TY  - JOUR
AU  - Šalinić, Slaviša
AU  - Obradović, Aleksandar
AU  - Tomović, Aleksandar
AU  - Trifković, Dragan
AU  - Grbović, Aleksandar
PY  - 2023
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/6802
AB  - The coupled axial-bending vibration of an axially functionally graded Timoshenko cantilever beam
of non-uniform cross-section is considered. The coupling phenomenon appears due to the presence of the transverse eccentricity of the mass centre of a rigid body attached to the beam free end. To study the coupled phenomenon, an approach based on the symbolic-numeric method of initial parameters is proposed. The influence of the transverse eccentricity on the cantilever beam natural frequencies and mode shapes is examined. The approach has the potential to be also applied to vibration problems of the systems composed of rigid bodies interconnected by non-uniform non-homogeneous beams.
PB  - Springer
T2  - Meccanica
T1  - Coupled axial-bending vibration of axially functionally graded Timoshenko cantilever beams of non-uniform cross-section with an attached rigid body
UR  - https://hdl.handle.net/21.15107/rcub_machinery_6802
ER  - 

@article{
author = "Šalinić, Slaviša and Obradović, Aleksandar and Tomović, Aleksandar and Trifković, Dragan and Grbović, Aleksandar",
year = "2023",
abstract = "The coupled axial-bending vibration of an axially functionally graded Timoshenko cantilever beam
of non-uniform cross-section is considered. The coupling phenomenon appears due to the presence of the transverse eccentricity of the mass centre of a rigid body attached to the beam free end. To study the coupled phenomenon, an approach based on the symbolic-numeric method of initial parameters is proposed. The influence of the transverse eccentricity on the cantilever beam natural frequencies and mode shapes is examined. The approach has the potential to be also applied to vibration problems of the systems composed of rigid bodies interconnected by non-uniform non-homogeneous beams.",
publisher = "Springer",
journal = "Meccanica",
title = "Coupled axial-bending vibration of axially functionally graded Timoshenko cantilever beams of non-uniform cross-section with an attached rigid body",
url = "https://hdl.handle.net/21.15107/rcub_machinery_6802"
}

Šalinić, S., Obradović, A., Tomović, A., Trifković, D.,& Grbović, A.. (2023). Coupled axial-bending vibration of axially functionally graded Timoshenko cantilever beams of non-uniform cross-section with an attached rigid body. in Meccanica
Springer..
https://hdl.handle.net/21.15107/rcub_machinery_6802

Šalinić S, Obradović A, Tomović A, Trifković D, Grbović A. Coupled axial-bending vibration of axially functionally graded Timoshenko cantilever beams of non-uniform cross-section with an attached rigid body. in Meccanica. 2023;.
https://hdl.handle.net/21.15107/rcub_machinery_6802 .

Šalinić, Slaviša, Obradović, Aleksandar, Tomović, Aleksandar, Trifković, Dragan, Grbović, Aleksandar, "Coupled axial-bending vibration of axially functionally graded Timoshenko cantilever beams of non-uniform cross-section with an attached rigid body" in Meccanica (2023),
https://hdl.handle.net/21.15107/rcub_machinery_6802 .

TY  - JOUR
AU  - Dobratić, Predrag S.
AU  - Ristivojević, Mileta
AU  - Rosić, Božidar
AU  - Mitrović, Radivoje
AU  - Trifković, Dragan
PY  - 2019
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3039
AB  - The impact of geometric parameters of teeth and lubricating oils to the efficiency of involute internal spur gears, when the transverse contact ratio is 2  lt  epsilon(alpha)  lt = 3, has been analyzed in this paper. The mathematical model and computer program for determining the current and the effective value of the efficiency have been developed. The influence of the character of load distribution and energy losses due to heating effects during the meshing period is included in the factor of load distribution. The results of computer simulation are given in the form of a diagram of the current values of the efficiency during the meshing period. Also, the values of effective efficiency for the considered cylindrical gear pairs have been calculated.
PB  - Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd
T2  - Thermal Science
T1  - Mathematical model of energy efficiency in internal spur gears
EP  - S1813
SP  - S1801
VL  - 23
DO  - 10.2298/TSCI180118074D
ER  - 

@article{
author = "Dobratić, Predrag S. and Ristivojević, Mileta and Rosić, Božidar and Mitrović, Radivoje and Trifković, Dragan",
year = "2019",
abstract = "The impact of geometric parameters of teeth and lubricating oils to the efficiency of involute internal spur gears, when the transverse contact ratio is 2  lt  epsilon(alpha)  lt = 3, has been analyzed in this paper. The mathematical model and computer program for determining the current and the effective value of the efficiency have been developed. The influence of the character of load distribution and energy losses due to heating effects during the meshing period is included in the factor of load distribution. The results of computer simulation are given in the form of a diagram of the current values of the efficiency during the meshing period. Also, the values of effective efficiency for the considered cylindrical gear pairs have been calculated.",
publisher = "Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd",
journal = "Thermal Science",
title = "Mathematical model of energy efficiency in internal spur gears",
pages = "S1813-S1801",
volume = "23",
doi = "10.2298/TSCI180118074D"
}

Dobratić, P. S., Ristivojević, M., Rosić, B., Mitrović, R.,& Trifković, D.. (2019). Mathematical model of energy efficiency in internal spur gears. in Thermal Science
Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd., 23, S1801-S1813.
https://doi.org/10.2298/TSCI180118074D

Dobratić PS, Ristivojević M, Rosić B, Mitrović R, Trifković D. Mathematical model of energy efficiency in internal spur gears. in Thermal Science. 2019;23:S1801-S1813.
doi:10.2298/TSCI180118074D .

Dobratić, Predrag S., Ristivojević, Mileta, Rosić, Božidar, Mitrović, Radivoje, Trifković, Dragan, "Mathematical model of energy efficiency in internal spur gears" in Thermal Science, 23 (2019):S1801-S1813,
https://doi.org/10.2298/TSCI180118074D . .

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

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

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

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

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

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

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

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

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

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

TY  - 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  - Obradović, Aleksandar
AU  - Šalinić, Slaviša
AU  - Trifković, Dragan
AU  - Zorić, Nemanja
AU  - Stokić, Zoran
PY  - 2015
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4330
AB  - Free vibration of structures composed of rigid bodies and elastic beam segments is considered, assuming that the mass centers of rigid bodies are not located on the neutral axes of undeformed elastic beam segments. It is assumed that the rigid bodies of the system perform planar motion in the same plane and that their mass centers are located in that plane. The elastic beam segments are treated as the Euler-Bernoulli beams. In order to determine natural frequencies of the system, modification of the conventional continuous-mass transfer matrix method has been clone. The order of the overall transfer matrix has been reduced by this modification. Theoretical considerations are accompanied by two numerical examples.
PB  - Academic Press Ltd- Elsevier Science Ltd, London
T2  - Journal of Sound and Vibration
T1  - Free vibration of structures composed of rigid bodies and elastic beam segments
EP  - 138
SP  - 126
VL  - 347
DO  - 10.1016/j.jsv.2015.03.001
ER  - 

@article{
author = "Obradović, Aleksandar and Šalinić, Slaviša and Trifković, Dragan and Zorić, Nemanja and Stokić, Zoran",
year = "2015",
abstract = "Free vibration of structures composed of rigid bodies and elastic beam segments is considered, assuming that the mass centers of rigid bodies are not located on the neutral axes of undeformed elastic beam segments. It is assumed that the rigid bodies of the system perform planar motion in the same plane and that their mass centers are located in that plane. The elastic beam segments are treated as the Euler-Bernoulli beams. In order to determine natural frequencies of the system, modification of the conventional continuous-mass transfer matrix method has been clone. The order of the overall transfer matrix has been reduced by this modification. Theoretical considerations are accompanied by two numerical examples.",
publisher = "Academic Press Ltd- Elsevier Science Ltd, London",
journal = "Journal of Sound and Vibration",
title = "Free vibration of structures composed of rigid bodies and elastic beam segments",
pages = "138-126",
volume = "347",
doi = "10.1016/j.jsv.2015.03.001"
}

Obradović, A., Šalinić, S., Trifković, D., Zorić, N.,& Stokić, Z.. (2015). Free vibration of structures composed of rigid bodies and elastic beam segments. in Journal of Sound and Vibration
Academic Press Ltd- Elsevier Science Ltd, London., 347, 126-138.
https://doi.org/10.1016/j.jsv.2015.03.001

Obradović A, Šalinić S, Trifković D, Zorić N, Stokić Z. Free vibration of structures composed of rigid bodies and elastic beam segments. in Journal of Sound and Vibration. 2015;347:126-138.
doi:10.1016/j.jsv.2015.03.001 .

Obradović, Aleksandar, Šalinić, Slaviša, Trifković, Dragan, Zorić, Nemanja, Stokić, Zoran, "Free vibration of structures composed of rigid bodies and elastic beam segments" in Journal of Sound and Vibration, 347 (2015):126-138,
https://doi.org/10.1016/j.jsv.2015.03.001 . .

TY  - JOUR
AU  - Obradović, Aleksandar
AU  - Šalinić, Slaviša
AU  - Trifković, Dragan
AU  - Zorić, Nemanja
AU  - Stokić, Zoran
PY  - 2015
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2089
AB  - Free vibration of structures composed of rigid bodies and elastic beam segments is considered, assuming that the mass centers of rigid bodies are not located on the neutral axes of undeformed elastic beam segments. It is assumed that the rigid bodies of the system perform planar motion in the same plane and that their mass centers are located in that plane. The elastic beam segments are treated as the Euler-Bernoulli beams. In order to determine natural frequencies of the system, modification of the conventional continuous-mass transfer matrix method has been clone. The order of the overall transfer matrix has been reduced by this modification. Theoretical considerations are accompanied by two numerical examples.
PB  - Academic Press Ltd- Elsevier Science Ltd, London
T2  - Journal of Sound and Vibration
T1  - Free vibration of structures composed of rigid bodies and elastic beam segments
EP  - 138
SP  - 126
VL  - 347
DO  - 10.1016/j.jsv.2015.03.001
ER  - 

@article{
author = "Obradović, Aleksandar and Šalinić, Slaviša and Trifković, Dragan and Zorić, Nemanja and Stokić, Zoran",
year = "2015",
abstract = "Free vibration of structures composed of rigid bodies and elastic beam segments is considered, assuming that the mass centers of rigid bodies are not located on the neutral axes of undeformed elastic beam segments. It is assumed that the rigid bodies of the system perform planar motion in the same plane and that their mass centers are located in that plane. The elastic beam segments are treated as the Euler-Bernoulli beams. In order to determine natural frequencies of the system, modification of the conventional continuous-mass transfer matrix method has been clone. The order of the overall transfer matrix has been reduced by this modification. Theoretical considerations are accompanied by two numerical examples.",
publisher = "Academic Press Ltd- Elsevier Science Ltd, London",
journal = "Journal of Sound and Vibration",
title = "Free vibration of structures composed of rigid bodies and elastic beam segments",
pages = "138-126",
volume = "347",
doi = "10.1016/j.jsv.2015.03.001"
}

Obradović, A., Šalinić, S., Trifković, D., Zorić, N.,& Stokić, Z.. (2015). Free vibration of structures composed of rigid bodies and elastic beam segments. in Journal of Sound and Vibration
Academic Press Ltd- Elsevier Science Ltd, London., 347, 126-138.
https://doi.org/10.1016/j.jsv.2015.03.001

Obradović A, Šalinić S, Trifković D, Zorić N, Stokić Z. Free vibration of structures composed of rigid bodies and elastic beam segments. in Journal of Sound and Vibration. 2015;347:126-138.
doi:10.1016/j.jsv.2015.03.001 .

Obradović, Aleksandar, Šalinić, Slaviša, Trifković, Dragan, Zorić, Nemanja, Stokić, Zoran, "Free vibration of structures composed of rigid bodies and elastic beam segments" in Journal of Sound and Vibration, 347 (2015):126-138,
https://doi.org/10.1016/j.jsv.2015.03.001 . .

TY  - JOUR
AU  - Spasić, Dragoljub M.
AU  - Stupar, Slobodan
AU  - Simonović, Aleksandar
AU  - Trifković, Dragan
AU  - Ivanov, Toni
PY  - 2014
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1885
AB  - This paper analyzes the causes of fracture of the double pipe aerial cannon stellate starseparator, which occurred during the fighting plane mission. The linear finite element method (FEM) is used to determine the stresses that the star-shaped star-separator is subjected to during the grenade belts withdrawal and introduction into the bearing tube during gun action and under finite load, which resulted in high strains concentration of the star-separator's parts pulling the gun belt links. Therefore, in this paper we are particularly focusing on the static and dynamic behavior and the fatigue behavior of the star-separator which is an integral part of the cannon fire shutter mechanism used for the belt's withdrawal. In this study, the techniques such as numerical analysis, hardness measurement and fractographic examination were used. The testing results showed that the peel and longitudinal cracks started from the low-cycle fatigue and wear of the surface material in the thinnest area of the star-separator tooth, but without influence of the stress load.
PB  - Pergamon-Elsevier Science Ltd, Oxford
T2  - Engineering Failure Analysis
T1  - The failure analysis of the star-separator of an aircraft cannon
EP  - 86
SP  - 74
VL  - 42
DO  - 10.1016/j.engfailanal.2014.03.022
ER  - 

@article{
author = "Spasić, Dragoljub M. and Stupar, Slobodan and Simonović, Aleksandar and Trifković, Dragan and Ivanov, Toni",
year = "2014",
abstract = "This paper analyzes the causes of fracture of the double pipe aerial cannon stellate starseparator, which occurred during the fighting plane mission. The linear finite element method (FEM) is used to determine the stresses that the star-shaped star-separator is subjected to during the grenade belts withdrawal and introduction into the bearing tube during gun action and under finite load, which resulted in high strains concentration of the star-separator's parts pulling the gun belt links. Therefore, in this paper we are particularly focusing on the static and dynamic behavior and the fatigue behavior of the star-separator which is an integral part of the cannon fire shutter mechanism used for the belt's withdrawal. In this study, the techniques such as numerical analysis, hardness measurement and fractographic examination were used. The testing results showed that the peel and longitudinal cracks started from the low-cycle fatigue and wear of the surface material in the thinnest area of the star-separator tooth, but without influence of the stress load.",
publisher = "Pergamon-Elsevier Science Ltd, Oxford",
journal = "Engineering Failure Analysis",
title = "The failure analysis of the star-separator of an aircraft cannon",
pages = "86-74",
volume = "42",
doi = "10.1016/j.engfailanal.2014.03.022"
}

Spasić, D. M., Stupar, S., Simonović, A., Trifković, D.,& Ivanov, T.. (2014). The failure analysis of the star-separator of an aircraft cannon. in Engineering Failure Analysis
Pergamon-Elsevier Science Ltd, Oxford., 42, 74-86.
https://doi.org/10.1016/j.engfailanal.2014.03.022

Spasić DM, Stupar S, Simonović A, Trifković D, Ivanov T. The failure analysis of the star-separator of an aircraft cannon. in Engineering Failure Analysis. 2014;42:74-86.
doi:10.1016/j.engfailanal.2014.03.022 .

Spasić, Dragoljub M., Stupar, Slobodan, Simonović, Aleksandar, Trifković, Dragan, Ivanov, Toni, "The failure analysis of the star-separator of an aircraft cannon" in Engineering Failure Analysis, 42 (2014):74-86,
https://doi.org/10.1016/j.engfailanal.2014.03.022 . .

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

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

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

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

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

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

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

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

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

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

TY  - JOUR
AU  - Trifković, Dragan
AU  - Stupar, Slobodan
AU  - Bošnjak, Srđan
AU  - Milovančević, Milorad
AU  - Krstić, Branimir
AU  - Rajić, Zoran
AU  - Dunjić, Momčilo
PY  - 2011
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1199
AB  - This paper analyzes failure causes of the combat jet aircraft rudder shaft (RS) which occurred during the flight mission. A finite element method (FEM), utilized to determine the stress state of the RS subjected to hinge moment ultimate load, resulted in the high stress concentration sites around the rivet holes. The longitudinal crack was initiated from the corrosion pit in the zone of the rivet hole, where the fatigue beach marks were observed. The inner surface of the RS was heavily corroded. Moreover, pitting corrosion has destroyed approximately 50% of the wall thickness. Based on the presented results it was concluded that the failure of the RS had a character of fatigue combined with heavy corrosion. Therefore, it is recommended that the RS should be redesigned; the material changed into more corrosion resistant one and the maintenance procedure changed in order to avoid future similar failures.
PB  - Pergamon-Elsevier Science Ltd, Oxford
T2  - Engineering Failure Analysis
T1  - Failure analysis of the combat jet aircraft rudder shaft
EP  - 2007
IS  - 8
SP  - 1998
VL  - 18
DO  - 10.1016/j.engfailanal.2011.05.017
ER  - 

@article{
author = "Trifković, Dragan and Stupar, Slobodan and Bošnjak, Srđan and Milovančević, Milorad and Krstić, Branimir and Rajić, Zoran and Dunjić, Momčilo",
year = "2011",
abstract = "This paper analyzes failure causes of the combat jet aircraft rudder shaft (RS) which occurred during the flight mission. A finite element method (FEM), utilized to determine the stress state of the RS subjected to hinge moment ultimate load, resulted in the high stress concentration sites around the rivet holes. The longitudinal crack was initiated from the corrosion pit in the zone of the rivet hole, where the fatigue beach marks were observed. The inner surface of the RS was heavily corroded. Moreover, pitting corrosion has destroyed approximately 50% of the wall thickness. Based on the presented results it was concluded that the failure of the RS had a character of fatigue combined with heavy corrosion. Therefore, it is recommended that the RS should be redesigned; the material changed into more corrosion resistant one and the maintenance procedure changed in order to avoid future similar failures.",
publisher = "Pergamon-Elsevier Science Ltd, Oxford",
journal = "Engineering Failure Analysis",
title = "Failure analysis of the combat jet aircraft rudder shaft",
pages = "2007-1998",
number = "8",
volume = "18",
doi = "10.1016/j.engfailanal.2011.05.017"
}

Trifković, D., Stupar, S., Bošnjak, S., Milovančević, M., Krstić, B., Rajić, Z.,& Dunjić, M.. (2011). Failure analysis of the combat jet aircraft rudder shaft. in Engineering Failure Analysis
Pergamon-Elsevier Science Ltd, Oxford., 18(8), 1998-2007.
https://doi.org/10.1016/j.engfailanal.2011.05.017

Trifković D, Stupar S, Bošnjak S, Milovančević M, Krstić B, Rajić Z, Dunjić M. Failure analysis of the combat jet aircraft rudder shaft. in Engineering Failure Analysis. 2011;18(8):1998-2007.
doi:10.1016/j.engfailanal.2011.05.017 .

Trifković, Dragan, Stupar, Slobodan, Bošnjak, Srđan, Milovančević, Milorad, Krstić, Branimir, Rajić, Zoran, Dunjić, Momčilo, "Failure analysis of the combat jet aircraft rudder shaft" in Engineering Failure Analysis, 18, no. 8 (2011):1998-2007,
https://doi.org/10.1016/j.engfailanal.2011.05.017 . .

TY  - JOUR
AU  - Trifković, Dragan
AU  - Obradović, Aleksandar
PY  - 2010
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1058
AB  - U radu je prikazan postupak zamene elemenata kompleksnog torzionooscilatornog sistema brodske dizelmotorne propulzije uprošćenim ekvivalentnim elementima istih dinamičkih karakteristika. Izloženi postupak sadrži metode za određivanje ekvivalentnih dužina, krutosti i momenata inercije na osnovu jednakosti kinetičkih i potencijalnih energija realnih i ekvivalentnih elemenata sistema. Osim toga, analizirani su pobudni momenti koji izazivaju prinudne torzione oscilacije razmatranog sistema.
AB  - The procedure of replacing the elements of a complex torsional vibration system of ship diesel engine propulsion with simplified equivalent ones with the same dynamic characteristics is shown in this work. The given procedure comprises the methods for the determination of equivalent lengths, stifnesses and moments of inertia based on the equality between kinetic and potential energy of real and equivalent elements of the system. Additionally, the exciting moments which excite forced torsional vibrations of the considered system are analysed.
PB  - Univerzitet odbrane u Beogradu - Institut za naučne informacije, Beograd
T2  - Vojnotehnički glasnik
T1  - Definisanje ekvivalentnog torzionooscilatornog sistema
T1  - Determination of the equivalent torsional vibration system
EP  - 124
IS  - 3
SP  - 105
VL  - 58
DO  - 10.5937/vojtehg1003105T
ER  - 

@article{
author = "Trifković, Dragan and Obradović, Aleksandar",
year = "2010",
abstract = "U radu je prikazan postupak zamene elemenata kompleksnog torzionooscilatornog sistema brodske dizelmotorne propulzije uprošćenim ekvivalentnim elementima istih dinamičkih karakteristika. Izloženi postupak sadrži metode za određivanje ekvivalentnih dužina, krutosti i momenata inercije na osnovu jednakosti kinetičkih i potencijalnih energija realnih i ekvivalentnih elemenata sistema. Osim toga, analizirani su pobudni momenti koji izazivaju prinudne torzione oscilacije razmatranog sistema., The procedure of replacing the elements of a complex torsional vibration system of ship diesel engine propulsion with simplified equivalent ones with the same dynamic characteristics is shown in this work. The given procedure comprises the methods for the determination of equivalent lengths, stifnesses and moments of inertia based on the equality between kinetic and potential energy of real and equivalent elements of the system. Additionally, the exciting moments which excite forced torsional vibrations of the considered system are analysed.",
publisher = "Univerzitet odbrane u Beogradu - Institut za naučne informacije, Beograd",
journal = "Vojnotehnički glasnik",
title = "Definisanje ekvivalentnog torzionooscilatornog sistema, Determination of the equivalent torsional vibration system",
pages = "124-105",
number = "3",
volume = "58",
doi = "10.5937/vojtehg1003105T"
}

Trifković, D.,& Obradović, A.. (2010). Definisanje ekvivalentnog torzionooscilatornog sistema. in Vojnotehnički glasnik
Univerzitet odbrane u Beogradu - Institut za naučne informacije, Beograd., 58(3), 105-124.
https://doi.org/10.5937/vojtehg1003105T

Trifković D, Obradović A. Definisanje ekvivalentnog torzionooscilatornog sistema. in Vojnotehnički glasnik. 2010;58(3):105-124.
doi:10.5937/vojtehg1003105T .

Trifković, Dragan, Obradović, Aleksandar, "Definisanje ekvivalentnog torzionooscilatornog sistema" in Vojnotehnički glasnik, 58, no. 3 (2010):105-124,
https://doi.org/10.5937/vojtehg1003105T . .