TY  - JOUR
AU  - Baloš, Sebastian
AU  - Radisavljević, Igor
AU  - Rajnović, Dragan
AU  - Janjatović, P.
AU  - Dramićanin, Miroslav 
AU  - Erić-Cekić, Olivera
AU  - Šiđanin, Leposava
PY  - 2019
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3043
AB  - In this study, the performance of austempered compacted graphite iron was evaluated to find its suitability as perforated plates used in add-on armour. Perforated compacted graphite plates were subjected to austenitisation at 900 degrees C for 2 h followed by austempering at 275 and 400 degrees C for 1 h. The basic plate was fixed at 400 mm away from the perforated plate and armour and then piercing incendiary projectile was shot from a distance of 100 m. It was observed that both 7 mm and 9 mm perforated plates austempered at lower temperature of 275 degrees C producing higher hardness and lower ductility were effective in fracturing the penetrating core, thereby significantly decreasing the chances of penetrating the basic plate.
PB  - Defence Scientific Information Documentation Centre, Delhi
T2  - Defence Science Journal
T1  - Ballistic Behaviour of Austempered Compacted Graphite Iron Perforated Plates
EP  - 576
IS  - 6
SP  - 571
VL  - 69
DO  - 10.14429/dsj.69.14010
ER  - 

@article{
author = "Baloš, Sebastian and Radisavljević, Igor and Rajnović, Dragan and Janjatović, P. and Dramićanin, Miroslav  and Erić-Cekić, Olivera and Šiđanin, Leposava",
year = "2019",
abstract = "In this study, the performance of austempered compacted graphite iron was evaluated to find its suitability as perforated plates used in add-on armour. Perforated compacted graphite plates were subjected to austenitisation at 900 degrees C for 2 h followed by austempering at 275 and 400 degrees C for 1 h. The basic plate was fixed at 400 mm away from the perforated plate and armour and then piercing incendiary projectile was shot from a distance of 100 m. It was observed that both 7 mm and 9 mm perforated plates austempered at lower temperature of 275 degrees C producing higher hardness and lower ductility were effective in fracturing the penetrating core, thereby significantly decreasing the chances of penetrating the basic plate.",
publisher = "Defence Scientific Information Documentation Centre, Delhi",
journal = "Defence Science Journal",
title = "Ballistic Behaviour of Austempered Compacted Graphite Iron Perforated Plates",
pages = "576-571",
number = "6",
volume = "69",
doi = "10.14429/dsj.69.14010"
}

Baloš, S., Radisavljević, I., Rajnović, D., Janjatović, P., Dramićanin, M., Erić-Cekić, O.,& Šiđanin, L.. (2019). Ballistic Behaviour of Austempered Compacted Graphite Iron Perforated Plates. in Defence Science Journal
Defence Scientific Information Documentation Centre, Delhi., 69(6), 571-576.
https://doi.org/10.14429/dsj.69.14010

Baloš S, Radisavljević I, Rajnović D, Janjatović P, Dramićanin M, Erić-Cekić O, Šiđanin L. Ballistic Behaviour of Austempered Compacted Graphite Iron Perforated Plates. in Defence Science Journal. 2019;69(6):571-576.
doi:10.14429/dsj.69.14010 .

Baloš, Sebastian, Radisavljević, Igor, Rajnović, Dragan, Janjatović, P., Dramićanin, Miroslav , Erić-Cekić, Olivera, Šiđanin, Leposava, "Ballistic Behaviour of Austempered Compacted Graphite Iron Perforated Plates" in Defence Science Journal, 69, no. 6 (2019):571-576,
https://doi.org/10.14429/dsj.69.14010 . .

TY  - JOUR
AU  - Rakić, Slavko N.
AU  - Bugarić, Uglješa
AU  - Radisavljević, Igor
AU  - Bulatović, Željko
PY  - 2017
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3931
AB  - This paper presents failure analysis of the connecting rod used in a 12-cylinder diesel engine set on a special vehicle. The fracture of the connecting rod occurred during the engine test in laboratory conditions. Chemical and metallographic analysis as well as mechanical testing have confirmed that the material properties of the connecting rod met the requirements of standard specification and technical documentation. Linear finite element (FE) analysis was performed to evaluate stress state of the connecting rod under maximum load. The results of FE analysis showed that the position of the fracture is consistent with the zone of highest stress. Fractographic analysis has not been able to reveal the main cause of mechanism of fracture due to substantially damaged fracture surface. Inadequate machining, absence of polishing and highest stress in the region of fracture were identified as the main causes of failure. Finally, the engine had been working at maximum load for a longer period of time that also led to the breakage of the connecting rod.
PB  - Pergamon-Elsevier Science Ltd, Oxford
T2  - Engineering Failure Analysis
T1  - Failure analysis of a special vehicle engine connecting rod
EP  - 109
SP  - 98
VL  - 79
DO  - 10.1016/j.engfailanal.2017.04.014
ER  - 

@article{
author = "Rakić, Slavko N. and Bugarić, Uglješa and Radisavljević, Igor and Bulatović, Željko",
year = "2017",
abstract = "This paper presents failure analysis of the connecting rod used in a 12-cylinder diesel engine set on a special vehicle. The fracture of the connecting rod occurred during the engine test in laboratory conditions. Chemical and metallographic analysis as well as mechanical testing have confirmed that the material properties of the connecting rod met the requirements of standard specification and technical documentation. Linear finite element (FE) analysis was performed to evaluate stress state of the connecting rod under maximum load. The results of FE analysis showed that the position of the fracture is consistent with the zone of highest stress. Fractographic analysis has not been able to reveal the main cause of mechanism of fracture due to substantially damaged fracture surface. Inadequate machining, absence of polishing and highest stress in the region of fracture were identified as the main causes of failure. Finally, the engine had been working at maximum load for a longer period of time that also led to the breakage of the connecting rod.",
publisher = "Pergamon-Elsevier Science Ltd, Oxford",
journal = "Engineering Failure Analysis",
title = "Failure analysis of a special vehicle engine connecting rod",
pages = "109-98",
volume = "79",
doi = "10.1016/j.engfailanal.2017.04.014"
}

Rakić, S. N., Bugarić, U., Radisavljević, I.,& Bulatović, Ž.. (2017). Failure analysis of a special vehicle engine connecting rod. in Engineering Failure Analysis
Pergamon-Elsevier Science Ltd, Oxford., 79, 98-109.
https://doi.org/10.1016/j.engfailanal.2017.04.014

Rakić SN, Bugarić U, Radisavljević I, Bulatović Ž. Failure analysis of a special vehicle engine connecting rod. in Engineering Failure Analysis. 2017;79:98-109.
doi:10.1016/j.engfailanal.2017.04.014 .

Rakić, Slavko N., Bugarić, Uglješa, Radisavljević, Igor, Bulatović, Željko, "Failure analysis of a special vehicle engine connecting rod" in Engineering Failure Analysis, 79 (2017):98-109,
https://doi.org/10.1016/j.engfailanal.2017.04.014 . .

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  - Baloš, Sebastian
AU  - Radisavljević, Igor
AU  - Rajnović, Dragan
AU  - Dramićanin, Miroslav 
AU  - Tabaković, Slobodan
AU  - Erić-Cekić, Olivera
AU  - Šiđanin, Leposava
PY  - 2015
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2237
AB  - In this paper, austempered ductile iron has been evaluated as an alternative to steel for perforated plates applied in the ballistic protection of military vehicles. The austempering was performed in lower and higher austempering ranges in order to obtain two types of austempered ductile iron: one with a higher strength, and the other with a higher ductility. Perforated plates having two different thicknesses of 7 and 9 mm were mounted in front of basic armour and 12.7 x 99 mm armour piercing incendiary ammunition was fired from 100 m. It was shown that the austempered ductile iron material austempered at a lower temperature has superior ballistic resistance, providing a full (five out of five armour piercing incendiary shots stopped) ballistic resistance if combined with 13 mm basic armour plate. The thicker austempered ductile iron perforated plate provides more significant penetrating core damage, and therefore, lower basic plate damage. On the other hand, the thinner austempered ductile iron material perforated plate can be considered optimal due to its lower weight and higher mass effectiveness. In austempered ductile iron material austempered at a higher temperature, besides a lower hardness, bulk retained low-carbon metastable austenite transforms into martensite through strain induced mechanism, causing a partial brittle fracture.
PB  - Elsevier Sci Ltd, Oxford
T2  - Materials & Design
T1  - Geometry, mechanical and ballistic properties of ADI material perforated plates
EP  - 74
SP  - 66
VL  - 83
DO  - 10.1016/j.matdes.2015.05.081
ER  - 

@article{
author = "Baloš, Sebastian and Radisavljević, Igor and Rajnović, Dragan and Dramićanin, Miroslav  and Tabaković, Slobodan and Erić-Cekić, Olivera and Šiđanin, Leposava",
year = "2015",
abstract = "In this paper, austempered ductile iron has been evaluated as an alternative to steel for perforated plates applied in the ballistic protection of military vehicles. The austempering was performed in lower and higher austempering ranges in order to obtain two types of austempered ductile iron: one with a higher strength, and the other with a higher ductility. Perforated plates having two different thicknesses of 7 and 9 mm were mounted in front of basic armour and 12.7 x 99 mm armour piercing incendiary ammunition was fired from 100 m. It was shown that the austempered ductile iron material austempered at a lower temperature has superior ballistic resistance, providing a full (five out of five armour piercing incendiary shots stopped) ballistic resistance if combined with 13 mm basic armour plate. The thicker austempered ductile iron perforated plate provides more significant penetrating core damage, and therefore, lower basic plate damage. On the other hand, the thinner austempered ductile iron material perforated plate can be considered optimal due to its lower weight and higher mass effectiveness. In austempered ductile iron material austempered at a higher temperature, besides a lower hardness, bulk retained low-carbon metastable austenite transforms into martensite through strain induced mechanism, causing a partial brittle fracture.",
publisher = "Elsevier Sci Ltd, Oxford",
journal = "Materials & Design",
title = "Geometry, mechanical and ballistic properties of ADI material perforated plates",
pages = "74-66",
volume = "83",
doi = "10.1016/j.matdes.2015.05.081"
}

Baloš, S., Radisavljević, I., Rajnović, D., Dramićanin, M., Tabaković, S., Erić-Cekić, O.,& Šiđanin, L.. (2015). Geometry, mechanical and ballistic properties of ADI material perforated plates. in Materials & Design
Elsevier Sci Ltd, Oxford., 83, 66-74.
https://doi.org/10.1016/j.matdes.2015.05.081

Baloš S, Radisavljević I, Rajnović D, Dramićanin M, Tabaković S, Erić-Cekić O, Šiđanin L. Geometry, mechanical and ballistic properties of ADI material perforated plates. in Materials & Design. 2015;83:66-74.
doi:10.1016/j.matdes.2015.05.081 .

Baloš, Sebastian, Radisavljević, Igor, Rajnović, Dragan, Dramićanin, Miroslav , Tabaković, Slobodan, Erić-Cekić, Olivera, Šiđanin, Leposava, "Geometry, mechanical and ballistic properties of ADI material perforated plates" in Materials & Design, 83 (2015):66-74,
https://doi.org/10.1016/j.matdes.2015.05.081 . .

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 . .