TY  - CONF
AU  - Ćosić, Petar
AU  - Petrašinović, Miloš
AU  - Grbović, Aleksandar
AU  - Petrašinović, Danilo
AU  - Petrović, Mihailo
AU  - Petrović, Veljko
AU  - Raičević, Nikola
AU  - Rašuo, Boško
PY  - 2023
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7730
AB  - Aerospace engineering, as a field in which the reduction of mass has always been one of the primary tasks of its engineers, has made significant progress as a result of numerous developments and advancements in the field of composite materials in the sense of gaining large benefits from the relatively low density that characterizes composites. In the spirit of the increasing use of composite materials on aerospace structures, in this paper we will conduct an experimental and numerical analysis of the strength of a drone arm made of a composite material. Every method of analysis, whether it is analytical, numerical, or experimental, has some advantages and disadvantages. Experimental results are easily affected by random and instrumental errors and numerical methods are highly affected by the chosen physical model. In order to obtain the most reliable analysis solution, a mixture of numerical analysis backed up by experimental data is required. In the hope of bypassing the expensive and time-consuming experiments in the future, in this paper we will conduct a numerical analysis on a drone arm made of composite materials which will then be replicated by an experiment verifying its validity.
PB  - The Serbian Society of Mechanics
C3  - 9th International Congress of the Serbian Society of Mechanics
T1  - Experimental and Numerical Analysis of the Strength of a Drone Arm Made of Composite Material
EP  - 300
SP  - 293
UR  - https://hdl.handle.net/21.15107/rcub_machinery_7730
ER  - 

@conference{
author = "Ćosić, Petar and Petrašinović, Miloš and Grbović, Aleksandar and Petrašinović, Danilo and Petrović, Mihailo and Petrović, Veljko and Raičević, Nikola and Rašuo, Boško",
year = "2023",
abstract = "Aerospace engineering, as a field in which the reduction of mass has always been one of the primary tasks of its engineers, has made significant progress as a result of numerous developments and advancements in the field of composite materials in the sense of gaining large benefits from the relatively low density that characterizes composites. In the spirit of the increasing use of composite materials on aerospace structures, in this paper we will conduct an experimental and numerical analysis of the strength of a drone arm made of a composite material. Every method of analysis, whether it is analytical, numerical, or experimental, has some advantages and disadvantages. Experimental results are easily affected by random and instrumental errors and numerical methods are highly affected by the chosen physical model. In order to obtain the most reliable analysis solution, a mixture of numerical analysis backed up by experimental data is required. In the hope of bypassing the expensive and time-consuming experiments in the future, in this paper we will conduct a numerical analysis on a drone arm made of composite materials which will then be replicated by an experiment verifying its validity.",
publisher = "The Serbian Society of Mechanics",
journal = "9th International Congress of the Serbian Society of Mechanics",
title = "Experimental and Numerical Analysis of the Strength of a Drone Arm Made of Composite Material",
pages = "300-293",
url = "https://hdl.handle.net/21.15107/rcub_machinery_7730"
}

Ćosić, P., Petrašinović, M., Grbović, A., Petrašinović, D., Petrović, M., Petrović, V., Raičević, N.,& Rašuo, B.. (2023). Experimental and Numerical Analysis of the Strength of a Drone Arm Made of Composite Material. in 9th International Congress of the Serbian Society of Mechanics
The Serbian Society of Mechanics., 293-300.
https://hdl.handle.net/21.15107/rcub_machinery_7730

Ćosić P, Petrašinović M, Grbović A, Petrašinović D, Petrović M, Petrović V, Raičević N, Rašuo B. Experimental and Numerical Analysis of the Strength of a Drone Arm Made of Composite Material. in 9th International Congress of the Serbian Society of Mechanics. 2023;:293-300.
https://hdl.handle.net/21.15107/rcub_machinery_7730 .

Ćosić, Petar, Petrašinović, Miloš, Grbović, Aleksandar, Petrašinović, Danilo, Petrović, Mihailo, Petrović, Veljko, Raičević, Nikola, Rašuo, Boško, "Experimental and Numerical Analysis of the Strength of a Drone Arm Made of Composite Material" in 9th International Congress of the Serbian Society of Mechanics (2023):293-300,
https://hdl.handle.net/21.15107/rcub_machinery_7730 .

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  - Kostić, Cedomir
AU  - Bengin, Aleksandar
AU  - Rašuo, Boško
AU  - Damljanović, Dijana
PY  - 2021
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3487
AB  - The goal of this work is to build a unique numerical method to obtain the basic aerodynamic characteristics of the aircraft and to enable a wide application of the method in the analysis of some aerodynamic characteristics of the aircraft, without use of empirical methods. The Computational fluid dynamics (CFD) simulation method was being calibrated based on test results of the standard AGARD-B (Advisory Group for Aerospace Research and Development) test model, which were obtained in the T-38 trisonic wind tunnel facility of the Military Technical Institute (VTI) in Belgrade, Serbia.The paper presents the CFD simulation through a description of the conditions of flow, geometry of the computer domain, grid density and mesh strategy, boundary conditions, initial strategy and turbulence model. The CFD simulation was carried out for flow cases with similarity parameters M = 0.6, M = 0.85 and M = 1.6 and Re = from 7.7(x10(6)) to 9.9(x10(6)) . The results of calculations were compared with the appropriate experimental ones and presented in the form of comparative diagrams for the drag, lift and pitching moment coefficients. The results of investigation presented in divergence diagrams show very good agreement between numerical and experimental ones. Simulated flows are illustrated by the distribution of pressure and velocity components on the surface of the tested model and the computational domain. This CFD simulation will be applied to other similar aerodynamic designs for a wide range angles of attack and Mach numbers and can be a strong point for the development of different aerodynamic designs.The ultimate aim of the work is to use the previous calibrated CFD simulation method as the basis for future determination of the aerodynamic characteristics of aircraft in non-stationary flight modes, caused by motion of the aircraft and/or by changing the free-velocity vector.
PB  - Sage Publications Ltd, London
T2  - Proceedings of The Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering
T1  - Calibration of the CFD code based on testing of a standard AGARD-B model for determination of aerodynamic characteristics
EP  - 1145
IS  - 10
SP  - 1129
VL  - 235
DO  - 10.1177/0954410020966859
ER  - 

@article{
author = "Kostić, Cedomir and Bengin, Aleksandar and Rašuo, Boško and Damljanović, Dijana",
year = "2021",
abstract = "The goal of this work is to build a unique numerical method to obtain the basic aerodynamic characteristics of the aircraft and to enable a wide application of the method in the analysis of some aerodynamic characteristics of the aircraft, without use of empirical methods. The Computational fluid dynamics (CFD) simulation method was being calibrated based on test results of the standard AGARD-B (Advisory Group for Aerospace Research and Development) test model, which were obtained in the T-38 trisonic wind tunnel facility of the Military Technical Institute (VTI) in Belgrade, Serbia.The paper presents the CFD simulation through a description of the conditions of flow, geometry of the computer domain, grid density and mesh strategy, boundary conditions, initial strategy and turbulence model. The CFD simulation was carried out for flow cases with similarity parameters M = 0.6, M = 0.85 and M = 1.6 and Re = from 7.7(x10(6)) to 9.9(x10(6)) . The results of calculations were compared with the appropriate experimental ones and presented in the form of comparative diagrams for the drag, lift and pitching moment coefficients. The results of investigation presented in divergence diagrams show very good agreement between numerical and experimental ones. Simulated flows are illustrated by the distribution of pressure and velocity components on the surface of the tested model and the computational domain. This CFD simulation will be applied to other similar aerodynamic designs for a wide range angles of attack and Mach numbers and can be a strong point for the development of different aerodynamic designs.The ultimate aim of the work is to use the previous calibrated CFD simulation method as the basis for future determination of the aerodynamic characteristics of aircraft in non-stationary flight modes, caused by motion of the aircraft and/or by changing the free-velocity vector.",
publisher = "Sage Publications Ltd, London",
journal = "Proceedings of The Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering",
title = "Calibration of the CFD code based on testing of a standard AGARD-B model for determination of aerodynamic characteristics",
pages = "1145-1129",
number = "10",
volume = "235",
doi = "10.1177/0954410020966859"
}

Kostić, C., Bengin, A., Rašuo, B.,& Damljanović, D.. (2021). Calibration of the CFD code based on testing of a standard AGARD-B model for determination of aerodynamic characteristics. in Proceedings of The Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering
Sage Publications Ltd, London., 235(10), 1129-1145.
https://doi.org/10.1177/0954410020966859

Kostić C, Bengin A, Rašuo B, Damljanović D. Calibration of the CFD code based on testing of a standard AGARD-B model for determination of aerodynamic characteristics. in Proceedings of The Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering. 2021;235(10):1129-1145.
doi:10.1177/0954410020966859 .

Kostić, Cedomir, Bengin, Aleksandar, Rašuo, Boško, Damljanović, Dijana, "Calibration of the CFD code based on testing of a standard AGARD-B model for determination of aerodynamic characteristics" in Proceedings of The Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering, 235, no. 10 (2021):1129-1145,
https://doi.org/10.1177/0954410020966859 . .

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  - CONF
AU  - Kastratović, Gordana
AU  - Vidanović, Nenad
AU  - Grbović, Aleksandar
AU  - Mirkov, Nikola
AU  - Rašuo, Boško
PY  - 2020
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3323
AB  - This paper discusses certain aspects of numerical simulation of crack propagation in wire ropes subjected to axial loading, with the aim to explore and to demonstrate the capacity, performances and difficulties of crack propagation modeling by usage of numerical computational methods in such complex structures. For this purpose, the finite element method (FEM) was used, and 3D numerical analyses were performed in Ansys Workbench software. In order to validate and verify performed numerical modeling, crack growth rate based on calculated stress intensity factors (SIFs) along the crack fronts was obtained for the model for which experimental results could be found in the available literature. Finally, using the advanced modeling techniques, the parametric 3D model of seven-wire strand was analyzed. Conducted analysis showed that FEM could be a powerful tool for fatigue life predictions in order to reduce the need for experiments, which are still the only successful method for fatigue life estimation of wire ropes.
PB  - Springer International Publishing Ag, Cham
C3  - Computational and Experimental Approaches in Materials Science and Engineering, Cnntech 2019
T1  - Numerical Simulation of Crack Propagation in Seven-Wire Strand
EP  - 91
SP  - 76
VL  - 90
DO  - 10.1007/978-3-030-30853-7_5
ER  - 

@conference{
author = "Kastratović, Gordana and Vidanović, Nenad and Grbović, Aleksandar and Mirkov, Nikola and Rašuo, Boško",
year = "2020",
abstract = "This paper discusses certain aspects of numerical simulation of crack propagation in wire ropes subjected to axial loading, with the aim to explore and to demonstrate the capacity, performances and difficulties of crack propagation modeling by usage of numerical computational methods in such complex structures. For this purpose, the finite element method (FEM) was used, and 3D numerical analyses were performed in Ansys Workbench software. In order to validate and verify performed numerical modeling, crack growth rate based on calculated stress intensity factors (SIFs) along the crack fronts was obtained for the model for which experimental results could be found in the available literature. Finally, using the advanced modeling techniques, the parametric 3D model of seven-wire strand was analyzed. Conducted analysis showed that FEM could be a powerful tool for fatigue life predictions in order to reduce the need for experiments, which are still the only successful method for fatigue life estimation of wire ropes.",
publisher = "Springer International Publishing Ag, Cham",
journal = "Computational and Experimental Approaches in Materials Science and Engineering, Cnntech 2019",
title = "Numerical Simulation of Crack Propagation in Seven-Wire Strand",
pages = "91-76",
volume = "90",
doi = "10.1007/978-3-030-30853-7_5"
}

Kastratović, G., Vidanović, N., Grbović, A., Mirkov, N.,& Rašuo, B.. (2020). Numerical Simulation of Crack Propagation in Seven-Wire Strand. in Computational and Experimental Approaches in Materials Science and Engineering, Cnntech 2019
Springer International Publishing Ag, Cham., 90, 76-91.
https://doi.org/10.1007/978-3-030-30853-7_5

Kastratović G, Vidanović N, Grbović A, Mirkov N, Rašuo B. Numerical Simulation of Crack Propagation in Seven-Wire Strand. in Computational and Experimental Approaches in Materials Science and Engineering, Cnntech 2019. 2020;90:76-91.
doi:10.1007/978-3-030-30853-7_5 .

Kastratović, Gordana, Vidanović, Nenad, Grbović, Aleksandar, Mirkov, Nikola, Rašuo, Boško, "Numerical Simulation of Crack Propagation in Seven-Wire Strand" in Computational and Experimental Approaches in Materials Science and Engineering, Cnntech 2019, 90 (2020):76-91,
https://doi.org/10.1007/978-3-030-30853-7_5 . .

TY  - JOUR
AU  - Vidanović, Nenad
AU  - Rašuo, Boško
AU  - Kastratović, Gordana
AU  - Grbović, Aleksandar
AU  - Puharić, Mirjana
AU  - Maksimović, Katarina
PY  - 2020
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3380
AB  - The main goal of this paper is to expand previously conducted study and consequently to upgrade the proposed multimodular numerical framework developed for fluid-structure interaction simulation (FSI) and multidisciplinary design optimization (MDO) purposes, in a manner that thermal-structure interaction is observed and implemented into the established numerical framework. The upgraded and considerably improved algorithm was used for MDO of the short-range ballistic missile (SRBM) model. Because of its high-speed regimes, this aircraft model was selected for the purpose of numerical modeling and optimization of aerodynamically heated structure. The present study is concerned with a broader observation of critical multipoint flight conditions and represents a more realistic scenario, which indicates this study as one contribution more in a scope of fluid-thermal-structure interaction (FTSI) numerical modeling and optimization. With respect to predefined objectives and constraints, multidisciplinary shape optimization of the fin structure resulted in overall improvement of the missile initial performances. Also, aerothermally induced critical responses of the fin structure were prevented. Numerical modeling of FSI/FTSI and MDO within an industry-accepted design tool resulted in powerful monolithic environment, which, with adopted multipoint regimes and multicriteria settings, was used for aerodynamic-thermal/structural optimization. The obtained results were compared with the results from the previous study conducted without thermal effects.
PB  - Amer Inst Aeronautics  Astronautics, Reston
T2  - Journal of Spacecraft and Rockets
T1  - Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating
EP  - 527
IS  - 3
SP  - 510
VL  - 57
DO  - 10.2514/1.A34575
ER  - 

@article{
author = "Vidanović, Nenad and Rašuo, Boško and Kastratović, Gordana and Grbović, Aleksandar and Puharić, Mirjana and Maksimović, Katarina",
year = "2020",
abstract = "The main goal of this paper is to expand previously conducted study and consequently to upgrade the proposed multimodular numerical framework developed for fluid-structure interaction simulation (FSI) and multidisciplinary design optimization (MDO) purposes, in a manner that thermal-structure interaction is observed and implemented into the established numerical framework. The upgraded and considerably improved algorithm was used for MDO of the short-range ballistic missile (SRBM) model. Because of its high-speed regimes, this aircraft model was selected for the purpose of numerical modeling and optimization of aerodynamically heated structure. The present study is concerned with a broader observation of critical multipoint flight conditions and represents a more realistic scenario, which indicates this study as one contribution more in a scope of fluid-thermal-structure interaction (FTSI) numerical modeling and optimization. With respect to predefined objectives and constraints, multidisciplinary shape optimization of the fin structure resulted in overall improvement of the missile initial performances. Also, aerothermally induced critical responses of the fin structure were prevented. Numerical modeling of FSI/FTSI and MDO within an industry-accepted design tool resulted in powerful monolithic environment, which, with adopted multipoint regimes and multicriteria settings, was used for aerodynamic-thermal/structural optimization. The obtained results were compared with the results from the previous study conducted without thermal effects.",
publisher = "Amer Inst Aeronautics  Astronautics, Reston",
journal = "Journal of Spacecraft and Rockets",
title = "Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating",
pages = "527-510",
number = "3",
volume = "57",
doi = "10.2514/1.A34575"
}

Vidanović, N., Rašuo, B., Kastratović, G., Grbović, A., Puharić, M.,& Maksimović, K.. (2020). Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating. in Journal of Spacecraft and Rockets
Amer Inst Aeronautics  Astronautics, Reston., 57(3), 510-527.
https://doi.org/10.2514/1.A34575

Vidanović N, Rašuo B, Kastratović G, Grbović A, Puharić M, Maksimović K. Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating. in Journal of Spacecraft and Rockets. 2020;57(3):510-527.
doi:10.2514/1.A34575 .

Vidanović, Nenad, Rašuo, Boško, Kastratović, Gordana, Grbović, Aleksandar, Puharić, Mirjana, Maksimović, Katarina, "Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating" in Journal of Spacecraft and Rockets, 57, no. 3 (2020):510-527,
https://doi.org/10.2514/1.A34575 . .

TY  - JOUR
AU  - Ekmedzić, Marko Z.
AU  - Bengin, Aleksandar
AU  - Rašuo, Boško
PY  - 2018
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2766
AB  - In this paper is presented a new conceptual design of the light aircraft for Mars atmosphere, ALPEMA. It allows atmospheric dropping (aeroshell), as well as direct take-off from Martian surface. Complex atmosphere demanded for simplified yet efficient wing geometry, capable of maximizing Lift-to-Drag ratio. Martian atmospheric pressure, density, temperature and speed of sound variations, demand a scrutinized powerplant choice. Efficient aspect ratio and drag polar lead to optimal flight envelopes as a proof of sustainability of ALPEMA project. Special performances and basic aerodynamics provide boundaries and constraints of the project, in line with similar approaches. Chosen propeller allows for ALPEMA to use maximum power capabilities of its engine, described through V-min and V-max, which are significant inputs for flight envelope. Envelope provides effective width and profile for a variety of possible missions. ALPEMA's specific propeller and engine are a certain comparative advantage, together with its flight envelope.
PB  - Univ Osijek, Tech Fac, Slavonski Brod
T2  - Tehnički vjesnik
T1  - Conceptual Design and Flight Envelopes of a Light Aircraft for Mars Atmosphere
EP  - 381
SP  - 375
VL  - 25
DO  - 10.17559/TV-20170908130808
ER  - 

@article{
author = "Ekmedzić, Marko Z. and Bengin, Aleksandar and Rašuo, Boško",
year = "2018",
abstract = "In this paper is presented a new conceptual design of the light aircraft for Mars atmosphere, ALPEMA. It allows atmospheric dropping (aeroshell), as well as direct take-off from Martian surface. Complex atmosphere demanded for simplified yet efficient wing geometry, capable of maximizing Lift-to-Drag ratio. Martian atmospheric pressure, density, temperature and speed of sound variations, demand a scrutinized powerplant choice. Efficient aspect ratio and drag polar lead to optimal flight envelopes as a proof of sustainability of ALPEMA project. Special performances and basic aerodynamics provide boundaries and constraints of the project, in line with similar approaches. Chosen propeller allows for ALPEMA to use maximum power capabilities of its engine, described through V-min and V-max, which are significant inputs for flight envelope. Envelope provides effective width and profile for a variety of possible missions. ALPEMA's specific propeller and engine are a certain comparative advantage, together with its flight envelope.",
publisher = "Univ Osijek, Tech Fac, Slavonski Brod",
journal = "Tehnički vjesnik",
title = "Conceptual Design and Flight Envelopes of a Light Aircraft for Mars Atmosphere",
pages = "381-375",
volume = "25",
doi = "10.17559/TV-20170908130808"
}

Ekmedzić, M. Z., Bengin, A.,& Rašuo, B.. (2018). Conceptual Design and Flight Envelopes of a Light Aircraft for Mars Atmosphere. in Tehnički vjesnik
Univ Osijek, Tech Fac, Slavonski Brod., 25, 375-381.
https://doi.org/10.17559/TV-20170908130808

Ekmedzić MZ, Bengin A, Rašuo B. Conceptual Design and Flight Envelopes of a Light Aircraft for Mars Atmosphere. in Tehnički vjesnik. 2018;25:375-381.
doi:10.17559/TV-20170908130808 .

Ekmedzić, Marko Z., Bengin, Aleksandar, Rašuo, Boško, "Conceptual Design and Flight Envelopes of a Light Aircraft for Mars Atmosphere" in Tehnički vjesnik, 25 (2018):375-381,
https://doi.org/10.17559/TV-20170908130808 . .

TY  - JOUR
AU  - Linić, Suzana
AU  - Ocokoljić, Goran
AU  - Ristić, Slavica S.
AU  - Lučanin, Vojkan
AU  - Kozić, Mirko
AU  - Rašuo, Boško
AU  - Jegdić, Bore
PY  - 2018
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2792
AB  - Methods of diagnosing aerodynamic characteristics are constantly developing in order to conduct the precise and energy efficient wind tunnel testing of transport vehicles in the prototype design early stages. This is of a special importance when facing the time/cost consumption problems of detection of the transition zone over the simplified design of the high-speed train. Herein the applied thermodynamics found a very significant role in the field of experimental aerodynamics. With the intention of detecting the boundary-layer transition zone the following measurements were applied: the infrared thermography, flow visualization, and drag force measurements. In addition, the CFD was applied to predict the flow behaviour and transition zone, solving PDE consisting of the Reynolds-averaged Navier-Stokes equations, energy equation, and the equation of state for an ideal gas employing density-based solver. The thermal imaging defined the transition zone by simple application, and fast recognition, while the transition bounds were defined in the analysis. The flow visualization confirmed thermography results and the method itself as favourable, especially in the most expensive early phases of redesigning for aerodynamically optimized and energy efficient solutions. The numerical method was confirmed by the experiments, resulting in acceptable differences in the definition of the transition zone. For a better understanding of the phenomenon, the overlapped implementation of the presented methods focused on forced convection showed as the best solution. Based on the experiences of this research, development of the additional equipment and adjustments will be introduced in the future experiments.
PB  - Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd
T2  - Thermal Science
T1  - Boundary-layer transition detection by thermography and numerical method around bionic train model in wind tunnel test
EP  - 1148
IS  - 2
SP  - 1137
VL  - 22
DO  - 10.2298/TSCI170619302L
ER  - 

@article{
author = "Linić, Suzana and Ocokoljić, Goran and Ristić, Slavica S. and Lučanin, Vojkan and Kozić, Mirko and Rašuo, Boško and Jegdić, Bore",
year = "2018",
abstract = "Methods of diagnosing aerodynamic characteristics are constantly developing in order to conduct the precise and energy efficient wind tunnel testing of transport vehicles in the prototype design early stages. This is of a special importance when facing the time/cost consumption problems of detection of the transition zone over the simplified design of the high-speed train. Herein the applied thermodynamics found a very significant role in the field of experimental aerodynamics. With the intention of detecting the boundary-layer transition zone the following measurements were applied: the infrared thermography, flow visualization, and drag force measurements. In addition, the CFD was applied to predict the flow behaviour and transition zone, solving PDE consisting of the Reynolds-averaged Navier-Stokes equations, energy equation, and the equation of state for an ideal gas employing density-based solver. The thermal imaging defined the transition zone by simple application, and fast recognition, while the transition bounds were defined in the analysis. The flow visualization confirmed thermography results and the method itself as favourable, especially in the most expensive early phases of redesigning for aerodynamically optimized and energy efficient solutions. The numerical method was confirmed by the experiments, resulting in acceptable differences in the definition of the transition zone. For a better understanding of the phenomenon, the overlapped implementation of the presented methods focused on forced convection showed as the best solution. Based on the experiences of this research, development of the additional equipment and adjustments will be introduced in the future experiments.",
publisher = "Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd",
journal = "Thermal Science",
title = "Boundary-layer transition detection by thermography and numerical method around bionic train model in wind tunnel test",
pages = "1148-1137",
number = "2",
volume = "22",
doi = "10.2298/TSCI170619302L"
}

Linić, S., Ocokoljić, G., Ristić, S. S., Lučanin, V., Kozić, M., Rašuo, B.,& Jegdić, B.. (2018). Boundary-layer transition detection by thermography and numerical method around bionic train model in wind tunnel test. in Thermal Science
Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd., 22(2), 1137-1148.
https://doi.org/10.2298/TSCI170619302L

Linić S, Ocokoljić G, Ristić SS, Lučanin V, Kozić M, Rašuo B, Jegdić B. Boundary-layer transition detection by thermography and numerical method around bionic train model in wind tunnel test. in Thermal Science. 2018;22(2):1137-1148.
doi:10.2298/TSCI170619302L .

Linić, Suzana, Ocokoljić, Goran, Ristić, Slavica S., Lučanin, Vojkan, Kozić, Mirko, Rašuo, Boško, Jegdić, Bore, "Boundary-layer transition detection by thermography and numerical method around bionic train model in wind tunnel test" in Thermal Science, 22, no. 2 (2018):1137-1148,
https://doi.org/10.2298/TSCI170619302L . .

TY  - JOUR
AU  - Dančuo, Zorana
AU  - Rašuo, Boško
AU  - Bengin, Aleksandar
AU  - Željković, Vladimir
PY  - 2018
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2836
AB  - Ovo istraživanje ima za cilj da doprinese slanju prve ljudske posade na Mars. U radu je simulirana anvelopa leta na Marsa u centrifugi visokih performansi. Visoka G-opterećenja prilikom poletanja, iskustvo nulte i mikrogravitacije, može rezultirati mnogim psiho-fiziološkim poremećajima kod astronauta. Ovo uslovljava potrebu za posebnim protokolima obuke. Predložena je anvelopa leta za prvu ljudsku misiju na Mars i simulirana u funkciji G-opterećenja. U radu su predloženi profili obuke. Poseban akcenat je stavljen na fazu lansiranja sa zemlje, kao i na fazu ponovnog ulaska i sletanja. Ponovni ulazak može biti posebno opasan, uz mnogo veća ubrzanja. Precizna simulacija zahteva pravilno podešavanje rotacionih uglova centrifuge. Prilagođavanje uglova se vrši u cilju smanjenja bočnih i poprečnih G-opterećenja. Ova studija će, nadamo se, pomoći da se čovečanstvo približi snu “Ljudi na Marsu”.
AB  - This research is an effort to contribute to the human exploration of Mars by simulating phases of the Mars flight envelope in a high performance human centrifuge. The crushing sensation experienced at high-G levels during take-off, the experience of zero and microgravity, can result in many psycho-problems to astronauts, obviating the need for realistic training protocols. The flight envelope for the first manned mission to Mars is proposed, and simulated in terms of G- load. Some training profile suggestions are given. A special emphasis is placed on the Earth launch phase, and on the Earth re-entry and landing phase. Re-entry can be especially dangerous with much higher accelerations. Accurate simulation requires a proper adjustment of rotational angles of the centrifuge. Angle adjustments are made in order to minimize side-Gy and transverse-Gx load. This study will hopefully help to move faster towards the dream of “Humans on Mars”.
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Let na Mars - simulacija anvelope u centrifugi visokih performansi na zemlji
T1  - Flight to Mars: Envelope simulation in a ground based high-performance human centrifuge
EP  - 9
IS  - 1
SP  - 1
VL  - 46
DO  - 10.5937/fmet1801001D
ER  - 

@article{
author = "Dančuo, Zorana and Rašuo, Boško and Bengin, Aleksandar and Željković, Vladimir",
year = "2018",
abstract = "Ovo istraživanje ima za cilj da doprinese slanju prve ljudske posade na Mars. U radu je simulirana anvelopa leta na Marsa u centrifugi visokih performansi. Visoka G-opterećenja prilikom poletanja, iskustvo nulte i mikrogravitacije, može rezultirati mnogim psiho-fiziološkim poremećajima kod astronauta. Ovo uslovljava potrebu za posebnim protokolima obuke. Predložena je anvelopa leta za prvu ljudsku misiju na Mars i simulirana u funkciji G-opterećenja. U radu su predloženi profili obuke. Poseban akcenat je stavljen na fazu lansiranja sa zemlje, kao i na fazu ponovnog ulaska i sletanja. Ponovni ulazak može biti posebno opasan, uz mnogo veća ubrzanja. Precizna simulacija zahteva pravilno podešavanje rotacionih uglova centrifuge. Prilagođavanje uglova se vrši u cilju smanjenja bočnih i poprečnih G-opterećenja. Ova studija će, nadamo se, pomoći da se čovečanstvo približi snu “Ljudi na Marsu”., This research is an effort to contribute to the human exploration of Mars by simulating phases of the Mars flight envelope in a high performance human centrifuge. The crushing sensation experienced at high-G levels during take-off, the experience of zero and microgravity, can result in many psycho-problems to astronauts, obviating the need for realistic training protocols. The flight envelope for the first manned mission to Mars is proposed, and simulated in terms of G- load. Some training profile suggestions are given. A special emphasis is placed on the Earth launch phase, and on the Earth re-entry and landing phase. Re-entry can be especially dangerous with much higher accelerations. Accurate simulation requires a proper adjustment of rotational angles of the centrifuge. Angle adjustments are made in order to minimize side-Gy and transverse-Gx load. This study will hopefully help to move faster towards the dream of “Humans on Mars”.",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Let na Mars - simulacija anvelope u centrifugi visokih performansi na zemlji, Flight to Mars: Envelope simulation in a ground based high-performance human centrifuge",
pages = "9-1",
number = "1",
volume = "46",
doi = "10.5937/fmet1801001D"
}

Dančuo, Z., Rašuo, B., Bengin, A.,& Željković, V.. (2018). Let na Mars - simulacija anvelope u centrifugi visokih performansi na zemlji. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 46(1), 1-9.
https://doi.org/10.5937/fmet1801001D

Dančuo Z, Rašuo B, Bengin A, Željković V. Let na Mars - simulacija anvelope u centrifugi visokih performansi na zemlji. in FME Transactions. 2018;46(1):1-9.
doi:10.5937/fmet1801001D .

Dančuo, Zorana, Rašuo, Boško, Bengin, Aleksandar, Željković, Vladimir, "Let na Mars - simulacija anvelope u centrifugi visokih performansi na zemlji" in FME Transactions, 46, no. 1 (2018):1-9,
https://doi.org/10.5937/fmet1801001D . .

TY  - JOUR
AU  - Kastratović, Gordana
AU  - Vidanović, Nenad
AU  - Grbović, Aleksandar
AU  - Rašuo, Boško
PY  - 2018
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2799
AB  - U ovom radu korišćena je jednostavna aproksimativna metoda za procenu faktora intenziteta napona za mod I tip opterećenja, i to u slučaju višestrukih površinskih prslina u trodimenzionalnom elastičnom telu, koje je podvrgnuto udaljenom jednoosnom opterećenju. Navedena metoda koristi poznata rešenja za 2D ili 3D konfiguracije koje sadrže samo jednu prslinu i uzima u obzir efekat interakcije između istih. Ova metoda, inače zasnovana na principu super-pozicije, konkretno je primenjena na konfiguraciji sa tri koplanarne polueliptične prsline koje su umetnute u trodimenzionalno elastično telo, a koje je podvrgnuto udaljenom jednoosnom naponu na zatezanje. Sve prsline se nalaze u istoj ravni na istim rastojanjima, u sredini tela, a primenjeni napon je upravan na ravan u kojoj prsline leže. Za potrebe verifikacije, faktori intenziteta napona su određenii pomoću kompjuterskog programa baziranog na metodi konačnih elemenata. Sprovedena analiza pokazala je da je aproksimativna metoda pre svega brz i efikasan alat za procenu faktora intenziteta napona čak i u slučaju 3D konfiguracija sa višestrukim prslinama. Poređenje rezultata pokazalo je i značaj preciznog izračunavanja faktora intenziteta napona, kako bi se omogućilo bolje razumevanje i predviđanje širenja 3D prslina.
AB  - In this paper a versatile and easy to use approximate procedure was used for the estimation of mode I stress intensity factors in case of multiple surface cracks in a three dimensional elastic body, subjected to remote uniaxial tensile loading. The mentioned method uses known solutions for either 2D or 3D configurations containing only one crack, and takes into consideration the interaction effect between cracks. This procedure, which is based on the principle of superposition, was applied on a configuration with three coplanar semi-elliptical cracks embedded in three dimensional elastic body, subjected to remote uniaxial tensile loading. All cracks are located in the same plane at the same distances, in the middle of the body and the applied stress is perpendicular to the cracks plane. For the verification purposes, the stress intensity factors solutions were obtained by using finite element method based computer program. The conducted analysis showed that approximate method is, above all, fast and efficient tool for stress intensity factors assessment even in the case of 3D configurations with multiple site damage. The comparison between results also showed the significance of accurate calculation of stress intensity factors, in order to provide a better understanding and prediction of 3D multiple cracks propagation.
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Aproksimativno određivanje faktora intenziteta napona za slučaj višestrukih površinskih prslina
T1  - Approximate determination of stress intensity factor for multiple surface cracks
EP  - 45
IS  - 1
SP  - 39
VL  - 46
DO  - 10.5937/fmet1801039K
ER  - 

@article{
author = "Kastratović, Gordana and Vidanović, Nenad and Grbović, Aleksandar and Rašuo, Boško",
year = "2018",
abstract = "U ovom radu korišćena je jednostavna aproksimativna metoda za procenu faktora intenziteta napona za mod I tip opterećenja, i to u slučaju višestrukih površinskih prslina u trodimenzionalnom elastičnom telu, koje je podvrgnuto udaljenom jednoosnom opterećenju. Navedena metoda koristi poznata rešenja za 2D ili 3D konfiguracije koje sadrže samo jednu prslinu i uzima u obzir efekat interakcije između istih. Ova metoda, inače zasnovana na principu super-pozicije, konkretno je primenjena na konfiguraciji sa tri koplanarne polueliptične prsline koje su umetnute u trodimenzionalno elastično telo, a koje je podvrgnuto udaljenom jednoosnom naponu na zatezanje. Sve prsline se nalaze u istoj ravni na istim rastojanjima, u sredini tela, a primenjeni napon je upravan na ravan u kojoj prsline leže. Za potrebe verifikacije, faktori intenziteta napona su određenii pomoću kompjuterskog programa baziranog na metodi konačnih elemenata. Sprovedena analiza pokazala je da je aproksimativna metoda pre svega brz i efikasan alat za procenu faktora intenziteta napona čak i u slučaju 3D konfiguracija sa višestrukim prslinama. Poređenje rezultata pokazalo je i značaj preciznog izračunavanja faktora intenziteta napona, kako bi se omogućilo bolje razumevanje i predviđanje širenja 3D prslina., In this paper a versatile and easy to use approximate procedure was used for the estimation of mode I stress intensity factors in case of multiple surface cracks in a three dimensional elastic body, subjected to remote uniaxial tensile loading. The mentioned method uses known solutions for either 2D or 3D configurations containing only one crack, and takes into consideration the interaction effect between cracks. This procedure, which is based on the principle of superposition, was applied on a configuration with three coplanar semi-elliptical cracks embedded in three dimensional elastic body, subjected to remote uniaxial tensile loading. All cracks are located in the same plane at the same distances, in the middle of the body and the applied stress is perpendicular to the cracks plane. For the verification purposes, the stress intensity factors solutions were obtained by using finite element method based computer program. The conducted analysis showed that approximate method is, above all, fast and efficient tool for stress intensity factors assessment even in the case of 3D configurations with multiple site damage. The comparison between results also showed the significance of accurate calculation of stress intensity factors, in order to provide a better understanding and prediction of 3D multiple cracks propagation.",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Aproksimativno određivanje faktora intenziteta napona za slučaj višestrukih površinskih prslina, Approximate determination of stress intensity factor for multiple surface cracks",
pages = "45-39",
number = "1",
volume = "46",
doi = "10.5937/fmet1801039K"
}

Kastratović, G., Vidanović, N., Grbović, A.,& Rašuo, B.. (2018). Aproksimativno određivanje faktora intenziteta napona za slučaj višestrukih površinskih prslina. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 46(1), 39-45.
https://doi.org/10.5937/fmet1801039K

Kastratović G, Vidanović N, Grbović A, Rašuo B. Aproksimativno određivanje faktora intenziteta napona za slučaj višestrukih površinskih prslina. in FME Transactions. 2018;46(1):39-45.
doi:10.5937/fmet1801039K .

Kastratović, Gordana, Vidanović, Nenad, Grbović, Aleksandar, Rašuo, Boško, "Aproksimativno određivanje faktora intenziteta napona za slučaj višestrukih površinskih prslina" in FME Transactions, 46, no. 1 (2018):39-45,
https://doi.org/10.5937/fmet1801039K . .

TY  - JOUR
AU  - Jeremić, Olivera
AU  - Milinović, Momčilo
AU  - Marković, Miloš
AU  - Rašuo, Boško
PY  - 2017
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2506
AB  - Ovaj rad predstavlja analitički i numerički pristup procenu performansi brzine za Eksplozivno Formirane Projektile (EFP). Predložene analitičke metode matematički razvijaju parametre brzina pojedinačnih segmenata za EFP disk pogonjen eksplozivnim procesom. Ovaj model baziran je na dobro poznatim teorijskim pristupima distribucije energije na plastičnim telima u dinamičkim uslovima formiranjem integralnih rešenja za konačnu brzinu projektila. Paralelno sa analitičkim takođe je razvijen i numerički metod u cilju obezbeđenja procene ponašanje projktila u toku vrmena procesa formiranja EFP-a pogonjenog eksplozivom. Oba modela su validna za procenu performansi EFP bojevih glava i projektnih podatka za optimalno projektivanje oblika EFP-a. Simulacije su podržane softverima Matlob i Autodin kako za ananlitičko tako i numeričko modeliranje. Dobijeni numerički i analitički rezultati upoređeni su sa raspoloživivim eksperimentalnim rezultatima. PR Projekat Ministarstva nauke Republike Srbije, br. III-47029.
AB  - The current paper presents analytical and numerical approaches of velocity performances estimations for the EFP (Explosively Formed Projectiles). The proposed analytical methods mathematically develop velocities parameters of a particular segment for EFP liner propelled by explosive process. This model is based on the well-known theoretical approaches of energy distribution on plastic body in dynamical conditions providing integral solution for projectile final velocity. The redundant to analytical, the numerical method is also developed, to provides estimations about behavior of projectile vs. time in the EFP forming process powered by explosion. Both models are valid for performances estimations of EFP warheads and design data for optimal EFP configuration. Simulations are supported by the software Matlab and Autodyn for analytical and numerical modeling respectively. The obtained numerical and analytical results are compared with the available experimental data.
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Analitička i numerička metoda polja brzine za eksplozivno formirane projektile
T1  - Analytical and numerical method of velocity fields for the explosively formed projectiles
EP  - 44
IS  - 1
SP  - 38
VL  - 45
DO  - 10.5937/fmet1701038J
ER  - 

@article{
author = "Jeremić, Olivera and Milinović, Momčilo and Marković, Miloš and Rašuo, Boško",
year = "2017",
abstract = "Ovaj rad predstavlja analitički i numerički pristup procenu performansi brzine za Eksplozivno Formirane Projektile (EFP). Predložene analitičke metode matematički razvijaju parametre brzina pojedinačnih segmenata za EFP disk pogonjen eksplozivnim procesom. Ovaj model baziran je na dobro poznatim teorijskim pristupima distribucije energije na plastičnim telima u dinamičkim uslovima formiranjem integralnih rešenja za konačnu brzinu projektila. Paralelno sa analitičkim takođe je razvijen i numerički metod u cilju obezbeđenja procene ponašanje projktila u toku vrmena procesa formiranja EFP-a pogonjenog eksplozivom. Oba modela su validna za procenu performansi EFP bojevih glava i projektnih podatka za optimalno projektivanje oblika EFP-a. Simulacije su podržane softverima Matlob i Autodin kako za ananlitičko tako i numeričko modeliranje. Dobijeni numerički i analitički rezultati upoređeni su sa raspoloživivim eksperimentalnim rezultatima. PR Projekat Ministarstva nauke Republike Srbije, br. III-47029., The current paper presents analytical and numerical approaches of velocity performances estimations for the EFP (Explosively Formed Projectiles). The proposed analytical methods mathematically develop velocities parameters of a particular segment for EFP liner propelled by explosive process. This model is based on the well-known theoretical approaches of energy distribution on plastic body in dynamical conditions providing integral solution for projectile final velocity. The redundant to analytical, the numerical method is also developed, to provides estimations about behavior of projectile vs. time in the EFP forming process powered by explosion. Both models are valid for performances estimations of EFP warheads and design data for optimal EFP configuration. Simulations are supported by the software Matlab and Autodyn for analytical and numerical modeling respectively. The obtained numerical and analytical results are compared with the available experimental data.",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Analitička i numerička metoda polja brzine za eksplozivno formirane projektile, Analytical and numerical method of velocity fields for the explosively formed projectiles",
pages = "44-38",
number = "1",
volume = "45",
doi = "10.5937/fmet1701038J"
}

Jeremić, O., Milinović, M., Marković, M.,& Rašuo, B.. (2017). Analitička i numerička metoda polja brzine za eksplozivno formirane projektile. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 45(1), 38-44.
https://doi.org/10.5937/fmet1701038J

Jeremić O, Milinović M, Marković M, Rašuo B. Analitička i numerička metoda polja brzine za eksplozivno formirane projektile. in FME Transactions. 2017;45(1):38-44.
doi:10.5937/fmet1701038J .

Jeremić, Olivera, Milinović, Momčilo, Marković, Miloš, Rašuo, Boško, "Analitička i numerička metoda polja brzine za eksplozivno formirane projektile" in FME Transactions, 45, no. 1 (2017):38-44,
https://doi.org/10.5937/fmet1701038J . .

TY  - JOUR
AU  - Petrašinović, Nikola
AU  - Petrašinović, Danilo
AU  - Rašuo, Boško
AU  - Milković, Dragan
PY  - 2017
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2597
AB  - U radu je prikazana eksperimentalna analiza širenja zamorne prsline u strukturalnom delu vazduhoplovne konstrukcije pod cikličnim opterećenjem. Cilj eksperimentalne analize je da se odredi stvarni zamorni vek ramenjače napravljene od aluminijuma 2024-T3. Ispitna instalacija, za ispitivanje zamornih karakteristika vazduhoplovnih konstrukcija, sopstvene izrade prikazana je u potpunosti. Ispitni uzorak korišćen u radu napravljen je isključivo za ispitivanje na zamor. Rezultati zamornog ispitivanja prikupljeni su najsavremenijom opremom za akviziciju podataka. Primenjena opterećenja, kao i prikupljeni rezultati su detaljno izloženi u tekstu. Na osnovu prethodno sprovedenih istraživanja, doneti su zaključci o dobijenim rezultatima eksperimentalne analize kao i uporedna analiza eksperimentalne i savremene numeričke metode. Na kraju rada date su smernice u kom pravcu bi trebala da idu dalja eksperimentalna istraživanja, koja nam pokazuju da ima smisla vršiti poređenje između realnih i numeričkih rezultata samo u situaciji gde su broj potrebnih ciklusa i ponašanje zamornih prslina isti.
AB  - Experimental fatigue crack growth analysis of the aircraft structural component subjected to different cycling loading has been presented. The purpose of the experimental test was to evaluates the fatigue behavior of the real aircraft spar, made in aluminum 2024-T3. In-house laboratory fatigue test installation is described in the paper. The spar-test specimen has been manufactured specifically for the cycling damage testing. Test results were obtained with most modern equipment for data acquisition. Applied loads and obtained spar fatigue results are described in detail. Conclusions have been made with reference to the previous work on the duraluminum spar fatigue testing. As it is presented in the previous work with advanced numerical methods for fatigue analysis, in this paper is given an opinion on the same. At the end, possible directions of the further experimental spar fatigue testing is given and shows us that it makes sense to make the comparison between real and numerical results only in situations where cracks behave similarly and the numbers of required cycles are about the same.
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Eksperimentalno određivanje zamornogh veka duraluminijumske ramenjače krila
T1  - Aircraft duraluminum wing spar fatigue testing
EP  - 536
IS  - 4
SP  - 531
VL  - 45
DO  - 10.5937/fmet1704531P
ER  - 

@article{
author = "Petrašinović, Nikola and Petrašinović, Danilo and Rašuo, Boško and Milković, Dragan",
year = "2017",
abstract = "U radu je prikazana eksperimentalna analiza širenja zamorne prsline u strukturalnom delu vazduhoplovne konstrukcije pod cikličnim opterećenjem. Cilj eksperimentalne analize je da se odredi stvarni zamorni vek ramenjače napravljene od aluminijuma 2024-T3. Ispitna instalacija, za ispitivanje zamornih karakteristika vazduhoplovnih konstrukcija, sopstvene izrade prikazana je u potpunosti. Ispitni uzorak korišćen u radu napravljen je isključivo za ispitivanje na zamor. Rezultati zamornog ispitivanja prikupljeni su najsavremenijom opremom za akviziciju podataka. Primenjena opterećenja, kao i prikupljeni rezultati su detaljno izloženi u tekstu. Na osnovu prethodno sprovedenih istraživanja, doneti su zaključci o dobijenim rezultatima eksperimentalne analize kao i uporedna analiza eksperimentalne i savremene numeričke metode. Na kraju rada date su smernice u kom pravcu bi trebala da idu dalja eksperimentalna istraživanja, koja nam pokazuju da ima smisla vršiti poređenje između realnih i numeričkih rezultata samo u situaciji gde su broj potrebnih ciklusa i ponašanje zamornih prslina isti., Experimental fatigue crack growth analysis of the aircraft structural component subjected to different cycling loading has been presented. The purpose of the experimental test was to evaluates the fatigue behavior of the real aircraft spar, made in aluminum 2024-T3. In-house laboratory fatigue test installation is described in the paper. The spar-test specimen has been manufactured specifically for the cycling damage testing. Test results were obtained with most modern equipment for data acquisition. Applied loads and obtained spar fatigue results are described in detail. Conclusions have been made with reference to the previous work on the duraluminum spar fatigue testing. As it is presented in the previous work with advanced numerical methods for fatigue analysis, in this paper is given an opinion on the same. At the end, possible directions of the further experimental spar fatigue testing is given and shows us that it makes sense to make the comparison between real and numerical results only in situations where cracks behave similarly and the numbers of required cycles are about the same.",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Eksperimentalno određivanje zamornogh veka duraluminijumske ramenjače krila, Aircraft duraluminum wing spar fatigue testing",
pages = "536-531",
number = "4",
volume = "45",
doi = "10.5937/fmet1704531P"
}

Petrašinović, N., Petrašinović, D., Rašuo, B.,& Milković, D.. (2017). Eksperimentalno određivanje zamornogh veka duraluminijumske ramenjače krila. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 45(4), 531-536.
https://doi.org/10.5937/fmet1704531P

Petrašinović N, Petrašinović D, Rašuo B, Milković D. Eksperimentalno određivanje zamornogh veka duraluminijumske ramenjače krila. in FME Transactions. 2017;45(4):531-536.
doi:10.5937/fmet1704531P .

Petrašinović, Nikola, Petrašinović, Danilo, Rašuo, Boško, Milković, Dragan, "Eksperimentalno određivanje zamornogh veka duraluminijumske ramenjače krila" in FME Transactions, 45, no. 4 (2017):531-536,
https://doi.org/10.5937/fmet1704531P . .

TY  - JOUR
AU  - Ocokoljić, Goran
AU  - Rašuo, Boško
AU  - Bengin, Aleksandar
PY  - 2017
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2601
AB  - This paper presents modcation of the existing guided missile which was done by replacing the existing front part with the new five, while the rear part of the missile with rocket motor and missile thrust vector control system remains the same. The shape of all improved front parts is completely different from the original one. Modification was performed based on required aerodynamic coefficients for the existing guided missile. The preliminary aerodynamic configurations of the improved missile front parts were designed based on theoretical and computational fluid dynamics simulations. All aerodynamic configurations were tested in the T-35 wind tunnel at the Military Technical Institute in order to determine the final geometry of the new front parts. The 3-D Reynolds averaged Navier-Stokes numerical simulations were carried out to predict the aerodynamic loads of the missile based on the finite volume method. Experimental results of the axial force, normal force, and pitching moment coefficients are presented. The computational results of the aerodynamic loads of a guided missile model are also given, and agreed well with.
PB  - Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd
T2  - Thermal Science
T1  - Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation
EP  - 1554
IS  - 3
SP  - 1543
VL  - 21
DO  - 10.2298/TSCI150515184O
ER  - 

@article{
author = "Ocokoljić, Goran and Rašuo, Boško and Bengin, Aleksandar",
year = "2017",
abstract = "This paper presents modcation of the existing guided missile which was done by replacing the existing front part with the new five, while the rear part of the missile with rocket motor and missile thrust vector control system remains the same. The shape of all improved front parts is completely different from the original one. Modification was performed based on required aerodynamic coefficients for the existing guided missile. The preliminary aerodynamic configurations of the improved missile front parts were designed based on theoretical and computational fluid dynamics simulations. All aerodynamic configurations were tested in the T-35 wind tunnel at the Military Technical Institute in order to determine the final geometry of the new front parts. The 3-D Reynolds averaged Navier-Stokes numerical simulations were carried out to predict the aerodynamic loads of the missile based on the finite volume method. Experimental results of the axial force, normal force, and pitching moment coefficients are presented. The computational results of the aerodynamic loads of a guided missile model are also given, and agreed well with.",
publisher = "Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd",
journal = "Thermal Science",
title = "Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation",
pages = "1554-1543",
number = "3",
volume = "21",
doi = "10.2298/TSCI150515184O"
}

Ocokoljić, G., Rašuo, B.,& Bengin, A.. (2017). Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation. in Thermal Science
Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd., 21(3), 1543-1554.
https://doi.org/10.2298/TSCI150515184O

Ocokoljić G, Rašuo B, Bengin A. Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation. in Thermal Science. 2017;21(3):1543-1554.
doi:10.2298/TSCI150515184O .

Ocokoljić, Goran, Rašuo, Boško, Bengin, Aleksandar, "Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation" in Thermal Science, 21, no. 3 (2017):1543-1554,
https://doi.org/10.2298/TSCI150515184O . .

TY  - JOUR
AU  - Ilić, Zoran
AU  - Rašuo, Boško
AU  - Jovanović, Miroslav
AU  - Jovicić, Stevan
AU  - Tomić, Ljubiša
AU  - Janković, Milutin
AU  - Petrašinović, Danilo
PY  - 2017
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2630
AB  - Long-term exposure to vibration adversely affects mental and physical condition of the pilot and increases body fatigue. This paper presents the results of tests dealing with the measurements of vibrations at the seat and cabin floor of the flight instructor of the piston engine propeller aircraft and other engine and flight, parameters. Two tests were conducted, one with a rubber absorber built in under the pilot seat and the other test without the absorber. The research is based on an analysis of magnitude of the vibration accelerations, at the harmonics of the engine running speed, in three flight regimes. The applied rubber absorber, with certain physical properties and mechanical characteristics, has provided the desired vibration damping on the seat in vertical direction of Z axis, in all flight profiles on Propeller Rotation Frequency and its several harmonics.
PB  - Elsevier Sci Ltd, Oxford
T2  - Measurement
T1  - The efficiency of passive vibration damping on the pilot seat of piston propeller aircraft
EP  - 32
SP  - 21
VL  - 95
DO  - 10.1016/j.measurement.2016.09.042
ER  - 

@article{
author = "Ilić, Zoran and Rašuo, Boško and Jovanović, Miroslav and Jovicić, Stevan and Tomić, Ljubiša and Janković, Milutin and Petrašinović, Danilo",
year = "2017",
abstract = "Long-term exposure to vibration adversely affects mental and physical condition of the pilot and increases body fatigue. This paper presents the results of tests dealing with the measurements of vibrations at the seat and cabin floor of the flight instructor of the piston engine propeller aircraft and other engine and flight, parameters. Two tests were conducted, one with a rubber absorber built in under the pilot seat and the other test without the absorber. The research is based on an analysis of magnitude of the vibration accelerations, at the harmonics of the engine running speed, in three flight regimes. The applied rubber absorber, with certain physical properties and mechanical characteristics, has provided the desired vibration damping on the seat in vertical direction of Z axis, in all flight profiles on Propeller Rotation Frequency and its several harmonics.",
publisher = "Elsevier Sci Ltd, Oxford",
journal = "Measurement",
title = "The efficiency of passive vibration damping on the pilot seat of piston propeller aircraft",
pages = "32-21",
volume = "95",
doi = "10.1016/j.measurement.2016.09.042"
}

Ilić, Z., Rašuo, B., Jovanović, M., Jovicić, S., Tomić, L., Janković, M.,& Petrašinović, D.. (2017). The efficiency of passive vibration damping on the pilot seat of piston propeller aircraft. in Measurement
Elsevier Sci Ltd, Oxford., 95, 21-32.
https://doi.org/10.1016/j.measurement.2016.09.042

Ilić Z, Rašuo B, Jovanović M, Jovicić S, Tomić L, Janković M, Petrašinović D. The efficiency of passive vibration damping on the pilot seat of piston propeller aircraft. in Measurement. 2017;95:21-32.
doi:10.1016/j.measurement.2016.09.042 .

Ilić, Zoran, Rašuo, Boško, Jovanović, Miroslav, Jovicić, Stevan, Tomić, Ljubiša, Janković, Milutin, Petrašinović, Danilo, "The efficiency of passive vibration damping on the pilot seat of piston propeller aircraft" in Measurement, 95 (2017):21-32,
https://doi.org/10.1016/j.measurement.2016.09.042 . .

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  - 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  - Golubović, Snežana D.
AU  - Rašuo, Boško
AU  - Lučanin, Vojkan
PY  - 2015
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2070
AB  - Povećanje konkuretnosti železničkih transportnih sistema u odnosu na druge vidove transportnih sistema u poslednjih šezdeset godina rezultat je intenzivnog razvoja novih generacija brzih vozova. Ove vrste vozova ne samo da zadovoljavaju potrebe za povećanom brzinom prevoza, a tako i kraće vreme putovanja, već i zahteve za povećanje pouzdanosti, sigurnosti i direktne primene energetske efikasnosti na sam sistem transporta. Sa povećanjem brzine vozova, povećavaju se i otpori kretanja, pri čemu pri brzinama većim od 200 km/h udeo otpora vazduha postaje najdominantniji član. Jedna od najefikasnijih mera za smanjenje otpora vazduha, kao i ostalih negativnih posledica koje nastaju pri kretanju velikim brzinama, je razvoj aerodinamičkog oblika voza. U ovom radu su predstavljena neka od konstrukcionih rešenja koja utiču na aerodinamičke karakteristike vozova velikih brzina, pre svega oblik čeonog dela, kao i sličnosti i razlike pojedinih podsistema neophodnih za funkcionisanje savremenih železničkih sisteme vozova velikih brzina. Analizirana su dva pristupa rešavanja problema aerodinamičkog oblika voza i odgovarajuće infrastructure na primeru Japana i Francuske. Razmatrana su dva modela voza velikih brzina, Shinkansen (Japan) i TGV odnosno AGV (Francuska.).
AB  - Increased advantages of railway transportation systems over other types of transportation systems in the past sixty years have been a result of an intensive development of the new generations of high-speed trains. Not only do these types of trains comply with the need for increased speed of transportation and make the duration of the journey shorter, but they also meet the demands for increased reliability, safety and direct application of energy efficiency to the transportation system itself. Along with increased train speed, the motion resistance is increased as well, whereby at speeds over 200 km/h the proportion of air resistance becomes the most dominant member. One of the most efficient measures for reducing air resistance, as well as other negative consequences of high-speed motion, is the development of the aerodynamic shape of the train. This paper presents some construction solutions that affect the aerodynamic properties of high-speed trains, first and foremost, the nose shape, as well as the similarities and differences of individual subsystems necessary for the functioning of modern high-speed rail systems. We analysed two approaches to solving the problem of the aerodynamic shape of the train and the appropriate infrastructure using the examples of Japan and France. Two models of high-speed trains, Shinkansen (Japan) and TGV, i.e. AGV (France), have been discussed.
PB  - Savez inženjera i tehničara Srbije, Beograd
T2  - Tehnika
T1  - Savremeni trendovi u dizajnu vozova velikih brzina
T1  - Modern trends in designing high-speed trains
EP  - 462
IS  - 3
SP  - 455
VL  - 70
DO  - 10.5937/tehnika1503455G
ER  - 

@article{
author = "Golubović, Snežana D. and Rašuo, Boško and Lučanin, Vojkan",
year = "2015",
abstract = "Povećanje konkuretnosti železničkih transportnih sistema u odnosu na druge vidove transportnih sistema u poslednjih šezdeset godina rezultat je intenzivnog razvoja novih generacija brzih vozova. Ove vrste vozova ne samo da zadovoljavaju potrebe za povećanom brzinom prevoza, a tako i kraće vreme putovanja, već i zahteve za povećanje pouzdanosti, sigurnosti i direktne primene energetske efikasnosti na sam sistem transporta. Sa povećanjem brzine vozova, povećavaju se i otpori kretanja, pri čemu pri brzinama većim od 200 km/h udeo otpora vazduha postaje najdominantniji član. Jedna od najefikasnijih mera za smanjenje otpora vazduha, kao i ostalih negativnih posledica koje nastaju pri kretanju velikim brzinama, je razvoj aerodinamičkog oblika voza. U ovom radu su predstavljena neka od konstrukcionih rešenja koja utiču na aerodinamičke karakteristike vozova velikih brzina, pre svega oblik čeonog dela, kao i sličnosti i razlike pojedinih podsistema neophodnih za funkcionisanje savremenih železničkih sisteme vozova velikih brzina. Analizirana su dva pristupa rešavanja problema aerodinamičkog oblika voza i odgovarajuće infrastructure na primeru Japana i Francuske. Razmatrana su dva modela voza velikih brzina, Shinkansen (Japan) i TGV odnosno AGV (Francuska.)., Increased advantages of railway transportation systems over other types of transportation systems in the past sixty years have been a result of an intensive development of the new generations of high-speed trains. Not only do these types of trains comply with the need for increased speed of transportation and make the duration of the journey shorter, but they also meet the demands for increased reliability, safety and direct application of energy efficiency to the transportation system itself. Along with increased train speed, the motion resistance is increased as well, whereby at speeds over 200 km/h the proportion of air resistance becomes the most dominant member. One of the most efficient measures for reducing air resistance, as well as other negative consequences of high-speed motion, is the development of the aerodynamic shape of the train. This paper presents some construction solutions that affect the aerodynamic properties of high-speed trains, first and foremost, the nose shape, as well as the similarities and differences of individual subsystems necessary for the functioning of modern high-speed rail systems. We analysed two approaches to solving the problem of the aerodynamic shape of the train and the appropriate infrastructure using the examples of Japan and France. Two models of high-speed trains, Shinkansen (Japan) and TGV, i.e. AGV (France), have been discussed.",
publisher = "Savez inženjera i tehničara Srbije, Beograd",
journal = "Tehnika",
title = "Savremeni trendovi u dizajnu vozova velikih brzina, Modern trends in designing high-speed trains",
pages = "462-455",
number = "3",
volume = "70",
doi = "10.5937/tehnika1503455G"
}

Golubović, S. D., Rašuo, B.,& Lučanin, V.. (2015). Savremeni trendovi u dizajnu vozova velikih brzina. in Tehnika
Savez inženjera i tehničara Srbije, Beograd., 70(3), 455-462.
https://doi.org/10.5937/tehnika1503455G

Golubović SD, Rašuo B, Lučanin V. Savremeni trendovi u dizajnu vozova velikih brzina. in Tehnika. 2015;70(3):455-462.
doi:10.5937/tehnika1503455G .

Golubović, Snežana D., Rašuo, Boško, Lučanin, Vojkan, "Savremeni trendovi u dizajnu vozova velikih brzina" in Tehnika, 70, no. 3 (2015):455-462,
https://doi.org/10.5937/tehnika1503455G . .

TY  - JOUR
AU  - Marković, Miloš
AU  - Rašuo, Boško
AU  - Milinović, Momčilo
AU  - Amine, Mohammed Boulahlib
PY  - 2014
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1974
AB  - Ciljevi ovog iztraživanja su testiranje odnosa odgovarajućih letnih performansi posredno upravljanih raketa i uslovno kreiranje njihovih taktičkih, prostornih zona i vremena gađanja tokom upotrebe na površinske ciljeve. Manevar leta, posredno daljinski upravljane rakete je testiran sa uslovno povezanim ograničenjima koja proističu iz kinematike leta sa turbomlaznim pogonom rakete i načina kretanja cilja, tipičnog za iznenadne napade. Ograničenja sposobnosti manervisanja u letu, u fazi krstarenja, su razmatrani kao modeli kretanja materijalne tačke radi kreiranja nevođenih (pretraživanja) i vođenih navigacionih kinematskih trajektorija, projektovanih po odgovarajućem zakonu navigacije. U iztraživanju je korišćen numerički metod za simuliranje kretanja posredno upravljane rakete i cilja u horizontalnoj ravni kontrolisanjem linije cilja na odgovarajućoj visini leta. Ovo generiše granice zone pogotka i zone lansiranja, uspostavljene pomoću operativnog vremena leta posredno vođenih raketa kao i mogućih varijacija mase za očekivani način borbenog leta.
AB  - The goals of this research are to test the relationships of appropriate nonline of site (NLOS) missile flight performances and conditionally created their tactical ranges, spaces zones and shooting time during employment on the surface targets. Flight maneuver of distance remote controlled NLOS missile is tested with the conditionally joint constrains coming from flight kinematics with turbo-jet engine of NLOS missile and manner of target motion, typical of rapid reaction attacks. The constraints of maneuverability and flight, in the cruise phase, are considered as the mass point motion to create both unguided (searching) and guided navigated kinematical trajectories, which was designed by the appropriate guidance law. Research used numerical methods to simulate NLOS missile and targets motions in horizontal plane by controlling line of target (LOT) referred at the appropriate flight height. This generates borders of target impact and launching areas, establishes NLOS missile operation time, as well as masses variations for the expected manner of battle flight. .
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Zone zahvata raketama u proporcionalno navođenom letu sa vazdušno reaktivnim pogonom
T1  - Engagement areas of missiles in the proportional navigated flight powered by air breathing engines
EP  - 188
IS  - 3
SP  - 181
VL  - 42
DO  - 10.5937/fmet1403181M
ER  - 

@article{
author = "Marković, Miloš and Rašuo, Boško and Milinović, Momčilo and Amine, Mohammed Boulahlib",
year = "2014",
abstract = "Ciljevi ovog iztraživanja su testiranje odnosa odgovarajućih letnih performansi posredno upravljanih raketa i uslovno kreiranje njihovih taktičkih, prostornih zona i vremena gađanja tokom upotrebe na površinske ciljeve. Manevar leta, posredno daljinski upravljane rakete je testiran sa uslovno povezanim ograničenjima koja proističu iz kinematike leta sa turbomlaznim pogonom rakete i načina kretanja cilja, tipičnog za iznenadne napade. Ograničenja sposobnosti manervisanja u letu, u fazi krstarenja, su razmatrani kao modeli kretanja materijalne tačke radi kreiranja nevođenih (pretraživanja) i vođenih navigacionih kinematskih trajektorija, projektovanih po odgovarajućem zakonu navigacije. U iztraživanju je korišćen numerički metod za simuliranje kretanja posredno upravljane rakete i cilja u horizontalnoj ravni kontrolisanjem linije cilja na odgovarajućoj visini leta. Ovo generiše granice zone pogotka i zone lansiranja, uspostavljene pomoću operativnog vremena leta posredno vođenih raketa kao i mogućih varijacija mase za očekivani način borbenog leta., The goals of this research are to test the relationships of appropriate nonline of site (NLOS) missile flight performances and conditionally created their tactical ranges, spaces zones and shooting time during employment on the surface targets. Flight maneuver of distance remote controlled NLOS missile is tested with the conditionally joint constrains coming from flight kinematics with turbo-jet engine of NLOS missile and manner of target motion, typical of rapid reaction attacks. The constraints of maneuverability and flight, in the cruise phase, are considered as the mass point motion to create both unguided (searching) and guided navigated kinematical trajectories, which was designed by the appropriate guidance law. Research used numerical methods to simulate NLOS missile and targets motions in horizontal plane by controlling line of target (LOT) referred at the appropriate flight height. This generates borders of target impact and launching areas, establishes NLOS missile operation time, as well as masses variations for the expected manner of battle flight. .",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Zone zahvata raketama u proporcionalno navođenom letu sa vazdušno reaktivnim pogonom, Engagement areas of missiles in the proportional navigated flight powered by air breathing engines",
pages = "188-181",
number = "3",
volume = "42",
doi = "10.5937/fmet1403181M"
}

Marković, M., Rašuo, B., Milinović, M.,& Amine, M. B.. (2014). Zone zahvata raketama u proporcionalno navođenom letu sa vazdušno reaktivnim pogonom. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 42(3), 181-188.
https://doi.org/10.5937/fmet1403181M

Marković M, Rašuo B, Milinović M, Amine MB. Zone zahvata raketama u proporcionalno navođenom letu sa vazdušno reaktivnim pogonom. in FME Transactions. 2014;42(3):181-188.
doi:10.5937/fmet1403181M .

Marković, Miloš, Rašuo, Boško, Milinović, Momčilo, Amine, Mohammed Boulahlib, "Zone zahvata raketama u proporcionalno navođenom letu sa vazdušno reaktivnim pogonom" in FME Transactions, 42, no. 3 (2014):181-188,
https://doi.org/10.5937/fmet1403181M . .

TY  - JOUR
AU  - Jovanović, Rastko
AU  - Cvetinović, Dejan
AU  - Erić, Milić D.
AU  - Rašuo, Boško
AU  - Adžić, Miroljub
PY  - 2014
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1949
AB  - Numerical modeling is widely used tool for prediction of combustion processes. Computational Fluid Dynamics - CFD models use three kinetic rates for description of the coal combustion processes: coal devolatilization, volatile combustion and char combustion. Reported rates for coal devolatilization vary considerably among the authors depending on the type of experimental systems used in describing the phenomenon. Accurate representation of devolatilization process is necessary in order to perform successful CFD calculations of pulverized coal combustion and gasification. The subject of this work is numerical modeling of Serbian lignite pulverized coal devolatilization in drop tube type laboratory scale reactor. The aim of this study is to evaluate the influence of different devolatilization kinetic factors on total devolatilization time in numerical modeling of pulverized Serbian lignite devolatilization. Nine different devolatilization kinetic rates mostly used in devolatilization numerical modeling are compared in the presented work.
T2  - International Journal of Heat and Mass Transfer
T1  - Sensitivity analysis of different kinetic factors for numerical modeling of Serbian lignite devolatilization process
EP  - 500
SP  - 489
VL  - 72
DO  - 10.1016/j.ijheatmasstransfer.2014.01.036
ER  - 

@article{
author = "Jovanović, Rastko and Cvetinović, Dejan and Erić, Milić D. and Rašuo, Boško and Adžić, Miroljub",
year = "2014",
abstract = "Numerical modeling is widely used tool for prediction of combustion processes. Computational Fluid Dynamics - CFD models use three kinetic rates for description of the coal combustion processes: coal devolatilization, volatile combustion and char combustion. Reported rates for coal devolatilization vary considerably among the authors depending on the type of experimental systems used in describing the phenomenon. Accurate representation of devolatilization process is necessary in order to perform successful CFD calculations of pulverized coal combustion and gasification. The subject of this work is numerical modeling of Serbian lignite pulverized coal devolatilization in drop tube type laboratory scale reactor. The aim of this study is to evaluate the influence of different devolatilization kinetic factors on total devolatilization time in numerical modeling of pulverized Serbian lignite devolatilization. Nine different devolatilization kinetic rates mostly used in devolatilization numerical modeling are compared in the presented work.",
journal = "International Journal of Heat and Mass Transfer",
title = "Sensitivity analysis of different kinetic factors for numerical modeling of Serbian lignite devolatilization process",
pages = "500-489",
volume = "72",
doi = "10.1016/j.ijheatmasstransfer.2014.01.036"
}

Jovanović, R., Cvetinović, D., Erić, M. D., Rašuo, B.,& Adžić, M.. (2014). Sensitivity analysis of different kinetic factors for numerical modeling of Serbian lignite devolatilization process. in International Journal of Heat and Mass Transfer, 72, 489-500.
https://doi.org/10.1016/j.ijheatmasstransfer.2014.01.036

Jovanović R, Cvetinović D, Erić MD, Rašuo B, Adžić M. Sensitivity analysis of different kinetic factors for numerical modeling of Serbian lignite devolatilization process. in International Journal of Heat and Mass Transfer. 2014;72:489-500.
doi:10.1016/j.ijheatmasstransfer.2014.01.036 .

Jovanović, Rastko, Cvetinović, Dejan, Erić, Milić D., Rašuo, Boško, Adžić, Miroljub, "Sensitivity analysis of different kinetic factors for numerical modeling of Serbian lignite devolatilization process" in International Journal of Heat and Mass Transfer, 72 (2014):489-500,
https://doi.org/10.1016/j.ijheatmasstransfer.2014.01.036 . .

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  - CONF
AU  - Ocokoljić, Goran
AU  - Rašuo, Boško
AU  - Bengin, Aleksandar
PY  - 2014
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1985
AB  - Wind tunnel test results of an Anti-Tank Missile model with five different warheads are presented in this paper at 0.35 Mach number and in the ±10°angle of attack range. The main goal of these experiments was to determine the final geometry among five warheads, which differs in wings geometry and wings location. Based on required aerodynamic coefficients for the existing Anti-Tank Missile, the preliminary aerodynamic configurations of the front parts (warheads) of the missile were designed based on theoretical and CFD simulation. For fine tuning and definition of the final geometry of warheads all aerodynamic configurations were tested in the T-35 subsonic wind tunnel in the Military Technical Institute. Threedimensional Reynolds averaged Navier-Stokes numerical simulations were carried out to predict the aerodynamic loads of the missile based on the finite volume method. Experimental results of the axial force, normal force and pitching moment coefficients are presented. The computational results of the aerodynamic loads of an ATM model are also given, and agreed well with.
PB  - American Institute of Aeronautics and Astronautics Inc.
C3  - 32nd AIAA Applied Aerodynamics Conference
T1  - Aerodynamic shape optimization of the front part of an anti-tank missile based on wind tunnel testing and CFD simulation
DO  - 10.2514/6.2014-3134
ER  - 

@conference{
author = "Ocokoljić, Goran and Rašuo, Boško and Bengin, Aleksandar",
year = "2014",
abstract = "Wind tunnel test results of an Anti-Tank Missile model with five different warheads are presented in this paper at 0.35 Mach number and in the ±10°angle of attack range. The main goal of these experiments was to determine the final geometry among five warheads, which differs in wings geometry and wings location. Based on required aerodynamic coefficients for the existing Anti-Tank Missile, the preliminary aerodynamic configurations of the front parts (warheads) of the missile were designed based on theoretical and CFD simulation. For fine tuning and definition of the final geometry of warheads all aerodynamic configurations were tested in the T-35 subsonic wind tunnel in the Military Technical Institute. Threedimensional Reynolds averaged Navier-Stokes numerical simulations were carried out to predict the aerodynamic loads of the missile based on the finite volume method. Experimental results of the axial force, normal force and pitching moment coefficients are presented. The computational results of the aerodynamic loads of an ATM model are also given, and agreed well with.",
publisher = "American Institute of Aeronautics and Astronautics Inc.",
journal = "32nd AIAA Applied Aerodynamics Conference",
title = "Aerodynamic shape optimization of the front part of an anti-tank missile based on wind tunnel testing and CFD simulation",
doi = "10.2514/6.2014-3134"
}

Ocokoljić, G., Rašuo, B.,& Bengin, A.. (2014). Aerodynamic shape optimization of the front part of an anti-tank missile based on wind tunnel testing and CFD simulation. in 32nd AIAA Applied Aerodynamics Conference
American Institute of Aeronautics and Astronautics Inc...
https://doi.org/10.2514/6.2014-3134

Ocokoljić G, Rašuo B, Bengin A. Aerodynamic shape optimization of the front part of an anti-tank missile based on wind tunnel testing and CFD simulation. in 32nd AIAA Applied Aerodynamics Conference. 2014;.
doi:10.2514/6.2014-3134 .

Ocokoljić, Goran, Rašuo, Boško, Bengin, Aleksandar, "Aerodynamic shape optimization of the front part of an anti-tank missile based on wind tunnel testing and CFD simulation" in 32nd AIAA Applied Aerodynamics Conference (2014),
https://doi.org/10.2514/6.2014-3134 . .

TY  - CHAP
AU  - Grbović, Aleksandar
AU  - Rašuo, Boško
PY  - 2014
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1978
AB  - In this chapter, FEM is used for fatigue crack growth predictions on 2D model of the spar, whereas XFEM is used for fatigue crack growth predictions and fatigue life estimation of corresponding 3D model. The values of stress intensity factors (SIFs) are extracted from FRANC2D software and MorfeoCrack for Abaqus add-on. The results obtained corresponded well with the experimental values, which proves that numerical methods can be successfully used in the determination of proper inspection intervals for the purpose of preventing the catastrophic failure of structural components under variable amplitude loading.
PB  - Nova Science Publishers, Inc.
T2  - Recent Trends in Fatigue Design
T1  - Use of modern numerical methods for fatigue life predictions
EP  - 73
SP  - 31
UR  - https://hdl.handle.net/21.15107/rcub_machinery_1978
ER  - 

@inbook{
author = "Grbović, Aleksandar and Rašuo, Boško",
year = "2014",
abstract = "In this chapter, FEM is used for fatigue crack growth predictions on 2D model of the spar, whereas XFEM is used for fatigue crack growth predictions and fatigue life estimation of corresponding 3D model. The values of stress intensity factors (SIFs) are extracted from FRANC2D software and MorfeoCrack for Abaqus add-on. The results obtained corresponded well with the experimental values, which proves that numerical methods can be successfully used in the determination of proper inspection intervals for the purpose of preventing the catastrophic failure of structural components under variable amplitude loading.",
publisher = "Nova Science Publishers, Inc.",
journal = "Recent Trends in Fatigue Design",
booktitle = "Use of modern numerical methods for fatigue life predictions",
pages = "73-31",
url = "https://hdl.handle.net/21.15107/rcub_machinery_1978"
}

Grbović, A.,& Rašuo, B.. (2014). Use of modern numerical methods for fatigue life predictions. in Recent Trends in Fatigue Design
Nova Science Publishers, Inc.., 31-73.
https://hdl.handle.net/21.15107/rcub_machinery_1978

Grbović A, Rašuo B. Use of modern numerical methods for fatigue life predictions. in Recent Trends in Fatigue Design. 2014;:31-73.
https://hdl.handle.net/21.15107/rcub_machinery_1978 .

Grbović, Aleksandar, Rašuo, Boško, "Use of modern numerical methods for fatigue life predictions" in Recent Trends in Fatigue Design (2014):31-73,
https://hdl.handle.net/21.15107/rcub_machinery_1978 .