen
AU  - Stefanović, Predrag Lj.
AU  - Cvetinović, Dejan
PY  - 2016
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2304
AB  - A fuzzy approximation concept is applied in order to predict results of coupled computational structure mechanics and computational fluid dynamics while solving a problem of steady incompressible gas flow through thermally loaded rectangular thin-walled channel. Channel wall deforms into wave-type shapes depending on thermal load and fluid inlet velocity inducing the changes of fluid flow accordingly. A set of fluid-structure interaction numerical tests have been defined by varying the values of fluid inlet velocity, temperature of inner and outer surface of the channel wall, and numerical grid density. The unsteady Navier-Stokes equations are numerically solved using an element-based finite volume method and second order backward Euler discretization scheme. The structural model is solved by finite element method including geometric and material non-linearities. The implicit two-way iterative code coupling, partitioned solution approach, were used while solving these numerical tests. Results of numerical analysis indicate that gravity and pressure distribution inside the channel contributes to triggering the shape of deformation. In the inverse problem, the results of fluid-structure interaction numerical simulations formed a database of input variables for development fuzzy logic based models considering downstream pressure drop and maximum stresses as the objective functions. Developed fuzzy models predicted targeting results within a reasonable accuracy limit at lower computation cost compared to series of fluid-structure interaction numerical calculations. Smaller relative difference were obtained when calculating the values of pressure drop then maximal stresses indicating that transfer function influence on output values have to be additionally investigated.
PB  - Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd
T2  - Thermal Science
T1  - Assessment results of fluid-structure interaction numerical simulation using fuzzy logic
EP  - S250
SP  - S235
VL  - 20
DO  - 10.2298/TSCI160111083M
ER  - 

@article{
author = "Marković, Zoran J. and Stupar, Slobodan and Dinulović, Mirko and Peković, Ognjen and Stefanović, Predrag Lj. and Cvetinović, Dejan",
year = "2016",
abstract = "A fuzzy approximation concept is applied in order to predict results of coupled computational structure mechanics and computational fluid dynamics while solving a problem of steady incompressible gas flow through thermally loaded rectangular thin-walled channel. Channel wall deforms into wave-type shapes depending on thermal load and fluid inlet velocity inducing the changes of fluid flow accordingly. A set of fluid-structure interaction numerical tests have been defined by varying the values of fluid inlet velocity, temperature of inner and outer surface of the channel wall, and numerical grid density. The unsteady Navier-Stokes equations are numerically solved using an element-based finite volume method and second order backward Euler discretization scheme. The structural model is solved by finite element method including geometric and material non-linearities. The implicit two-way iterative code coupling, partitioned solution approach, were used while solving these numerical tests. Results of numerical analysis indicate that gravity and pressure distribution inside the channel contributes to triggering the shape of deformation. In the inverse problem, the results of fluid-structure interaction numerical simulations formed a database of input variables for development fuzzy logic based models considering downstream pressure drop and maximum stresses as the objective functions. Developed fuzzy models predicted targeting results within a reasonable accuracy limit at lower computation cost compared to series of fluid-structure interaction numerical calculations. Smaller relative difference were obtained when calculating the values of pressure drop then maximal stresses indicating that transfer function influence on output values have to be additionally investigated.",
publisher = "Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd",
journal = "Thermal Science",
title = "Assessment results of fluid-structure interaction numerical simulation using fuzzy logic",
pages = "S250-S235",
volume = "20",
doi = "10.2298/TSCI160111083M"
}

Marković, Z. J., Stupar, S., Dinulović, M., Peković, O., Stefanović, P. Lj.,& Cvetinović, D.. (2016). Assessment results of fluid-structure interaction numerical simulation using fuzzy logic. in Thermal Science
Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd., 20, S235-S250.
https://doi.org/10.2298/TSCI160111083M

Marković ZJ, Stupar S, Dinulović M, Peković O, Stefanović PL, Cvetinović D. Assessment results of fluid-structure interaction numerical simulation using fuzzy logic. in Thermal Science. 2016;20:S235-S250.
doi:10.2298/TSCI160111083M .

Marković, Zoran J., Stupar, Slobodan, Dinulović, Mirko, Peković, Ognjen, Stefanović, Predrag Lj., Cvetinović, Dejan, "Assessment results of fluid-structure interaction numerical simulation using fuzzy logic" in Thermal Science, 20 (2016):S235-S250,
https://doi.org/10.2298/TSCI160111083M . .

TY  - JOUR
AU  - Rebhi, Lamine
AU  - Dinulović, Mirko
AU  - Andrić, Predrag
AU  - Dodić, Marjan
AU  - Krstić, Branimir
PY  - 2016
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2280
AB  - U radu je određen efektivni modul klizanja kompozitnog panela sa saćastom ispunom. Ovaj elastični koeficijent predstavlja veoma važnu karakteristiku kompozitnih panela, naročito kod kompozitnih konstrukcija koje su izložene uvijanju kao i kombinovanom uvijanju sa savijanjem. Analizirane strukture u ovom radu sastoje se od gornje i donje kompozitne ploče (različitih tipova karbonskih vlakana, T300, AS4 u epoksidnoj matrici) kao i saćaste ispune (HexWeb EC engineered core). Polazeći od klasične teorije lamine, efektivni modul elastičnosti klizanja je određen za svaki sloj u kompozitnoj ploči. Ovi slojevi su spojeni u jedinstveni kompozitni sloj za različita usmerenja vlakana kao i debljine lamina. Elastični koeficijenti saćaste ispune HexWeb središnjeg sloja kompozitnog panela su izračunati koristeći teoriju Master Evans u cilju dobijanja ekvivalentnih vrednosti. Za proveru predloženog pristupa korišćen je metod konačnih elemenata, u cilju dobijanja polja pomeranja, deformacija i napona u kompozitnim pločama i saćastoj ispuni. Dva tipa numeričkih modela su upoređena: početni model, pri čemu su svi slojevi ploče modelirani sa svojim karakteristikama i drugi model kod kojeg su spojeni u jednu celinu sa svojim ekvivalentnim karakteristikama. Zaključeno je da se ekvivalentni metod određivanja modula klizanja kompozitnih panela sa saćastim ispunama može efikasno primeniti u slučajevima kada su gornja i donja kompozitna ploča simetričnog slaganja ili uopšte kvaziizotropna.
AB  - In the presented paper the effective shear modulus of composite plates with honeycomb core is determined. This elastic coefficient represents one very important property, especially in constructions subjected to torsion and combined bending - torsion. The structures investigated in this research consisted of top and bottom plates (of different types of carbon fibers, T300, AS4 in epoxy matrix) and honeycomb core (HexWeb engineered core). Starting from classical lamination theory, the effective shear modulus of top and bottom plates was determined for each ply in the stack up sequence. These plies were 'lumped' into a single composite layer for different fiber orientations and plies thicknesses. Elastic coefficients for the HexWeb engineered core were obtained using Master and Evans relations for the equivalent properties of honeycomb cores. To verify this approach, finite element method was used to determine the displacement, stress and strain field on composite plates with honeycomb core. Two types of models were compared: the initial model where all the material components, plates and the core were modeled with their intrinsic properties and 'lumped' model with calculated effective elastic coefficients. It was found that the method of effective shear modulus calculation can successfully be used in situations where top and bottom plates are symmetric or quasi isotropic in general.
PB  - Vojnotehnički institut, Beograd
T2  - Scientific Technical Review
T1  - Efektivni modul klizanja kompozitnih panela sa saćastim ispunom
T1  - Ëffektivnyj modul' sdviga kompozitnyh sëndvič-panelej so sotovoj strukturoj / (francuski) Module de cisaillement effectif des panneaux composites en nid d'abeilles
T1  - On the effective shear modulus of composite honeycomb sandwich panels
EP  - 65
IS  - 4
SP  - 59
VL  - 66
DO  - 10.5937/STR1604059R
ER  - 

@article{
author = "Rebhi, Lamine and Dinulović, Mirko and Andrić, Predrag and Dodić, Marjan and Krstić, Branimir",
year = "2016",
abstract = "U radu je određen efektivni modul klizanja kompozitnog panela sa saćastom ispunom. Ovaj elastični koeficijent predstavlja veoma važnu karakteristiku kompozitnih panela, naročito kod kompozitnih konstrukcija koje su izložene uvijanju kao i kombinovanom uvijanju sa savijanjem. Analizirane strukture u ovom radu sastoje se od gornje i donje kompozitne ploče (različitih tipova karbonskih vlakana, T300, AS4 u epoksidnoj matrici) kao i saćaste ispune (HexWeb EC engineered core). Polazeći od klasične teorije lamine, efektivni modul elastičnosti klizanja je određen za svaki sloj u kompozitnoj ploči. Ovi slojevi su spojeni u jedinstveni kompozitni sloj za različita usmerenja vlakana kao i debljine lamina. Elastični koeficijenti saćaste ispune HexWeb središnjeg sloja kompozitnog panela su izračunati koristeći teoriju Master Evans u cilju dobijanja ekvivalentnih vrednosti. Za proveru predloženog pristupa korišćen je metod konačnih elemenata, u cilju dobijanja polja pomeranja, deformacija i napona u kompozitnim pločama i saćastoj ispuni. Dva tipa numeričkih modela su upoređena: početni model, pri čemu su svi slojevi ploče modelirani sa svojim karakteristikama i drugi model kod kojeg su spojeni u jednu celinu sa svojim ekvivalentnim karakteristikama. Zaključeno je da se ekvivalentni metod određivanja modula klizanja kompozitnih panela sa saćastim ispunama može efikasno primeniti u slučajevima kada su gornja i donja kompozitna ploča simetričnog slaganja ili uopšte kvaziizotropna., In the presented paper the effective shear modulus of composite plates with honeycomb core is determined. This elastic coefficient represents one very important property, especially in constructions subjected to torsion and combined bending - torsion. The structures investigated in this research consisted of top and bottom plates (of different types of carbon fibers, T300, AS4 in epoxy matrix) and honeycomb core (HexWeb engineered core). Starting from classical lamination theory, the effective shear modulus of top and bottom plates was determined for each ply in the stack up sequence. These plies were 'lumped' into a single composite layer for different fiber orientations and plies thicknesses. Elastic coefficients for the HexWeb engineered core were obtained using Master and Evans relations for the equivalent properties of honeycomb cores. To verify this approach, finite element method was used to determine the displacement, stress and strain field on composite plates with honeycomb core. Two types of models were compared: the initial model where all the material components, plates and the core were modeled with their intrinsic properties and 'lumped' model with calculated effective elastic coefficients. It was found that the method of effective shear modulus calculation can successfully be used in situations where top and bottom plates are symmetric or quasi isotropic in general.",
publisher = "Vojnotehnički institut, Beograd",
journal = "Scientific Technical Review",
title = "Efektivni modul klizanja kompozitnih panela sa saćastim ispunom, Ëffektivnyj modul' sdviga kompozitnyh sëndvič-panelej so sotovoj strukturoj / (francuski) Module de cisaillement effectif des panneaux composites en nid d'abeilles, On the effective shear modulus of composite honeycomb sandwich panels",
pages = "65-59",
number = "4",
volume = "66",
doi = "10.5937/STR1604059R"
}

Rebhi, L., Dinulović, M., Andrić, P., Dodić, M.,& Krstić, B.. (2016). Efektivni modul klizanja kompozitnih panela sa saćastim ispunom. in Scientific Technical Review
Vojnotehnički institut, Beograd., 66(4), 59-65.
https://doi.org/10.5937/STR1604059R

Rebhi L, Dinulović M, Andrić P, Dodić M, Krstić B. Efektivni modul klizanja kompozitnih panela sa saćastim ispunom. in Scientific Technical Review. 2016;66(4):59-65.
doi:10.5937/STR1604059R .

Rebhi, Lamine, Dinulović, Mirko, Andrić, Predrag, Dodić, Marjan, Krstić, Branimir, "Efektivni modul klizanja kompozitnih panela sa saćastim ispunom" in Scientific Technical Review, 66, no. 4 (2016):59-65,
https://doi.org/10.5937/STR1604059R . .

TY  - JOUR
AU  - Krstić, Branimir
AU  - Rebhi, Lamine
AU  - Ilić, Nada
AU  - Dodić, Marjan
AU  - Dinulović, Mirko
AU  - Andrić, Predrag
AU  - Trifković, Dragan
PY  - 2016
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2451
AB  - The mounting bolt of helicopter main gearbox support strut was fractured into two pieces during the flight mission. The fracture occurred at the root of the first engaged thread of the bolt-nut assembly. Visual inspection of the fracture zone revealed cracks, formed by interlinking of corrosion pits, at the almost all thread roots of the bolt. Energy dispersive spectroscopy disclosed significant damage of the cadmium plating as well as the presence of large amounts of corrosion products at the bolt threads. Through the fractography and metallography analysis, it was found that the mounting bolt failed due to hydrogen-induced intergranular stress corrosion cracking (HI-IGSCC). The finite element (FE) analysis confirmed that the crack origin was located at the area with the maximum tensile stress in the bolt.
PB  - Pergamon-Elsevier Science Ltd, Oxford
T2  - Engineering Failure Analysis
T1  - Failure of mounting bolt of helicopter main gearbox support strut
EP  - 363
SP  - 351
VL  - 70
DO  - 10.1016/j.engfailanal.2016.09.012
ER  - 

@article{
author = "Krstić, Branimir and Rebhi, Lamine and Ilić, Nada and Dodić, Marjan and Dinulović, Mirko and Andrić, Predrag and Trifković, Dragan",
year = "2016",
abstract = "The mounting bolt of helicopter main gearbox support strut was fractured into two pieces during the flight mission. The fracture occurred at the root of the first engaged thread of the bolt-nut assembly. Visual inspection of the fracture zone revealed cracks, formed by interlinking of corrosion pits, at the almost all thread roots of the bolt. Energy dispersive spectroscopy disclosed significant damage of the cadmium plating as well as the presence of large amounts of corrosion products at the bolt threads. Through the fractography and metallography analysis, it was found that the mounting bolt failed due to hydrogen-induced intergranular stress corrosion cracking (HI-IGSCC). The finite element (FE) analysis confirmed that the crack origin was located at the area with the maximum tensile stress in the bolt.",
publisher = "Pergamon-Elsevier Science Ltd, Oxford",
journal = "Engineering Failure Analysis",
title = "Failure of mounting bolt of helicopter main gearbox support strut",
pages = "363-351",
volume = "70",
doi = "10.1016/j.engfailanal.2016.09.012"
}

Krstić, B., Rebhi, L., Ilić, N., Dodić, M., Dinulović, M., Andrić, P.,& Trifković, D.. (2016). Failure of mounting bolt of helicopter main gearbox support strut. in Engineering Failure Analysis
Pergamon-Elsevier Science Ltd, Oxford., 70, 351-363.
https://doi.org/10.1016/j.engfailanal.2016.09.012

Krstić B, Rebhi L, Ilić N, Dodić M, Dinulović M, Andrić P, Trifković D. Failure of mounting bolt of helicopter main gearbox support strut. in Engineering Failure Analysis. 2016;70:351-363.
doi:10.1016/j.engfailanal.2016.09.012 .

Krstić, Branimir, Rebhi, Lamine, Ilić, Nada, Dodić, Marjan, Dinulović, Mirko, Andrić, Predrag, Trifković, Dragan, "Failure of mounting bolt of helicopter main gearbox support strut" in Engineering Failure Analysis, 70 (2016):351-363,
https://doi.org/10.1016/j.engfailanal.2016.09.012 . .

TY  - CHAP
AU  - Krstić, B.
AU  - Rašuo, Boško
AU  - Trifković, Dragan
AU  - Radisavljević, Igor
AU  - Rajić, Zoran
AU  - Dinulović, Mirko
PY  - 2016
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2378
AB  - Aircrafts powered by piston engine represent the bulk of the fixed wing fleet. Large majorities of these aircrafts are equipped with single, air-cooled, and horizontally opposed, piston engines. The mechanical failure in any of the piston engine components, especially concerning fatigue failure of the cylinder head (CH) made of an aluminum-casting alloy may have serious or fatal consequences to the safety of the crew and the aircraft. Therefore, the aim of this study is to identify the root cause(s) of repetitive premature failures in an aircraft engine CH.Two piston engines of the training aircraft Utva-75 have malfunctioned during the flight mission due to the fatigue cracking of their aluminum cast CHs. Visual inspection revealed that transverse cracking had occurred between the fifth and the sixth deep integral cooling fins. Based on the fractographic analysis, observation of the characteristic ratchet and beach marks indicated the occurrence of fatigue failure. The crack initiated from multiple origins located on the inner flange fillet on the exhaust side of the CHs. The metallographic examination revealed that the fatigue was promoted from pre-existing material defect due to a high concentration of shrinkage pores at the initiation crack site and can be most likely associated with the manufacturing process of casting. The finite element method, utilized to determine the stress state of the cylinder assembly, also confirmed that the crack origin was located at the most stressed area of the cylinder assembly, i.e., on the inner flange fillet of the exhaust side of the CH.
PB  - Elsevier Inc.
T2  - Handbook of Materials Failure Analysis with Case Studies from the Aerospace and Automotive Industrie
T1  - Fatigue as a cause of failure of aircraft engine cylinder head
EP  - 214
SP  - 191
DO  - 10.1016/B978-0-12-800950-5.00009-0
ER  - 

@inbook{
author = "Krstić, B. and Rašuo, Boško and Trifković, Dragan and Radisavljević, Igor and Rajić, Zoran and Dinulović, Mirko",
year = "2016",
abstract = "Aircrafts powered by piston engine represent the bulk of the fixed wing fleet. Large majorities of these aircrafts are equipped with single, air-cooled, and horizontally opposed, piston engines. The mechanical failure in any of the piston engine components, especially concerning fatigue failure of the cylinder head (CH) made of an aluminum-casting alloy may have serious or fatal consequences to the safety of the crew and the aircraft. Therefore, the aim of this study is to identify the root cause(s) of repetitive premature failures in an aircraft engine CH.Two piston engines of the training aircraft Utva-75 have malfunctioned during the flight mission due to the fatigue cracking of their aluminum cast CHs. Visual inspection revealed that transverse cracking had occurred between the fifth and the sixth deep integral cooling fins. Based on the fractographic analysis, observation of the characteristic ratchet and beach marks indicated the occurrence of fatigue failure. The crack initiated from multiple origins located on the inner flange fillet on the exhaust side of the CHs. The metallographic examination revealed that the fatigue was promoted from pre-existing material defect due to a high concentration of shrinkage pores at the initiation crack site and can be most likely associated with the manufacturing process of casting. The finite element method, utilized to determine the stress state of the cylinder assembly, also confirmed that the crack origin was located at the most stressed area of the cylinder assembly, i.e., on the inner flange fillet of the exhaust side of the CH.",
publisher = "Elsevier Inc.",
journal = "Handbook of Materials Failure Analysis with Case Studies from the Aerospace and Automotive Industrie",
booktitle = "Fatigue as a cause of failure of aircraft engine cylinder head",
pages = "214-191",
doi = "10.1016/B978-0-12-800950-5.00009-0"
}

Krstić, B., Rašuo, B., Trifković, D., Radisavljević, I., Rajić, Z.,& Dinulović, M.. (2016). Fatigue as a cause of failure of aircraft engine cylinder head. in Handbook of Materials Failure Analysis with Case Studies from the Aerospace and Automotive Industrie
Elsevier Inc.., 191-214.
https://doi.org/10.1016/B978-0-12-800950-5.00009-0

Krstić B, Rašuo B, Trifković D, Radisavljević I, Rajić Z, Dinulović M. Fatigue as a cause of failure of aircraft engine cylinder head. in Handbook of Materials Failure Analysis with Case Studies from the Aerospace and Automotive Industrie. 2016;:191-214.
doi:10.1016/B978-0-12-800950-5.00009-0 .

Krstić, B., Rašuo, Boško, Trifković, Dragan, Radisavljević, Igor, Rajić, Zoran, Dinulović, Mirko, "Fatigue as a cause of failure of aircraft engine cylinder head" in Handbook of Materials Failure Analysis with Case Studies from the Aerospace and Automotive Industrie (2016):191-214,
https://doi.org/10.1016/B978-0-12-800950-5.00009-0 . .

TY  - CONF
AU  - Dinulović, Mirko
AU  - Rašuo, Boško
AU  - Krstić, B.
PY  - 2016
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2367
AB  - This paper presents an analytical study on the effect of laminate lay-up of composite missile stabilizer structure for achieving a maximum flutter speed without strength penalty. The flexible stabilizer structure in high-velocity flow may experience flutter, an aeroelastic phenomena where vibrations of the structure become unstable and can cause stability loss and flight vehicle failure. Flutter in missiles is mainly affected by the aerodynamic and structural properties of the stabilizers whereas flight vehicle body has a minor role. In the present paper the effect of laminate lay-up on flutter speed of composite missile stabilizers is investigated. Two degrees of freedom (plunge and twist) analytical model of typical fin stabilizer airfoil section is presented. Based on this model the critical flutter speed for the composite missile stabilizer is derived for subsonic flight conditions. It was found that natural stabilizer frequencies (in bending and twisting) highly influence the maximum flutter speed. Natural fin frequencies (in bending and twisting) are calculated using finite element approach based on Lanczos method of frequencies extraction. Several modal frequency models are investigated and results are discussed, since the accurate prediction of natural frequencies plays significant role in overall flutter speed (VF) determination. For the trapezoidal stabilizer shape different laminate lay-up sequences are investigated, flutter speeds calculated and results compared in order to determine maximum flutter speed. The material of interest in this study was carbon based AS/4-3501-6.
PB  - International Council of the Aeronautical Sciences
C3  - 30th Congress of the International Council of the Aeronautical Sciences, ICAS 2016
T1  - The analysis of laminate lay-up effect on the flutter speed of composite stabilizers
UR  - https://hdl.handle.net/21.15107/rcub_machinery_2367
ER  - 

@conference{
author = "Dinulović, Mirko and Rašuo, Boško and Krstić, B.",
year = "2016",
abstract = "This paper presents an analytical study on the effect of laminate lay-up of composite missile stabilizer structure for achieving a maximum flutter speed without strength penalty. The flexible stabilizer structure in high-velocity flow may experience flutter, an aeroelastic phenomena where vibrations of the structure become unstable and can cause stability loss and flight vehicle failure. Flutter in missiles is mainly affected by the aerodynamic and structural properties of the stabilizers whereas flight vehicle body has a minor role. In the present paper the effect of laminate lay-up on flutter speed of composite missile stabilizers is investigated. Two degrees of freedom (plunge and twist) analytical model of typical fin stabilizer airfoil section is presented. Based on this model the critical flutter speed for the composite missile stabilizer is derived for subsonic flight conditions. It was found that natural stabilizer frequencies (in bending and twisting) highly influence the maximum flutter speed. Natural fin frequencies (in bending and twisting) are calculated using finite element approach based on Lanczos method of frequencies extraction. Several modal frequency models are investigated and results are discussed, since the accurate prediction of natural frequencies plays significant role in overall flutter speed (VF) determination. For the trapezoidal stabilizer shape different laminate lay-up sequences are investigated, flutter speeds calculated and results compared in order to determine maximum flutter speed. The material of interest in this study was carbon based AS/4-3501-6.",
publisher = "International Council of the Aeronautical Sciences",
journal = "30th Congress of the International Council of the Aeronautical Sciences, ICAS 2016",
title = "The analysis of laminate lay-up effect on the flutter speed of composite stabilizers",
url = "https://hdl.handle.net/21.15107/rcub_machinery_2367"
}

Dinulović, M., Rašuo, B.,& Krstić, B.. (2016). The analysis of laminate lay-up effect on the flutter speed of composite stabilizers. in 30th Congress of the International Council of the Aeronautical Sciences, ICAS 2016
International Council of the Aeronautical Sciences..
https://hdl.handle.net/21.15107/rcub_machinery_2367

Dinulović M, Rašuo B, Krstić B. The analysis of laminate lay-up effect on the flutter speed of composite stabilizers. in 30th Congress of the International Council of the Aeronautical Sciences, ICAS 2016. 2016;.
https://hdl.handle.net/21.15107/rcub_machinery_2367 .

Dinulović, Mirko, Rašuo, Boško, Krstić, B., "The analysis of laminate lay-up effect on the flutter speed of composite stabilizers" in 30th Congress of the International Council of the Aeronautical Sciences, ICAS 2016 (2016),
https://hdl.handle.net/21.15107/rcub_machinery_2367 .

TY  - JOUR
AU  - Marković, Zoran
AU  - Stupar, Slobodan
AU  - Dinulović, Mirko
AU  - Stefanović, Predrag Lj.
AU  - Cvetinović, Dejan
PY  - 2015
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2069
AB  - U radu su prikazani rezultati numeričkih proračuna interakcije fluid-struktura korišćenjem diskretizacionih numeričkih metoda - metode konačnih elemenata za proračun naponsko-deformacionog stanja zida kanala i metode konačnih zapremina za numerički proračun dinamike fluida. Na osnovu dobijenih rezultata razvijen je fazi ekspertski sistem za procenu izlaznih parametara numeričkog proračuna, prikazane su osnovne karakteristike razvijenog fazi modela i rezultati dobijeni njegovom primenom. Analizirani su uticaji tri ulazna parametra - temperature unutrašnje površine zida kanala, razlike između temperatura unutrašnje i spoljašnje površine zida i faktora koji definiše gustinu numeričkih mreža - na dva izlazna parametra: vrednost pada statičkog pritiska niz struju i vrednost maksimalnih kombinovanih Fon Misesovih napona ostvarenih u strukturi kanala za zadate uslove opterećenja. Na osnovu dobijenih rezultata vidimo da formirani fazi ekspertski sistem može sa zadovoljavajućom tačnošću biti iskorišćen za procenu posmatranih izlaznih veličina, pri znatno kraćem vremenu potrebnom za proračun i uz angažovanje resursa računarskog sistema u značajno manjem obimu.
AB  - This paper deal with structural deformation of one rectangular, closed, thin walled, steel made, thermally loaded channel and influence of this deformation on the air flow through the channel, recognised as coupled fluid-structure interaction problem. The geometrically non-linear deformation of thermally loaded channel was solved using commercial finite-element analysis software ANSYS. The unsteady Navier-Stokes equations in their conservation form defining fluid flow are solved using commercial computer fluid dynamics software ANSYS CFX. A fuzzy logic-based expert system has been developed to predict some results of structural and fluid flow numerical simulation instead of directly evaluating it by a time-consuming software coupling of finite-element and computer fluid dynamics numerical analysis. Three input parameters, namely temperature of channel inner walls, difference in temperature of inner and outer surface of channel wall, and factor of mesh size, are varied while solving the fluid-structure interaction problem. A pressure drop downstream the flow was considered as a computer fluid dynamics output parameter of importance, while Von Misses maximum stresses were an finite-element analysis output parameter observed. The developed FLES can predict the results of finite-element and computer fluid dynamics analysis, a pressure drop and Von Misses maximum stresses respectively, within a reasonable accuracy limit and at lower computation cost compared to the finite-element, and CFD computer fluid dynamics packages combined into series of multi-physics analyses.
PB  - Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd i Društvo termičara Srbije, Beograd
T2  - Termotehnika
T1  - Fazi ekspertski sistem za proračun parametara spregnute numeričke analize interakcije fluida i tankozidne strukture
T1  - Fuzzy logic expert system for calculating the parameters of coupled numerical analysis of the fluid and thin-walled structures interaction
EP  - 48
IS  - 1
SP  - 33
VL  - 41
DO  - 10.5937/termoteh1501033M
ER  - 

@article{
author = "Marković, Zoran and Stupar, Slobodan and Dinulović, Mirko and Stefanović, Predrag Lj. and Cvetinović, Dejan",
year = "2015",
abstract = "U radu su prikazani rezultati numeričkih proračuna interakcije fluid-struktura korišćenjem diskretizacionih numeričkih metoda - metode konačnih elemenata za proračun naponsko-deformacionog stanja zida kanala i metode konačnih zapremina za numerički proračun dinamike fluida. Na osnovu dobijenih rezultata razvijen je fazi ekspertski sistem za procenu izlaznih parametara numeričkog proračuna, prikazane su osnovne karakteristike razvijenog fazi modela i rezultati dobijeni njegovom primenom. Analizirani su uticaji tri ulazna parametra - temperature unutrašnje površine zida kanala, razlike između temperatura unutrašnje i spoljašnje površine zida i faktora koji definiše gustinu numeričkih mreža - na dva izlazna parametra: vrednost pada statičkog pritiska niz struju i vrednost maksimalnih kombinovanih Fon Misesovih napona ostvarenih u strukturi kanala za zadate uslove opterećenja. Na osnovu dobijenih rezultata vidimo da formirani fazi ekspertski sistem može sa zadovoljavajućom tačnošću biti iskorišćen za procenu posmatranih izlaznih veličina, pri znatno kraćem vremenu potrebnom za proračun i uz angažovanje resursa računarskog sistema u značajno manjem obimu., This paper deal with structural deformation of one rectangular, closed, thin walled, steel made, thermally loaded channel and influence of this deformation on the air flow through the channel, recognised as coupled fluid-structure interaction problem. The geometrically non-linear deformation of thermally loaded channel was solved using commercial finite-element analysis software ANSYS. The unsteady Navier-Stokes equations in their conservation form defining fluid flow are solved using commercial computer fluid dynamics software ANSYS CFX. A fuzzy logic-based expert system has been developed to predict some results of structural and fluid flow numerical simulation instead of directly evaluating it by a time-consuming software coupling of finite-element and computer fluid dynamics numerical analysis. Three input parameters, namely temperature of channel inner walls, difference in temperature of inner and outer surface of channel wall, and factor of mesh size, are varied while solving the fluid-structure interaction problem. A pressure drop downstream the flow was considered as a computer fluid dynamics output parameter of importance, while Von Misses maximum stresses were an finite-element analysis output parameter observed. The developed FLES can predict the results of finite-element and computer fluid dynamics analysis, a pressure drop and Von Misses maximum stresses respectively, within a reasonable accuracy limit and at lower computation cost compared to the finite-element, and CFD computer fluid dynamics packages combined into series of multi-physics analyses.",
publisher = "Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd i Društvo termičara Srbije, Beograd",
journal = "Termotehnika",
title = "Fazi ekspertski sistem za proračun parametara spregnute numeričke analize interakcije fluida i tankozidne strukture, Fuzzy logic expert system for calculating the parameters of coupled numerical analysis of the fluid and thin-walled structures interaction",
pages = "48-33",
number = "1",
volume = "41",
doi = "10.5937/termoteh1501033M"
}

Marković, Z., Stupar, S., Dinulović, M., Stefanović, P. Lj.,& Cvetinović, D.. (2015). Fazi ekspertski sistem za proračun parametara spregnute numeričke analize interakcije fluida i tankozidne strukture. in Termotehnika
Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd i Društvo termičara Srbije, Beograd., 41(1), 33-48.
https://doi.org/10.5937/termoteh1501033M

Marković Z, Stupar S, Dinulović M, Stefanović PL, Cvetinović D. Fazi ekspertski sistem za proračun parametara spregnute numeričke analize interakcije fluida i tankozidne strukture. in Termotehnika. 2015;41(1):33-48.
doi:10.5937/termoteh1501033M .

Marković, Zoran, Stupar, Slobodan, Dinulović, Mirko, Stefanović, Predrag Lj., Cvetinović, Dejan, "Fazi ekspertski sistem za proračun parametara spregnute numeričke analize interakcije fluida i tankozidne strukture" in Termotehnika, 41, no. 1 (2015):33-48,
https://doi.org/10.5937/termoteh1501033M . .

TY  - JOUR
AU  - Krstić, Branimir
AU  - Rašuo, Boško
AU  - Trifković, Dragan
AU  - Radisavljević, Igor
AU  - Rajić, Zoran
AU  - Dinulović, Mirko
PY  - 2015
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2078
AB  - Tokom leta školskog aviona Utva-75 došlo je do otkaza motora usled pucanja glave cilindra. Nakon uspešno izvršenog prinudnog sletanja oštećeni sklop cilindra je demontiran sa motora aviona i poslat na forenzičku ekspertizu. Fraktografskim ispitivanjem prelomne površine utvrđeno je da je uzrok otkaza zamor materijala glave cilindra. Metalografska ispitivanja pokazala su da je uzrok nastanka zamorne prsline postojanje značajne poroznosti materijala upravo u zoni nastanka loma. Numerička simulacija naponskog stanja sklopa cilindra, izvršena metodom konačnih elemenata, potvrdila je pretpostavku da je lom iniciran u zoni najveće koncentracije napona.
AB  - The piston engine of the training aircraft Utva-75 malfunctioned during the flight mission due to the cracking of its cylinder head. After successful forced landing, the damaged cylinder assembly was removed from the engine and sent to the lab for forensic expertise. Fractographic examination of the mating fracture surfaces revealed that the fatigue was the main cause of the cylinder head failure. The metallography examination has shown that the fatigue was promoted from pre-existing material defect due to an elevated presence of porosity forms at the crack initiation zone. The finite element method, utilized to determine the stress state of the cylinder assembly, confirmed that the crack origin was located at the most stress area.
PB  - Savez inženjera i tehničara Srbije, Beograd
T2  - Tehnika
T1  - Ispitivanje uzroka mehaničkog otkaza glave cilindra avionskog klipnog motora
T1  - Investigation of mechanical failure cause of an aircraft piston engine cylinder head
EP  - 80
IS  - 1
SP  - 71
VL  - 70
DO  - 10.5937/tehnika1501071K
ER  - 

@article{
author = "Krstić, Branimir and Rašuo, Boško and Trifković, Dragan and Radisavljević, Igor and Rajić, Zoran and Dinulović, Mirko",
year = "2015",
abstract = "Tokom leta školskog aviona Utva-75 došlo je do otkaza motora usled pucanja glave cilindra. Nakon uspešno izvršenog prinudnog sletanja oštećeni sklop cilindra je demontiran sa motora aviona i poslat na forenzičku ekspertizu. Fraktografskim ispitivanjem prelomne površine utvrđeno je da je uzrok otkaza zamor materijala glave cilindra. Metalografska ispitivanja pokazala su da je uzrok nastanka zamorne prsline postojanje značajne poroznosti materijala upravo u zoni nastanka loma. Numerička simulacija naponskog stanja sklopa cilindra, izvršena metodom konačnih elemenata, potvrdila je pretpostavku da je lom iniciran u zoni najveće koncentracije napona., The piston engine of the training aircraft Utva-75 malfunctioned during the flight mission due to the cracking of its cylinder head. After successful forced landing, the damaged cylinder assembly was removed from the engine and sent to the lab for forensic expertise. Fractographic examination of the mating fracture surfaces revealed that the fatigue was the main cause of the cylinder head failure. The metallography examination has shown that the fatigue was promoted from pre-existing material defect due to an elevated presence of porosity forms at the crack initiation zone. The finite element method, utilized to determine the stress state of the cylinder assembly, confirmed that the crack origin was located at the most stress area.",
publisher = "Savez inženjera i tehničara Srbije, Beograd",
journal = "Tehnika",
title = "Ispitivanje uzroka mehaničkog otkaza glave cilindra avionskog klipnog motora, Investigation of mechanical failure cause of an aircraft piston engine cylinder head",
pages = "80-71",
number = "1",
volume = "70",
doi = "10.5937/tehnika1501071K"
}

Krstić, B., Rašuo, B., Trifković, D., Radisavljević, I., Rajić, Z.,& Dinulović, M.. (2015). Ispitivanje uzroka mehaničkog otkaza glave cilindra avionskog klipnog motora. in Tehnika
Savez inženjera i tehničara Srbije, Beograd., 70(1), 71-80.
https://doi.org/10.5937/tehnika1501071K

Krstić B, Rašuo B, Trifković D, Radisavljević I, Rajić Z, Dinulović M. Ispitivanje uzroka mehaničkog otkaza glave cilindra avionskog klipnog motora. in Tehnika. 2015;70(1):71-80.
doi:10.5937/tehnika1501071K .

Krstić, Branimir, Rašuo, Boško, Trifković, Dragan, Radisavljević, Igor, Rajić, Zoran, Dinulović, Mirko, "Ispitivanje uzroka mehaničkog otkaza glave cilindra avionskog klipnog motora" in Tehnika, 70, no. 1 (2015):71-80,
https://doi.org/10.5937/tehnika1501071K . .

TY  - JOUR
AU  - Janićijević, Milovan
AU  - Srećković, Milesa
AU  - Kaluđerović, Branka
AU  - Dinulović, Mirko
AU  - Karastojković, Zoran
AU  - Jovanić, Predrag
AU  - Kovačević, Zorica
PY  - 2015
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2141
AB  - U ovom radu se analizira interakcija laserskih snopova sa ugljeničnim materijalom (staklasti ugljenik). Korišćen je Nd3+:YAG lasera (1.06 μm, odnosno bliska IC oblast) u ms režimu rada sa snopovima različitih gustina energije. U svim eksperimentima, u primenjenom režimu rada, uočene su površinske povrede na uzorku. Povrede nastale dejstvom lasera su analizirane optičkim i SEM mikroskopima. Program Image J je korišćen za kvantitativnu analizu nastalih povreda na osnovu mikrografa dobijenih optičkom i SEM mikroskopijom. Temperaturna raspodela u izloženom uzorku je dobijena numeričkom simulacijom zasnovanom na programskom paketu COMSOL Multiphysics 3.5 u ograničenom opsegu energija.
AB  - Laser beam interaction with carbon based material (glassy carbon) is analyzed in this paper. A Nd3+:YAG laser beam (1.06 μm, i.e., near infrared range (NIR)) in ms regime with various energy densities is used. In all experiments, provided in applied working regimes, surface damages have occurred. The results of laser damages are analyzed by light and scanning electron microscopy (SEM). Image J software is used for quantitative analysis of generated damages based on micrographs obtained by light and SEM microscopes. Temperature distribution in the exposed samples is evaluated by numerical simulations based on COMSOL Multiphysics 3.5 software in a limited energy range.
PB  - Savez hemijskih inženjera, Beograd
T2  - Chemical Industry & Chemical Engineering Quarterly
T1  - Procena interakcije laserskog snopa sa materijalom na bazi ugljenika - staklastim ugljenikom
T1  - Evaluation of laser beam interaction with carbon based material: Glassy carbon
EP  - 69
IS  - 1
SP  - 63
VL  - 21
DO  - 10.2298/CICEQ140131006J
ER  - 

@article{
author = "Janićijević, Milovan and Srećković, Milesa and Kaluđerović, Branka and Dinulović, Mirko and Karastojković, Zoran and Jovanić, Predrag and Kovačević, Zorica",
year = "2015",
abstract = "U ovom radu se analizira interakcija laserskih snopova sa ugljeničnim materijalom (staklasti ugljenik). Korišćen je Nd3+:YAG lasera (1.06 μm, odnosno bliska IC oblast) u ms režimu rada sa snopovima različitih gustina energije. U svim eksperimentima, u primenjenom režimu rada, uočene su površinske povrede na uzorku. Povrede nastale dejstvom lasera su analizirane optičkim i SEM mikroskopima. Program Image J je korišćen za kvantitativnu analizu nastalih povreda na osnovu mikrografa dobijenih optičkom i SEM mikroskopijom. Temperaturna raspodela u izloženom uzorku je dobijena numeričkom simulacijom zasnovanom na programskom paketu COMSOL Multiphysics 3.5 u ograničenom opsegu energija., Laser beam interaction with carbon based material (glassy carbon) is analyzed in this paper. A Nd3+:YAG laser beam (1.06 μm, i.e., near infrared range (NIR)) in ms regime with various energy densities is used. In all experiments, provided in applied working regimes, surface damages have occurred. The results of laser damages are analyzed by light and scanning electron microscopy (SEM). Image J software is used for quantitative analysis of generated damages based on micrographs obtained by light and SEM microscopes. Temperature distribution in the exposed samples is evaluated by numerical simulations based on COMSOL Multiphysics 3.5 software in a limited energy range.",
publisher = "Savez hemijskih inženjera, Beograd",
journal = "Chemical Industry & Chemical Engineering Quarterly",
title = "Procena interakcije laserskog snopa sa materijalom na bazi ugljenika - staklastim ugljenikom, Evaluation of laser beam interaction with carbon based material: Glassy carbon",
pages = "69-63",
number = "1",
volume = "21",
doi = "10.2298/CICEQ140131006J"
}

Janićijević, M., Srećković, M., Kaluđerović, B., Dinulović, M., Karastojković, Z., Jovanić, P.,& Kovačević, Z.. (2015). Procena interakcije laserskog snopa sa materijalom na bazi ugljenika - staklastim ugljenikom. in Chemical Industry & Chemical Engineering Quarterly
Savez hemijskih inženjera, Beograd., 21(1), 63-69.
https://doi.org/10.2298/CICEQ140131006J

Janićijević M, Srećković M, Kaluđerović B, Dinulović M, Karastojković Z, Jovanić P, Kovačević Z. Procena interakcije laserskog snopa sa materijalom na bazi ugljenika - staklastim ugljenikom. in Chemical Industry & Chemical Engineering Quarterly. 2015;21(1):63-69.
doi:10.2298/CICEQ140131006J .

Janićijević, Milovan, Srećković, Milesa, Kaluđerović, Branka, Dinulović, Mirko, Karastojković, Zoran, Jovanić, Predrag, Kovačević, Zorica, "Procena interakcije laserskog snopa sa materijalom na bazi ugljenika - staklastim ugljenikom" in Chemical Industry & Chemical Engineering Quarterly, 21, no. 1 (2015):63-69,
https://doi.org/10.2298/CICEQ140131006J . .

TY  - JOUR
AU  - Rašuo, Boško
AU  - Dinulović, Mirko
AU  - Veg, Aleksandar
AU  - Grbović, Aleksandar
AU  - Bengin, Aleksandar
PY  - 2014
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1925
AB  - In this paper the harmonization of new wind turbine rotor blades development is given as well as the analysis of behavior by verification testing for a wind turbine rotor blade of composite materials. The design, fabrication, the status of wind energy standards and the analysis of behavior by full-scale verification testing for wind turbine rotor blades of composite laminated materials is given, too. The experimental methodology of static, vibratory and fatigue tests for the wind turbine rotor blade of composite laminated materials is presented. These verification tests were performed after the rotor blade development had been completed. The development of the rotor blade was performed using the PC computer with the CATIA designing system and the Gerber Garment cutter system. The blade was fabricated from composite laminated materials. The contour of airfoil was formed by a continuous structural pocket and a fiberglass skin.
PB  - Pergamon-Elsevier Science Ltd, Oxford
T2  - Renewable & Sustainable Energy Reviews
T1  - Harmonization of new wind turbine rotor blades development process: A review
EP  - 882
SP  - 874
VL  - 39
DO  - 10.1016/j.rser.2014.07.137
ER  - 

@article{
author = "Rašuo, Boško and Dinulović, Mirko and Veg, Aleksandar and Grbović, Aleksandar and Bengin, Aleksandar",
year = "2014",
abstract = "In this paper the harmonization of new wind turbine rotor blades development is given as well as the analysis of behavior by verification testing for a wind turbine rotor blade of composite materials. The design, fabrication, the status of wind energy standards and the analysis of behavior by full-scale verification testing for wind turbine rotor blades of composite laminated materials is given, too. The experimental methodology of static, vibratory and fatigue tests for the wind turbine rotor blade of composite laminated materials is presented. These verification tests were performed after the rotor blade development had been completed. The development of the rotor blade was performed using the PC computer with the CATIA designing system and the Gerber Garment cutter system. The blade was fabricated from composite laminated materials. The contour of airfoil was formed by a continuous structural pocket and a fiberglass skin.",
publisher = "Pergamon-Elsevier Science Ltd, Oxford",
journal = "Renewable & Sustainable Energy Reviews",
title = "Harmonization of new wind turbine rotor blades development process: A review",
pages = "882-874",
volume = "39",
doi = "10.1016/j.rser.2014.07.137"
}

Rašuo, B., Dinulović, M., Veg, A., Grbović, A.,& Bengin, A.. (2014). Harmonization of new wind turbine rotor blades development process: A review. in Renewable & Sustainable Energy Reviews
Pergamon-Elsevier Science Ltd, Oxford., 39, 874-882.
https://doi.org/10.1016/j.rser.2014.07.137

Rašuo B, Dinulović M, Veg A, Grbović A, Bengin A. Harmonization of new wind turbine rotor blades development process: A review. in Renewable & Sustainable Energy Reviews. 2014;39:874-882.
doi:10.1016/j.rser.2014.07.137 .

Rašuo, Boško, Dinulović, Mirko, Veg, Aleksandar, Grbović, Aleksandar, Bengin, Aleksandar, "Harmonization of new wind turbine rotor blades development process: A review" in Renewable & Sustainable Energy Reviews, 39 (2014):874-882,
https://doi.org/10.1016/j.rser.2014.07.137 . .

TY  - JOUR
AU  - Ilić, Zoran
AU  - Rašuo, Boško
AU  - Jovanović, Miroslav
AU  - Pekmezović, Sladjan
AU  - Bengin, Aleksandar
AU  - Dinulović, Mirko
PY  - 2014
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1959
AB  - Improving aircraft pilot comfort requires continuous work in decreasing vibrations in the seat. In order to determine the suitability and potential of cockpit floor - seat connections we conducted an experiment where measurements were taken and seat vibration analysis conducted. Vibrations parameters were measured for maximum engine and propeller speed. This analysis indicates that passive vibrations damping or cockpit floor - seat connections functionality depends on flights profile and vibrations frequency. The connection in question was behaving like a vibration multiplier on the 3rd and 4th harmonic as well as on the 3,5 sub-harmonic in individual flight modes on basic propeller rotation frequency, however, it behaved as a vibration silencer on all other frequencies. Analysis of the experimental data has shown that it would be justified to start improving the self adaptive unit for active vibration reduction for pilot seats.
PB  - Strojarski Facultet
T2  - Tehnički vjesnik
T1  - Potential connections of cockpit floor-seat on passive vibration reduction at a piston propelled airplane
EP  - 478
IS  - 3
SP  - 471
VL  - 21
UR  - https://hdl.handle.net/21.15107/rcub_machinery_1959
ER  - 

@article{
author = "Ilić, Zoran and Rašuo, Boško and Jovanović, Miroslav and Pekmezović, Sladjan and Bengin, Aleksandar and Dinulović, Mirko",
year = "2014",
abstract = "Improving aircraft pilot comfort requires continuous work in decreasing vibrations in the seat. In order to determine the suitability and potential of cockpit floor - seat connections we conducted an experiment where measurements were taken and seat vibration analysis conducted. Vibrations parameters were measured for maximum engine and propeller speed. This analysis indicates that passive vibrations damping or cockpit floor - seat connections functionality depends on flights profile and vibrations frequency. The connection in question was behaving like a vibration multiplier on the 3rd and 4th harmonic as well as on the 3,5 sub-harmonic in individual flight modes on basic propeller rotation frequency, however, it behaved as a vibration silencer on all other frequencies. Analysis of the experimental data has shown that it would be justified to start improving the self adaptive unit for active vibration reduction for pilot seats.",
publisher = "Strojarski Facultet",
journal = "Tehnički vjesnik",
title = "Potential connections of cockpit floor-seat on passive vibration reduction at a piston propelled airplane",
pages = "478-471",
number = "3",
volume = "21",
url = "https://hdl.handle.net/21.15107/rcub_machinery_1959"
}

Ilić, Z., Rašuo, B., Jovanović, M., Pekmezović, S., Bengin, A.,& Dinulović, M.. (2014). Potential connections of cockpit floor-seat on passive vibration reduction at a piston propelled airplane. in Tehnički vjesnik
Strojarski Facultet., 21(3), 471-478.
https://hdl.handle.net/21.15107/rcub_machinery_1959

Ilić Z, Rašuo B, Jovanović M, Pekmezović S, Bengin A, Dinulović M. Potential connections of cockpit floor-seat on passive vibration reduction at a piston propelled airplane. in Tehnički vjesnik. 2014;21(3):471-478.
https://hdl.handle.net/21.15107/rcub_machinery_1959 .

Ilić, Zoran, Rašuo, Boško, Jovanović, Miroslav, Pekmezović, Sladjan, Bengin, Aleksandar, Dinulović, Mirko, "Potential connections of cockpit floor-seat on passive vibration reduction at a piston propelled airplane" in Tehnički vjesnik, 21, no. 3 (2014):471-478,
https://hdl.handle.net/21.15107/rcub_machinery_1959 .

TY  - JOUR
AU  - Krstić, Branimir
AU  - Rašuo, Boško
AU  - Trifković, Dragan
AU  - Radisavljević, Igor
AU  - Rajić, Zoran
AU  - Dinulović, Mirko
PY  - 2013
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1685
AB  - Cylinder head (CH) failures in aircraft piston engine may have serious or fatal consequences to the safety of the crew and the aircraft. Moreover, when failure becomes undoubtedly repetitive and critical resulting in loss of aircraft, destruction of properties, and first and foremost loss of human lives, the cause of the failure requires to be investigated using a scientific approach. Therefore, the aim of this study is to investigate and identify the root cause of a repetitive premature failure in an aircraft engine CH. The piston engine of the training aircraft Utva-75 has malfunctioned during the flight due to the cracking of its aluminum cast CH. It has been the second engine failure of this type of aircraft due to the cracking in the CH in a very short span of time. From the visual examination of the mating fracture surfaces, it has been possible to observe typical beach and ratchet marks indicating the occurrence of fatigue failure. The crack has initiated from multiple origins located on the inner flange fillet on the exhaust side of the CH. Further examinations by using scanning electron microscopy as well as energy dispersive spectroscopy and metallography have shown that the fatigue had promoted from pre-existing material defect due to a high concentration of shrinkage pores at the initiation crack site and can be most likely associated with the manufacturing process of casting. The stress analysis of the cylinder assembly, carried out by means of finite element analysis, has also confirmed that the crack origin was located at the most stressed area of the cylinder assembly i.e. on the inner flange fillet of the exhaust side of the CH. This case study, together with the other recently reported, has definitely confirmed the repetitive and therefore systematic problems with the CH of air cooled, horizontally opposed, aircraft piston engines.
PB  - Pergamon-Elsevier Science Ltd, Oxford
T2  - Engineering Failure Analysis
T1  - An investigation of the repetitive failure in an aircraft engine cylinder head
EP  - 349
SP  - 335
VL  - 34
DO  - 10.1016/j.engfailanal.2013.08.013
ER  - 

@article{
author = "Krstić, Branimir and Rašuo, Boško and Trifković, Dragan and Radisavljević, Igor and Rajić, Zoran and Dinulović, Mirko",
year = "2013",
abstract = "Cylinder head (CH) failures in aircraft piston engine may have serious or fatal consequences to the safety of the crew and the aircraft. Moreover, when failure becomes undoubtedly repetitive and critical resulting in loss of aircraft, destruction of properties, and first and foremost loss of human lives, the cause of the failure requires to be investigated using a scientific approach. Therefore, the aim of this study is to investigate and identify the root cause of a repetitive premature failure in an aircraft engine CH. The piston engine of the training aircraft Utva-75 has malfunctioned during the flight due to the cracking of its aluminum cast CH. It has been the second engine failure of this type of aircraft due to the cracking in the CH in a very short span of time. From the visual examination of the mating fracture surfaces, it has been possible to observe typical beach and ratchet marks indicating the occurrence of fatigue failure. The crack has initiated from multiple origins located on the inner flange fillet on the exhaust side of the CH. Further examinations by using scanning electron microscopy as well as energy dispersive spectroscopy and metallography have shown that the fatigue had promoted from pre-existing material defect due to a high concentration of shrinkage pores at the initiation crack site and can be most likely associated with the manufacturing process of casting. The stress analysis of the cylinder assembly, carried out by means of finite element analysis, has also confirmed that the crack origin was located at the most stressed area of the cylinder assembly i.e. on the inner flange fillet of the exhaust side of the CH. This case study, together with the other recently reported, has definitely confirmed the repetitive and therefore systematic problems with the CH of air cooled, horizontally opposed, aircraft piston engines.",
publisher = "Pergamon-Elsevier Science Ltd, Oxford",
journal = "Engineering Failure Analysis",
title = "An investigation of the repetitive failure in an aircraft engine cylinder head",
pages = "349-335",
volume = "34",
doi = "10.1016/j.engfailanal.2013.08.013"
}

Krstić, B., Rašuo, B., Trifković, D., Radisavljević, I., Rajić, Z.,& Dinulović, M.. (2013). An investigation of the repetitive failure in an aircraft engine cylinder head. in Engineering Failure Analysis
Pergamon-Elsevier Science Ltd, Oxford., 34, 335-349.
https://doi.org/10.1016/j.engfailanal.2013.08.013

Krstić B, Rašuo B, Trifković D, Radisavljević I, Rajić Z, Dinulović M. An investigation of the repetitive failure in an aircraft engine cylinder head. in Engineering Failure Analysis. 2013;34:335-349.
doi:10.1016/j.engfailanal.2013.08.013 .

Krstić, Branimir, Rašuo, Boško, Trifković, Dragan, Radisavljević, Igor, Rajić, Zoran, Dinulović, Mirko, "An investigation of the repetitive failure in an aircraft engine cylinder head" in Engineering Failure Analysis, 34 (2013):335-349,
https://doi.org/10.1016/j.engfailanal.2013.08.013 . .

TY  - JOUR
AU  - Janicijević, Milovan
AU  - Srećković, Milesa
AU  - Kaluđerović, Branka
AU  - Bojanić, Slobodan
AU  - Druzijanić, Dragan
AU  - Dinulović, Mirko
AU  - Kovacević, Aleksander
PY  - 2013
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1715
AB  - This paper presents simulation and experimental results for the exposure of some carbon-based materials to alexandrite and Nd3+:YAG (yttrium aluminum garnet) laser radiation. Simulation of the heating effects was carried out using the COMSOL Multiphysics 3.5 package for samples of carbon-based P7295-2 fiber irradiated using an alexandrite laser and carbon-based P4396-2 fiber irradiated using an Nd3+:YAG laser, as well as by applying finite element modeling for P7295-2 samples irradiated using an Nd3+:YAG laser. In the experimental part, P7295-2 samples were exposed to alexandrite laser radiation while samples of carbon-based composite 3D C/C were exposed to Nd3+:YAG laser radiation. Micrographs of the laser induced craters were obtained by light and scanning electron microscopy, and the images analyzed using the ImageJ software. The results obtained enable identification of the laser-material interaction spots, and characterization of the laser induced changes in the materials investigated.
PB  - IOP Publishing Ltd, Bristol
T2  - Laser Physics
T1  - Characterization of laser beam interaction with carbon materials
IS  - 5
VL  - 23
DO  - 10.1088/1054-660X/23/5/056002
ER  - 

@article{
author = "Janicijević, Milovan and Srećković, Milesa and Kaluđerović, Branka and Bojanić, Slobodan and Druzijanić, Dragan and Dinulović, Mirko and Kovacević, Aleksander",
year = "2013",
abstract = "This paper presents simulation and experimental results for the exposure of some carbon-based materials to alexandrite and Nd3+:YAG (yttrium aluminum garnet) laser radiation. Simulation of the heating effects was carried out using the COMSOL Multiphysics 3.5 package for samples of carbon-based P7295-2 fiber irradiated using an alexandrite laser and carbon-based P4396-2 fiber irradiated using an Nd3+:YAG laser, as well as by applying finite element modeling for P7295-2 samples irradiated using an Nd3+:YAG laser. In the experimental part, P7295-2 samples were exposed to alexandrite laser radiation while samples of carbon-based composite 3D C/C were exposed to Nd3+:YAG laser radiation. Micrographs of the laser induced craters were obtained by light and scanning electron microscopy, and the images analyzed using the ImageJ software. The results obtained enable identification of the laser-material interaction spots, and characterization of the laser induced changes in the materials investigated.",
publisher = "IOP Publishing Ltd, Bristol",
journal = "Laser Physics",
title = "Characterization of laser beam interaction with carbon materials",
number = "5",
volume = "23",
doi = "10.1088/1054-660X/23/5/056002"
}

Janicijević, M., Srećković, M., Kaluđerović, B., Bojanić, S., Druzijanić, D., Dinulović, M.,& Kovacević, A.. (2013). Characterization of laser beam interaction with carbon materials. in Laser Physics
IOP Publishing Ltd, Bristol., 23(5).
https://doi.org/10.1088/1054-660X/23/5/056002

Janicijević M, Srećković M, Kaluđerović B, Bojanić S, Druzijanić D, Dinulović M, Kovacević A. Characterization of laser beam interaction with carbon materials. in Laser Physics. 2013;23(5).
doi:10.1088/1054-660X/23/5/056002 .

Janicijević, Milovan, Srećković, Milesa, Kaluđerović, Branka, Bojanić, Slobodan, Druzijanić, Dragan, Dinulović, Mirko, Kovacević, Aleksander, "Characterization of laser beam interaction with carbon materials" in Laser Physics, 23, no. 5 (2013),
https://doi.org/10.1088/1054-660X/23/5/056002 . .

TY  - JOUR
AU  - Krstić, Branimir
AU  - Rašuo, Boško
AU  - Trifković, Dragan
AU  - Radisavljević, Igor
AU  - Rajić, Zoran
AU  - Dinulović, Mirko
PY  - 2013
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1726
AB  - The piston engine of the training aircraft malfunctioned during the flight due to the cracking of its cylinder head (CH), which is manufactured from an aluminum casting alloy. Based on the fractographic examination of the mating fracture surfaces, the characteristic ratchet and beach marks were observed indicating the occurrence of fatigue failure. The crack was initiated from multiple origins located on the inner flange fillet on the exhaust side of the CH. The metallography examination has shown that the fatigue was promoted from preexisting material defect due to an elevated presence of shrinkage pores at the crack initiation zone and was most likely associated with the manufacturing process of casting. The finite element (FE) method, utilized to determine the stress state of the CH subjected to gas pressure, also confirmed that the crack origin was located at the most stress area.
PB  - Pergamon-Elsevier Science Ltd, Oxford
T2  - Engineering Failure Analysis
T1  - Failure analysis of an aircraft engine cylinder head
EP  - 15
SP  - 1
VL  - 32
DO  - 10.1016/j.engfailanal.2013.03.004
ER  - 

@article{
author = "Krstić, Branimir and Rašuo, Boško and Trifković, Dragan and Radisavljević, Igor and Rajić, Zoran and Dinulović, Mirko",
year = "2013",
abstract = "The piston engine of the training aircraft malfunctioned during the flight due to the cracking of its cylinder head (CH), which is manufactured from an aluminum casting alloy. Based on the fractographic examination of the mating fracture surfaces, the characteristic ratchet and beach marks were observed indicating the occurrence of fatigue failure. The crack was initiated from multiple origins located on the inner flange fillet on the exhaust side of the CH. The metallography examination has shown that the fatigue was promoted from preexisting material defect due to an elevated presence of shrinkage pores at the crack initiation zone and was most likely associated with the manufacturing process of casting. The finite element (FE) method, utilized to determine the stress state of the CH subjected to gas pressure, also confirmed that the crack origin was located at the most stress area.",
publisher = "Pergamon-Elsevier Science Ltd, Oxford",
journal = "Engineering Failure Analysis",
title = "Failure analysis of an aircraft engine cylinder head",
pages = "15-1",
volume = "32",
doi = "10.1016/j.engfailanal.2013.03.004"
}

Krstić, B., Rašuo, B., Trifković, D., Radisavljević, I., Rajić, Z.,& Dinulović, M.. (2013). Failure analysis of an aircraft engine cylinder head. in Engineering Failure Analysis
Pergamon-Elsevier Science Ltd, Oxford., 32, 1-15.
https://doi.org/10.1016/j.engfailanal.2013.03.004

Krstić B, Rašuo B, Trifković D, Radisavljević I, Rajić Z, Dinulović M. Failure analysis of an aircraft engine cylinder head. in Engineering Failure Analysis. 2013;32:1-15.
doi:10.1016/j.engfailanal.2013.03.004 .

Krstić, Branimir, Rašuo, Boško, Trifković, Dragan, Radisavljević, Igor, Rajić, Zoran, Dinulović, Mirko, "Failure analysis of an aircraft engine cylinder head" in Engineering Failure Analysis, 32 (2013):1-15,
https://doi.org/10.1016/j.engfailanal.2013.03.004 . .

TY  - JOUR
AU  - Dinulović, Mirko
AU  - Rašuo, Boško
AU  - Krstić, Branimir
AU  - Bojanić, Aleksandar
AU  - Bojanić, A.
PY  - 2013
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1752
AB  - Povećana upotreba kompozitnih materijala donela potrebu za razvojem pouzdanih i efikasnih tehnika popravki. Kao i sve druge noseće metalne strukture i kompozitne strukture sklone su oštećenjima. Razvijene tehnike popravki metalnih konstrukcije nisu direktno primenljive na kompozite i problem popravki kompozitnih struktura mora biti detaljno proučen. U ovom radu analizirana je primena kompozitnih materijala sa slučajnim rasporedom vlakana, kao materijalom za popravku oštećenih saćastih jezgara visoke gustine sendvič konstrukcija. Pomoću Panove teorije izveden je izraz potrebnog zapreminskog udela vlakana materijala popravke i određeno je kompletno naponsko deformaciono stanje popravljene kompozitne stukture metodom konačnih elemenata. Zaključeno je da kompozitni materijali sa slučajnim rasporedom vlakana predstavljaju veoma dobre kandidate za popravku oštećenih kompozitnih struktura sa saćastim jezgrima.
AB  - The increased use of composites has rendered the need for development of reliable and efficient repair techniques. Like all other metallic structures composite structures are prone to variety of damage. Repair techniques developed for metallic structures are not directly applicable to composites and problem of composite repair has to be investigated in great detail. In the present paper application of 3D random fiber polymer composites, as a repair material for damaged high density honeycomb cores in sandwich structures is investigated. Based on Pan 's theory the expression for matching fiber volume fraction of the repair material is derived and complete stress-strain field, of the repaired sandwich structure is determined using finite element approach. It is concluded that the 3D random fiber composites represent very good candidates as repair materials for damaged honeycomb structured composites.
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Kompozitni materijali sa slučajnim rasporedom vlakana kao materijali za popravku oštećenih saćastih jezgara
T1  - 3D random fiber composites as a repair material for damaged honeycomb cores
EP  - 332
IS  - 4
SP  - 325
VL  - 41
UR  - https://hdl.handle.net/21.15107/rcub_machinery_1752
ER  - 

@article{
author = "Dinulović, Mirko and Rašuo, Boško and Krstić, Branimir and Bojanić, Aleksandar and Bojanić, A.",
year = "2013",
abstract = "Povećana upotreba kompozitnih materijala donela potrebu za razvojem pouzdanih i efikasnih tehnika popravki. Kao i sve druge noseće metalne strukture i kompozitne strukture sklone su oštećenjima. Razvijene tehnike popravki metalnih konstrukcije nisu direktno primenljive na kompozite i problem popravki kompozitnih struktura mora biti detaljno proučen. U ovom radu analizirana je primena kompozitnih materijala sa slučajnim rasporedom vlakana, kao materijalom za popravku oštećenih saćastih jezgara visoke gustine sendvič konstrukcija. Pomoću Panove teorije izveden je izraz potrebnog zapreminskog udela vlakana materijala popravke i određeno je kompletno naponsko deformaciono stanje popravljene kompozitne stukture metodom konačnih elemenata. Zaključeno je da kompozitni materijali sa slučajnim rasporedom vlakana predstavljaju veoma dobre kandidate za popravku oštećenih kompozitnih struktura sa saćastim jezgrima., The increased use of composites has rendered the need for development of reliable and efficient repair techniques. Like all other metallic structures composite structures are prone to variety of damage. Repair techniques developed for metallic structures are not directly applicable to composites and problem of composite repair has to be investigated in great detail. In the present paper application of 3D random fiber polymer composites, as a repair material for damaged high density honeycomb cores in sandwich structures is investigated. Based on Pan 's theory the expression for matching fiber volume fraction of the repair material is derived and complete stress-strain field, of the repaired sandwich structure is determined using finite element approach. It is concluded that the 3D random fiber composites represent very good candidates as repair materials for damaged honeycomb structured composites.",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Kompozitni materijali sa slučajnim rasporedom vlakana kao materijali za popravku oštećenih saćastih jezgara, 3D random fiber composites as a repair material for damaged honeycomb cores",
pages = "332-325",
number = "4",
volume = "41",
url = "https://hdl.handle.net/21.15107/rcub_machinery_1752"
}

Dinulović, M., Rašuo, B., Krstić, B., Bojanić, A.,& Bojanić, A.. (2013). Kompozitni materijali sa slučajnim rasporedom vlakana kao materijali za popravku oštećenih saćastih jezgara. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 41(4), 325-332.
https://hdl.handle.net/21.15107/rcub_machinery_1752

Dinulović M, Rašuo B, Krstić B, Bojanić A, Bojanić A. Kompozitni materijali sa slučajnim rasporedom vlakana kao materijali za popravku oštećenih saćastih jezgara. in FME Transactions. 2013;41(4):325-332.
https://hdl.handle.net/21.15107/rcub_machinery_1752 .

Dinulović, Mirko, Rašuo, Boško, Krstić, Branimir, Bojanić, Aleksandar, Bojanić, A., "Kompozitni materijali sa slučajnim rasporedom vlakana kao materijali za popravku oštećenih saćastih jezgara" in FME Transactions, 41, no. 4 (2013):325-332,
https://hdl.handle.net/21.15107/rcub_machinery_1752 .

TY  - JOUR
AU  - Garinis, Dimitrios
AU  - Dinulović, Mirko
AU  - Rašuo, Boško
PY  - 2012
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1580
AB  - U ovom radu izvršena je modalna analiza modifikovane lopatice helikoptera 'Gazela'. Modifikovana lopatica je kompletno kompozitna sa saćastom ispunom. Prikazan je metod određivanja modova oscilovanja i sopstvenih frekvencija. Modifikovana lopatica sastoji se od saćaste ispune, ramenjače od 3D usmerenog kompozita i tankih karbonskih ploča kao oplate. Da bi se odredila matrica krutosti ispune korišćen je metod ekvivalentnih masa. U cilju nalaženja optimalnog metoda za određivanje sopstvenih frekvencija ispitano je nekoliko poznatih metoda. Metod Lancosa pokazao je najtačnije rezultate kroz umereno procesorsko vreme kada je u pitanju određivanje sopstvenih frekvencija i modova oscilovanja kod struktura od kompozitnih materijala sa saćastim ispunama. Ovom metodom izračunata su prva četiri moda oscilovanja modifikovane kompozitne lopatice, i prikazani su rezultati modova oscilovanja i deformacione energije lopatice.
AB  - In the present study, modal analysis has been performed on modified Gazelle helicopter blade. The construction of the blade is fully composite with the honeycomb core. The approach to determining structure mode shapes and natural frequencies is presented. Modified blade consists of core material, 3D unidirectional composite spar and thin carbon composite facesheets as blade skin. To determine the stiffness of the honeycomb core, the equivalent mass approach was used. Several methods of eigenvalue extraction have been investigated in order to find optimal method which can be used in dynamic analysis of composite structures containing honeycomb cores. Among all extraction methods investigated, it was found that combined Lanczos method is most effective in terms of accuracy and CPU time for eigenvalue extraction in composite structures with honeycomb core having large number of degrees of freedom. Strain energies for first four mode shapes of modified helicopter blade have been calculated using numerical approach and results are presented.
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Dinamička analiza modifikovane helikopterske lopatice od kompozitnih materijala
T1  - Dynamic analysis of modified composite helicopter blade
EP  - 68
IS  - 2
SP  - 63
VL  - 40
UR  - https://hdl.handle.net/21.15107/rcub_machinery_1580
ER  - 

@article{
author = "Garinis, Dimitrios and Dinulović, Mirko and Rašuo, Boško",
year = "2012",
abstract = "U ovom radu izvršena je modalna analiza modifikovane lopatice helikoptera 'Gazela'. Modifikovana lopatica je kompletno kompozitna sa saćastom ispunom. Prikazan je metod određivanja modova oscilovanja i sopstvenih frekvencija. Modifikovana lopatica sastoji se od saćaste ispune, ramenjače od 3D usmerenog kompozita i tankih karbonskih ploča kao oplate. Da bi se odredila matrica krutosti ispune korišćen je metod ekvivalentnih masa. U cilju nalaženja optimalnog metoda za određivanje sopstvenih frekvencija ispitano je nekoliko poznatih metoda. Metod Lancosa pokazao je najtačnije rezultate kroz umereno procesorsko vreme kada je u pitanju određivanje sopstvenih frekvencija i modova oscilovanja kod struktura od kompozitnih materijala sa saćastim ispunama. Ovom metodom izračunata su prva četiri moda oscilovanja modifikovane kompozitne lopatice, i prikazani su rezultati modova oscilovanja i deformacione energije lopatice., In the present study, modal analysis has been performed on modified Gazelle helicopter blade. The construction of the blade is fully composite with the honeycomb core. The approach to determining structure mode shapes and natural frequencies is presented. Modified blade consists of core material, 3D unidirectional composite spar and thin carbon composite facesheets as blade skin. To determine the stiffness of the honeycomb core, the equivalent mass approach was used. Several methods of eigenvalue extraction have been investigated in order to find optimal method which can be used in dynamic analysis of composite structures containing honeycomb cores. Among all extraction methods investigated, it was found that combined Lanczos method is most effective in terms of accuracy and CPU time for eigenvalue extraction in composite structures with honeycomb core having large number of degrees of freedom. Strain energies for first four mode shapes of modified helicopter blade have been calculated using numerical approach and results are presented.",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Dinamička analiza modifikovane helikopterske lopatice od kompozitnih materijala, Dynamic analysis of modified composite helicopter blade",
pages = "68-63",
number = "2",
volume = "40",
url = "https://hdl.handle.net/21.15107/rcub_machinery_1580"
}

Garinis, D., Dinulović, M.,& Rašuo, B.. (2012). Dinamička analiza modifikovane helikopterske lopatice od kompozitnih materijala. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 40(2), 63-68.
https://hdl.handle.net/21.15107/rcub_machinery_1580

Garinis D, Dinulović M, Rašuo B. Dinamička analiza modifikovane helikopterske lopatice od kompozitnih materijala. in FME Transactions. 2012;40(2):63-68.
https://hdl.handle.net/21.15107/rcub_machinery_1580 .

Garinis, Dimitrios, Dinulović, Mirko, Rašuo, Boško, "Dinamička analiza modifikovane helikopterske lopatice od kompozitnih materijala" in FME Transactions, 40, no. 2 (2012):63-68,
https://hdl.handle.net/21.15107/rcub_machinery_1580 .

TY  - JOUR
AU  - Dinulović, Mirko
AU  - Rašuo, Boško
PY  - 2011
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1196
AB  - In this paper effective medium theory based on Clausius-Mossoti relation was used to predict dielectric properties of multiphase composite system. The composite consisted of E-glass fibers (plain weave S-glass, J.B. Martin) embedded in bisphenol A diglycidylether epoxy matrix (D.E.R. 324, D.O.W. chemicals) with hollow ceramic spherical inclusions (SF 14, P.Q. Corp.) at different volume fractions. In many engineering applications, materials with designed dielectric properties are often sought. An important question in engineering design of a composite material is how the overall properties of the composite depend on those of the individual constituents. Mixing the epoxy resin with hollow ceramic inclusions can effectively reduce dielectric constant of the resin, which is often desirable, rendering composites as good candidates for many applications, especially in telecommunications. Compensation for degradation of mechanical properties of matrix (due to inclusion insertion) is obtained by embedding fibers into the mixture. Measurements of dielectric constant and loss tangent for this multiphase composite system were conducted in the region between 0.1 and 100 kHz range using DEA 290 (T.A. Instruments) dielectric analyzer and experimental results are presented. Good correlation between analytical model and experimental results was observed throughout all frequency range of investigation.
PB  - Elsevier Sci Ltd, Oxford
T2  - Composite Structures
T1  - Dielectric modeling of multiphase composites
EP  - 3215
IS  - 12
SP  - 3209
VL  - 93
DO  - 10.1016/j.compstruct.2011.05.036
ER  - 

@article{
author = "Dinulović, Mirko and Rašuo, Boško",
year = "2011",
abstract = "In this paper effective medium theory based on Clausius-Mossoti relation was used to predict dielectric properties of multiphase composite system. The composite consisted of E-glass fibers (plain weave S-glass, J.B. Martin) embedded in bisphenol A diglycidylether epoxy matrix (D.E.R. 324, D.O.W. chemicals) with hollow ceramic spherical inclusions (SF 14, P.Q. Corp.) at different volume fractions. In many engineering applications, materials with designed dielectric properties are often sought. An important question in engineering design of a composite material is how the overall properties of the composite depend on those of the individual constituents. Mixing the epoxy resin with hollow ceramic inclusions can effectively reduce dielectric constant of the resin, which is often desirable, rendering composites as good candidates for many applications, especially in telecommunications. Compensation for degradation of mechanical properties of matrix (due to inclusion insertion) is obtained by embedding fibers into the mixture. Measurements of dielectric constant and loss tangent for this multiphase composite system were conducted in the region between 0.1 and 100 kHz range using DEA 290 (T.A. Instruments) dielectric analyzer and experimental results are presented. Good correlation between analytical model and experimental results was observed throughout all frequency range of investigation.",
publisher = "Elsevier Sci Ltd, Oxford",
journal = "Composite Structures",
title = "Dielectric modeling of multiphase composites",
pages = "3215-3209",
number = "12",
volume = "93",
doi = "10.1016/j.compstruct.2011.05.036"
}

Dinulović, M.,& Rašuo, B.. (2011). Dielectric modeling of multiphase composites. in Composite Structures
Elsevier Sci Ltd, Oxford., 93(12), 3209-3215.
https://doi.org/10.1016/j.compstruct.2011.05.036

Dinulović M, Rašuo B. Dielectric modeling of multiphase composites. in Composite Structures. 2011;93(12):3209-3215.
doi:10.1016/j.compstruct.2011.05.036 .

Dinulović, Mirko, Rašuo, Boško, "Dielectric modeling of multiphase composites" in Composite Structures, 93, no. 12 (2011):3209-3215,
https://doi.org/10.1016/j.compstruct.2011.05.036 . .

TY  - CONF
AU  - Rašuo, Boško
AU  - Dinulović, Mirko
PY  - 2011
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1294
C3  - ICCM International Conferences on Composite Materials
T1  - Free-edge stresses in composite laminates under mechanical loading
UR  - https://hdl.handle.net/21.15107/rcub_machinery_1294
ER  - 

@conference{
author = "Rašuo, Boško and Dinulović, Mirko",
year = "2011",
journal = "ICCM International Conferences on Composite Materials",
title = "Free-edge stresses in composite laminates under mechanical loading",
url = "https://hdl.handle.net/21.15107/rcub_machinery_1294"
}

Rašuo, B.,& Dinulović, M.. (2011). Free-edge stresses in composite laminates under mechanical loading. in ICCM International Conferences on Composite Materials.
https://hdl.handle.net/21.15107/rcub_machinery_1294

Rašuo B, Dinulović M. Free-edge stresses in composite laminates under mechanical loading. in ICCM International Conferences on Composite Materials. 2011;.
https://hdl.handle.net/21.15107/rcub_machinery_1294 .

Rašuo, Boško, Dinulović, Mirko, "Free-edge stresses in composite laminates under mechanical loading" in ICCM International Conferences on Composite Materials (2011),
https://hdl.handle.net/21.15107/rcub_machinery_1294 .