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  - Raičević, Nikola
AU  - Petrašinović, Danilo
AU  - Grbović, Aleksandar
AU  - Petrašinović, Miloš
AU  - Balać, Martina
AU  - Petrović, Mihailo
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/6045
AB  - Wind turbines are structures that transform wind energy into other types of energy. In the modern age, wind turbines are closely related to the production of electricity and are considered starters of the green industry. Designing this type of construction is a complex and demanding process. Wind turbine
blades are the most important part of the construction and are usually made of
composite materials that meet the requirements of strength as well as aerodynamic requirements. Due to the high cost of composite materials, numerical modeling programs are very important because they allow the structure to be inspected before production, as well as to identify possible errors and weaknesses. In this way, additional manufacturing costs are avoided and a fully optimized structure is obtained. The finite element method (FEM) is a reliable method that allows the structure to be tested for the occurrence of normal and shear stresses that can lead to unwanted values of deformations on the blade. In this paper, the procedure of static analysis of a wind turbine blade is presented and the results that are important for optimizing the blade structure are analyzed. The purpose of FEM analysis is to find critical sections of the blade and to predict where maximum values of stresses may occur. In this way, it can be concluded whether the chosen material is appropriate and how the structure can be further optimized.
PB  - Springer Cham
T2  - Experimental Research and Numerical Simulation in Applied Sciences. CNNTech 2022.
T1  - The wind speed impact on stress and deformation of composite wind turbine blade
EP  - 120
SP  - 114
DO  - 10.1007/978-3-031-19499-3_6
ER  - 

@article{
author = "Raičević, Nikola and Petrašinović, Danilo and Grbović, Aleksandar and Petrašinović, Miloš and Balać, Martina and Petrović, Mihailo",
year = "2022",
abstract = "Wind turbines are structures that transform wind energy into other types of energy. In the modern age, wind turbines are closely related to the production of electricity and are considered starters of the green industry. Designing this type of construction is a complex and demanding process. Wind turbine
blades are the most important part of the construction and are usually made of
composite materials that meet the requirements of strength as well as aerodynamic requirements. Due to the high cost of composite materials, numerical modeling programs are very important because they allow the structure to be inspected before production, as well as to identify possible errors and weaknesses. In this way, additional manufacturing costs are avoided and a fully optimized structure is obtained. The finite element method (FEM) is a reliable method that allows the structure to be tested for the occurrence of normal and shear stresses that can lead to unwanted values of deformations on the blade. In this paper, the procedure of static analysis of a wind turbine blade is presented and the results that are important for optimizing the blade structure are analyzed. The purpose of FEM analysis is to find critical sections of the blade and to predict where maximum values of stresses may occur. In this way, it can be concluded whether the chosen material is appropriate and how the structure can be further optimized.",
publisher = "Springer Cham",
journal = "Experimental Research and Numerical Simulation in Applied Sciences. CNNTech 2022.",
title = "The wind speed impact on stress and deformation of composite wind turbine blade",
pages = "120-114",
doi = "10.1007/978-3-031-19499-3_6"
}

Raičević, N., Petrašinović, D., Grbović, A., Petrašinović, M., Balać, M.,& Petrović, M.. (2022). The wind speed impact on stress and deformation of composite wind turbine blade. in Experimental Research and Numerical Simulation in Applied Sciences. CNNTech 2022.
Springer Cham., 114-120.
https://doi.org/10.1007/978-3-031-19499-3_6

Raičević N, Petrašinović D, Grbović A, Petrašinović M, Balać M, Petrović M. The wind speed impact on stress and deformation of composite wind turbine blade. in Experimental Research and Numerical Simulation in Applied Sciences. CNNTech 2022.. 2022;:114-120.
doi:10.1007/978-3-031-19499-3_6 .

Raičević, Nikola, Petrašinović, Danilo, Grbović, Aleksandar, Petrašinović, Miloš, Balać, Martina, Petrović, Mihailo, "The wind speed impact on stress and deformation of composite wind turbine blade" in Experimental Research and Numerical Simulation in Applied Sciences. CNNTech 2022. (2022):114-120,
https://doi.org/10.1007/978-3-031-19499-3_6 . .

TY  - CHAP
AU  - Raičević, Nikola
AU  - Petrašinović, Danilo
AU  - Grbović, Aleksandar
AU  - Petrašinović, Miloš
AU  - Balać, Martina
AU  - Petrović, Mihailo
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/5554
AB  - Wind turbines are structures that transform wind energy into other types of energy. In the modern age, wind turbines are closely related to the production of electricity and are considered starters of the green industry. Designing this type of construction is a complex and demanding process. Wind turbine blades are the most important part of the construction and are usually made of composite materials that meet the requirements of strength as well as aerodynamic requirements. Due to the high cost of composite materials, numerical modeling programs are very important because they allow the structure to be inspected before production, as well as to identify possible errors and weaknesses. In this way, additional manufacturing costs are avoided and a fully optimized structure is obtained. The finite element method (FEM) is a reliable method that allows the structure to be tested for the occurrence of normal and shear stresses that can lead to unwanted values of deformations on the blade. In this paper, the procedure of static analysis of a wind turbine blade is presented and the results that are important for optimizing the blade structure are analyzed. The purpose of FEM analysis is to find critical sections of the blade and to predict where maximum values of stresses may occur. In this way, it can be concluded whether the chosen material is appropriate and how the structure can be further optimized.
PB  - Springer Nature Switzerland AG
T2  - Experimental Research and Numerical Simulation in Applied Sciences. CNNTech 2022. Lecture Notes in Networks and Systems
T1  - The Wind Speed Impact on Stress and Deformation of Composite Wind Turbine Blade
EP  - 130
SP  - 114
VL  - 564
DO  - 10.1007/978-3-031-19499-3_6
ER  - 

@inbook{
author = "Raičević, Nikola and Petrašinović, Danilo and Grbović, Aleksandar and Petrašinović, Miloš and Balać, Martina and Petrović, Mihailo",
year = "2022",
abstract = "Wind turbines are structures that transform wind energy into other types of energy. In the modern age, wind turbines are closely related to the production of electricity and are considered starters of the green industry. Designing this type of construction is a complex and demanding process. Wind turbine blades are the most important part of the construction and are usually made of composite materials that meet the requirements of strength as well as aerodynamic requirements. Due to the high cost of composite materials, numerical modeling programs are very important because they allow the structure to be inspected before production, as well as to identify possible errors and weaknesses. In this way, additional manufacturing costs are avoided and a fully optimized structure is obtained. The finite element method (FEM) is a reliable method that allows the structure to be tested for the occurrence of normal and shear stresses that can lead to unwanted values of deformations on the blade. In this paper, the procedure of static analysis of a wind turbine blade is presented and the results that are important for optimizing the blade structure are analyzed. The purpose of FEM analysis is to find critical sections of the blade and to predict where maximum values of stresses may occur. In this way, it can be concluded whether the chosen material is appropriate and how the structure can be further optimized.",
publisher = "Springer Nature Switzerland AG",
journal = "Experimental Research and Numerical Simulation in Applied Sciences. CNNTech 2022. Lecture Notes in Networks and Systems",
booktitle = "The Wind Speed Impact on Stress and Deformation of Composite Wind Turbine Blade",
pages = "130-114",
volume = "564",
doi = "10.1007/978-3-031-19499-3_6"
}

Raičević, N., Petrašinović, D., Grbović, A., Petrašinović, M., Balać, M.,& Petrović, M.. (2022). The Wind Speed Impact on Stress and Deformation of Composite Wind Turbine Blade. in Experimental Research and Numerical Simulation in Applied Sciences. CNNTech 2022. Lecture Notes in Networks and Systems
Springer Nature Switzerland AG., 564, 114-130.
https://doi.org/10.1007/978-3-031-19499-3_6

Raičević N, Petrašinović D, Grbović A, Petrašinović M, Balać M, Petrović M. The Wind Speed Impact on Stress and Deformation of Composite Wind Turbine Blade. in Experimental Research and Numerical Simulation in Applied Sciences. CNNTech 2022. Lecture Notes in Networks and Systems. 2022;564:114-130.
doi:10.1007/978-3-031-19499-3_6 .

Raičević, Nikola, Petrašinović, Danilo, Grbović, Aleksandar, Petrašinović, Miloš, Balać, Martina, Petrović, Mihailo, "The Wind Speed Impact on Stress and Deformation of Composite Wind Turbine Blade" in Experimental Research and Numerical Simulation in Applied Sciences. CNNTech 2022. Lecture Notes in Networks and Systems, 564 (2022):114-130,
https://doi.org/10.1007/978-3-031-19499-3_6 . .

TY  - CONF
AU  - Raičević, Nikola
AU  - Petrašinović, Danilo
AU  - Grbović, Aleksandar
AU  - Petrašinović, Miloš
AU  - Petrović, Mihailo
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/5629
AB  - Macro programs used in computer modeling programs have become extremely important due to the high complexity of the models as well as the opportunity to create or adapt a specific geometry as soon as possible. Due to the implementation of the Python programming language, the FreeCAD program is highly suitable for creating advanced macros. When modeling aircraft parts (wings and tail surfaces), wind turbine blades, and similar structures, the biggest problem, due to the shape of the outer contour, is drawing the cross-section of the structures. The ImportAirfoil program allows to quickly and easily import and draw the contour of the desired airfoil, as well as modify it. This paper shows the complete procedure for importing and drawing of NACA2410 airfoil.
PB  - University of Belgrade - Faculty of Mechanical Engineering
C3  - 8th International Conference on Industrial Engineering - SIE 2022, Proceedings
T1  - FreeCAD ImportAirfoil Macro - Drawing Airfoil Geometry in an Open-Source CAD Program
EP  - 108
SP  - 105
UR  - https://hdl.handle.net/21.15107/rcub_machinery_5629
ER  - 

@conference{
author = "Raičević, Nikola and Petrašinović, Danilo and Grbović, Aleksandar and Petrašinović, Miloš and Petrović, Mihailo",
year = "2022",
abstract = "Macro programs used in computer modeling programs have become extremely important due to the high complexity of the models as well as the opportunity to create or adapt a specific geometry as soon as possible. Due to the implementation of the Python programming language, the FreeCAD program is highly suitable for creating advanced macros. When modeling aircraft parts (wings and tail surfaces), wind turbine blades, and similar structures, the biggest problem, due to the shape of the outer contour, is drawing the cross-section of the structures. The ImportAirfoil program allows to quickly and easily import and draw the contour of the desired airfoil, as well as modify it. This paper shows the complete procedure for importing and drawing of NACA2410 airfoil.",
publisher = "University of Belgrade - Faculty of Mechanical Engineering",
journal = "8th International Conference on Industrial Engineering - SIE 2022, Proceedings",
title = "FreeCAD ImportAirfoil Macro - Drawing Airfoil Geometry in an Open-Source CAD Program",
pages = "108-105",
url = "https://hdl.handle.net/21.15107/rcub_machinery_5629"
}

Raičević, N., Petrašinović, D., Grbović, A., Petrašinović, M.,& Petrović, M.. (2022). FreeCAD ImportAirfoil Macro - Drawing Airfoil Geometry in an Open-Source CAD Program. in 8th International Conference on Industrial Engineering - SIE 2022, Proceedings
University of Belgrade - Faculty of Mechanical Engineering., 105-108.
https://hdl.handle.net/21.15107/rcub_machinery_5629

Raičević N, Petrašinović D, Grbović A, Petrašinović M, Petrović M. FreeCAD ImportAirfoil Macro - Drawing Airfoil Geometry in an Open-Source CAD Program. in 8th International Conference on Industrial Engineering - SIE 2022, Proceedings. 2022;:105-108.
https://hdl.handle.net/21.15107/rcub_machinery_5629 .

Raičević, Nikola, Petrašinović, Danilo, Grbović, Aleksandar, Petrašinović, Miloš, Petrović, Mihailo, "FreeCAD ImportAirfoil Macro - Drawing Airfoil Geometry in an Open-Source CAD Program" in 8th International Conference on Industrial Engineering - SIE 2022, Proceedings (2022):105-108,
https://hdl.handle.net/21.15107/rcub_machinery_5629 .

TY  - CONF
AU  - Raičević, Nikola
AU  - Petrašinović, Danilo
AU  - Grbović, Aleksandar
AU  - Petrašinović, Miloš
AU  - Petrović, Mihailo
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/5739
AB  - Wind energy is one of the most promising sources of renewable energy. The wind energy is converted into mechanical power through blades which are a major part of wind turbines. Nowadays, composite materials have been used for the fabrication of wind turbine blades to reduce blade weight. Fluid flows over the blade's structure surface and creates pressure loads resulting in the deformation of the blade. Numerical modeling methods are applied to estimate flow-induced deformation and they are required for the optimization of composite wind turbine blades. The wind turbine blade is analysed by computational fluid dynamics (CFD), finite element analysis (FEA), and the one-way and two-way system coupling of fluid-structure interaction (FSI) simulations of the composite wind turbine blade. The CFD was used to find the initial pressure load of the structure. Five types of the composite material were analysed to compare the results and define the optimum composite material based on the values of stress and deformation. The finite element analysis was used to test the tensile stiffness of the chosen composite laminate and to study the effect of micro-scale structural porosity on strength of structural materials. FSI simulations were performed for several wind speeds and then the results were analysed through the comparison of normal and shear stresses, blade deformations, force and moment reactions. The results are presented in the terms of the normal and shear stress distribution, and blade deformation with defined positions of the maximum values on the blade structure.
PB  - Innovation Center of Faculty of Mechanical Engineering
C3  - International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022
T1  - Fluid-Structural Analysis and Optimization of Composite Wind Turbine Blade
EP  - 84
SP  - 84
UR  - https://hdl.handle.net/21.15107/rcub_machinery_5739
ER  - 

@conference{
author = "Raičević, Nikola and Petrašinović, Danilo and Grbović, Aleksandar and Petrašinović, Miloš and Petrović, Mihailo",
year = "2022",
abstract = "Wind energy is one of the most promising sources of renewable energy. The wind energy is converted into mechanical power through blades which are a major part of wind turbines. Nowadays, composite materials have been used for the fabrication of wind turbine blades to reduce blade weight. Fluid flows over the blade's structure surface and creates pressure loads resulting in the deformation of the blade. Numerical modeling methods are applied to estimate flow-induced deformation and they are required for the optimization of composite wind turbine blades. The wind turbine blade is analysed by computational fluid dynamics (CFD), finite element analysis (FEA), and the one-way and two-way system coupling of fluid-structure interaction (FSI) simulations of the composite wind turbine blade. The CFD was used to find the initial pressure load of the structure. Five types of the composite material were analysed to compare the results and define the optimum composite material based on the values of stress and deformation. The finite element analysis was used to test the tensile stiffness of the chosen composite laminate and to study the effect of micro-scale structural porosity on strength of structural materials. FSI simulations were performed for several wind speeds and then the results were analysed through the comparison of normal and shear stresses, blade deformations, force and moment reactions. The results are presented in the terms of the normal and shear stress distribution, and blade deformation with defined positions of the maximum values on the blade structure.",
publisher = "Innovation Center of Faculty of Mechanical Engineering",
journal = "International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022",
title = "Fluid-Structural Analysis and Optimization of Composite Wind Turbine Blade",
pages = "84-84",
url = "https://hdl.handle.net/21.15107/rcub_machinery_5739"
}

Raičević, N., Petrašinović, D., Grbović, A., Petrašinović, M.,& Petrović, M.. (2022). Fluid-Structural Analysis and Optimization of Composite Wind Turbine Blade. in International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022
Innovation Center of Faculty of Mechanical Engineering., 84-84.
https://hdl.handle.net/21.15107/rcub_machinery_5739

Raičević N, Petrašinović D, Grbović A, Petrašinović M, Petrović M. Fluid-Structural Analysis and Optimization of Composite Wind Turbine Blade. in International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022. 2022;:84-84.
https://hdl.handle.net/21.15107/rcub_machinery_5739 .

Raičević, Nikola, Petrašinović, Danilo, Grbović, Aleksandar, Petrašinović, Miloš, Petrović, Mihailo, "Fluid-Structural Analysis and Optimization of Composite Wind Turbine Blade" in International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022 (2022):84-84,
https://hdl.handle.net/21.15107/rcub_machinery_5739 .

TY  - CONF
AU  - Petrašinović, Miloš
AU  - Petrašinović, Danilo
AU  - Grbović, Aleksandar
AU  - Petrović, Veljko M.
AU  - Petrović, Mihailo
AU  - Raičević, Nikola
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/5738
AB  - The constant advance in the usage of unmanned aerial vehicles (UAVs) of all types, including electric multicopters (rotary-wing drones), requests further advancement on all project levels in order to create a competitive final product. With the usage of composite materials, mainly carbon fiber in epoxy resin, it is possible to have a very lightweight structure that is strong enough to sustain all anticipated loads. Arms are a crucial part of multicopter structures that are often made entirely of composite materials. Each multicopter arm has at least one electric motor and propeller on one and a connection with the body on the other end. A static load test stand for various sizes of arms is designed and developed in order to test prototypes within the design process and to be able to test the mechanical characteristics of each produced final part that will be later assembled with other parts. The test stand consists of a robust steel frame, part mounting clamps, a movable low-speed hydraulic cylinder with an appropriate hydraulic power pack powered by an electric motor which is controlled by a variable frequency drive, a load cell for force measurement, and a linear displacement transducer for displacement. A custom digital electronic circuit with a microcontroller is developed in order to control the actuator and obtain data from sensors. Also, custom user-friendly software with a graphical user interface is designed to control experiments and process measurements.
PB  - Innovation Center of Faculty of Mechanical Engineering
C3  - International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022
T1  - Design and Development of Static Load Test Stand for Various Sizes of Multicopter Arms
EP  - 44
SP  - 44
UR  - https://hdl.handle.net/21.15107/rcub_machinery_5738
ER  - 

@conference{
author = "Petrašinović, Miloš and Petrašinović, Danilo and Grbović, Aleksandar and Petrović, Veljko M. and Petrović, Mihailo and Raičević, Nikola",
year = "2022",
abstract = "The constant advance in the usage of unmanned aerial vehicles (UAVs) of all types, including electric multicopters (rotary-wing drones), requests further advancement on all project levels in order to create a competitive final product. With the usage of composite materials, mainly carbon fiber in epoxy resin, it is possible to have a very lightweight structure that is strong enough to sustain all anticipated loads. Arms are a crucial part of multicopter structures that are often made entirely of composite materials. Each multicopter arm has at least one electric motor and propeller on one and a connection with the body on the other end. A static load test stand for various sizes of arms is designed and developed in order to test prototypes within the design process and to be able to test the mechanical characteristics of each produced final part that will be later assembled with other parts. The test stand consists of a robust steel frame, part mounting clamps, a movable low-speed hydraulic cylinder with an appropriate hydraulic power pack powered by an electric motor which is controlled by a variable frequency drive, a load cell for force measurement, and a linear displacement transducer for displacement. A custom digital electronic circuit with a microcontroller is developed in order to control the actuator and obtain data from sensors. Also, custom user-friendly software with a graphical user interface is designed to control experiments and process measurements.",
publisher = "Innovation Center of Faculty of Mechanical Engineering",
journal = "International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022",
title = "Design and Development of Static Load Test Stand for Various Sizes of Multicopter Arms",
pages = "44-44",
url = "https://hdl.handle.net/21.15107/rcub_machinery_5738"
}

Petrašinović, M., Petrašinović, D., Grbović, A., Petrović, V. M., Petrović, M.,& Raičević, N.. (2022). Design and Development of Static Load Test Stand for Various Sizes of Multicopter Arms. in International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022
Innovation Center of Faculty of Mechanical Engineering., 44-44.
https://hdl.handle.net/21.15107/rcub_machinery_5738

Petrašinović M, Petrašinović D, Grbović A, Petrović VM, Petrović M, Raičević N. Design and Development of Static Load Test Stand for Various Sizes of Multicopter Arms. in International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022. 2022;:44-44.
https://hdl.handle.net/21.15107/rcub_machinery_5738 .

Petrašinović, Miloš, Petrašinović, Danilo, Grbović, Aleksandar, Petrović, Veljko M., Petrović, Mihailo, Raičević, Nikola, "Design and Development of Static Load Test Stand for Various Sizes of Multicopter Arms" in International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022 (2022):44-44,
https://hdl.handle.net/21.15107/rcub_machinery_5738 .

TY  - CONF
AU  - Raičević, Nikola
AU  - Petrašinović, Miloš
AU  - Petrašinović, Danilo
AU  - Kastratović, Gordana
AU  - Grbović, Aleksandar
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/5637
AB  - To become a reliable and widely accepted production process, additive manufacturing (AM) must provide metal structures with the same or better structural integrity than those produced using traditional methods. In the AM process, multiple build attempts are often required to obtain the part of standardized quality. Another crucial issue is the fatigue behaviour of AM structures (particularly in the presence of voids) which must be assessed and predicted with satisfactory accuracy. There are several major challenges connected to this issue, including obtaining the exact material properties and assessing the life of the complex shapes produced using AM. Bearing this in mind, numerical simulations of AM processes, as well as of the fatigue crack growth in structures of complex shapes, become crucial factors in speeding up the industrial implementation of AM. The aim of this paper is to demonstrate current abilities and performances, as well as the restrictions of the numerical methods in simulating AM processes and fatigue crack growth in metallic structures of complex geometry. In this study, numerical simulations were first carried out on the standard CT specimen (Fig. 1), and then on the real shape of an UAV’s attachment used to hold the composite arm and transfer loads to the main body of the UAV (Fig. 2, 3). For this purpose, the finite element method (FEM) was used, and the results of 3D numerical analyses, performed in Ansys Workbench software, were compared to experimental findings.
PB  - University of Belgrade - Faculty of Mechanical Engineering
C3  - 3rd International Workshop on Reliability and Design of Additively Manufactured Materials - RdAMM22, Workshop Programme & Book of Abstracts
T1  - Evaluation of fatigue life of damaged UAV’s attachment produced using additive manufacturing
EP  - 39
SP  - 38
UR  - https://hdl.handle.net/21.15107/rcub_machinery_5637
ER  - 

@conference{
author = "Raičević, Nikola and Petrašinović, Miloš and Petrašinović, Danilo and Kastratović, Gordana and Grbović, Aleksandar",
year = "2022",
abstract = "To become a reliable and widely accepted production process, additive manufacturing (AM) must provide metal structures with the same or better structural integrity than those produced using traditional methods. In the AM process, multiple build attempts are often required to obtain the part of standardized quality. Another crucial issue is the fatigue behaviour of AM structures (particularly in the presence of voids) which must be assessed and predicted with satisfactory accuracy. There are several major challenges connected to this issue, including obtaining the exact material properties and assessing the life of the complex shapes produced using AM. Bearing this in mind, numerical simulations of AM processes, as well as of the fatigue crack growth in structures of complex shapes, become crucial factors in speeding up the industrial implementation of AM. The aim of this paper is to demonstrate current abilities and performances, as well as the restrictions of the numerical methods in simulating AM processes and fatigue crack growth in metallic structures of complex geometry. In this study, numerical simulations were first carried out on the standard CT specimen (Fig. 1), and then on the real shape of an UAV’s attachment used to hold the composite arm and transfer loads to the main body of the UAV (Fig. 2, 3). For this purpose, the finite element method (FEM) was used, and the results of 3D numerical analyses, performed in Ansys Workbench software, were compared to experimental findings.",
publisher = "University of Belgrade - Faculty of Mechanical Engineering",
journal = "3rd International Workshop on Reliability and Design of Additively Manufactured Materials - RdAMM22, Workshop Programme & Book of Abstracts",
title = "Evaluation of fatigue life of damaged UAV’s attachment produced using additive manufacturing",
pages = "39-38",
url = "https://hdl.handle.net/21.15107/rcub_machinery_5637"
}

Raičević, N., Petrašinović, M., Petrašinović, D., Kastratović, G.,& Grbović, A.. (2022). Evaluation of fatigue life of damaged UAV’s attachment produced using additive manufacturing. in 3rd International Workshop on Reliability and Design of Additively Manufactured Materials - RdAMM22, Workshop Programme & Book of Abstracts
University of Belgrade - Faculty of Mechanical Engineering., 38-39.
https://hdl.handle.net/21.15107/rcub_machinery_5637

Raičević N, Petrašinović M, Petrašinović D, Kastratović G, Grbović A. Evaluation of fatigue life of damaged UAV’s attachment produced using additive manufacturing. in 3rd International Workshop on Reliability and Design of Additively Manufactured Materials - RdAMM22, Workshop Programme & Book of Abstracts. 2022;:38-39.
https://hdl.handle.net/21.15107/rcub_machinery_5637 .

Raičević, Nikola, Petrašinović, Miloš, Petrašinović, Danilo, Kastratović, Gordana, Grbović, Aleksandar, "Evaluation of fatigue life of damaged UAV’s attachment produced using additive manufacturing" in 3rd International Workshop on Reliability and Design of Additively Manufactured Materials - RdAMM22, Workshop Programme & Book of Abstracts (2022):38-39,
https://hdl.handle.net/21.15107/rcub_machinery_5637 .

TY  - CONF
AU  - Petrašinović, Miloš
AU  - Grbović, Aleksandar
AU  - Petrašinović, Danilo
AU  - Raičević, Nikola
AU  - Petrović, Mihailo
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/5737
AB  - One of the most important characteristics of the mechanism used for flight simulation is its workspace. The workspace of any mechanism (including parallel mechanisms, which has a closed kinematic chain) is a set of positions and orientations reachable by its end-effector. In order to be able to successfully simulate flight with a motion platform, on which the pilot sits while in training, its workspace has to meet some criteria. Based on previous, it is essential to have a computationally fast and efficient but at the same time also accurate workspace determination process in order to design and optimize the geometry of the mechanism used for the flight simulator. Full flight simulators are most often with parallel mechanisms based on the Stewart platform which has six degrees of freedom inside the workspace. There is no analytical solution for the workspace of this type of mechanism that considers all constraints (such as motion limits of joints) and that can be practically used in the design process. One option is to simply test all significant positions and orientations, this includes defining the range for each axis and value change step (increment between consecutive values) and then testing all possible combinations. In order to lower the number of combinations that must be tested space is divided a few times, first with the coarser step and then with the finer one just around the boundary of the workspace. The final step is defining the boundary surface based on points that are within the workspace.
PB  - Innovation Center of Faculty of Mechanical Engineering
C3  - International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022
T1  - Numerical Method for Workspace Determination of Flight Simulator with Stewart Platform Mechanism
EP  - 43
SP  - 43
UR  - https://hdl.handle.net/21.15107/rcub_machinery_5737
ER  - 

@conference{
author = "Petrašinović, Miloš and Grbović, Aleksandar and Petrašinović, Danilo and Raičević, Nikola and Petrović, Mihailo",
year = "2022",
abstract = "One of the most important characteristics of the mechanism used for flight simulation is its workspace. The workspace of any mechanism (including parallel mechanisms, which has a closed kinematic chain) is a set of positions and orientations reachable by its end-effector. In order to be able to successfully simulate flight with a motion platform, on which the pilot sits while in training, its workspace has to meet some criteria. Based on previous, it is essential to have a computationally fast and efficient but at the same time also accurate workspace determination process in order to design and optimize the geometry of the mechanism used for the flight simulator. Full flight simulators are most often with parallel mechanisms based on the Stewart platform which has six degrees of freedom inside the workspace. There is no analytical solution for the workspace of this type of mechanism that considers all constraints (such as motion limits of joints) and that can be practically used in the design process. One option is to simply test all significant positions and orientations, this includes defining the range for each axis and value change step (increment between consecutive values) and then testing all possible combinations. In order to lower the number of combinations that must be tested space is divided a few times, first with the coarser step and then with the finer one just around the boundary of the workspace. The final step is defining the boundary surface based on points that are within the workspace.",
publisher = "Innovation Center of Faculty of Mechanical Engineering",
journal = "International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022",
title = "Numerical Method for Workspace Determination of Flight Simulator with Stewart Platform Mechanism",
pages = "43-43",
url = "https://hdl.handle.net/21.15107/rcub_machinery_5737"
}

Petrašinović, M., Grbović, A., Petrašinović, D., Raičević, N.,& Petrović, M.. (2022). Numerical Method for Workspace Determination of Flight Simulator with Stewart Platform Mechanism. in International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022
Innovation Center of Faculty of Mechanical Engineering., 43-43.
https://hdl.handle.net/21.15107/rcub_machinery_5737

Petrašinović M, Grbović A, Petrašinović D, Raičević N, Petrović M. Numerical Method for Workspace Determination of Flight Simulator with Stewart Platform Mechanism. in International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022. 2022;:43-43.
https://hdl.handle.net/21.15107/rcub_machinery_5737 .

Petrašinović, Miloš, Grbović, Aleksandar, Petrašinović, Danilo, Raičević, Nikola, Petrović, Mihailo, "Numerical Method for Workspace Determination of Flight Simulator with Stewart Platform Mechanism" in International Conference of Experimental and Numerical Investigations and New Technologies – CNN TECH 2022 (2022):43-43,
https://hdl.handle.net/21.15107/rcub_machinery_5737 .

TY  - JOUR
AU  - Petrašinović, Miloš
AU  - Grbović, Aleksandar
AU  - Petrašinović, Danilo
AU  - Petrović, Mihailo G.
AU  - Raičević, Nikola
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3730
AB  - Featured Application Low-cost flight simulators with electric rotary actuators and optimized geometry for flight simulation. Designing the motion platform for the flight simulator is closely coupled with the particular aircraft's flight envelope. While in training, the pilot on the motion platform has to experience the same feeling as in the aircraft. That means that flight simulators need to simulate all flight cases and forces acting upon the pilot during flight. Among many existing mechanisms, parallel mechanisms based on the Stewart platform are suitable because they have six degrees of freedom. In this paper, a real coded mixed integer genetic algorithm (RCMIGA) is applied for geometry optimization of the Stewart platform with rotary actuators (6-RUS) to design a mechanism with appropriate physical limitations of workspace and motion performances. The chosen algorithm proved that it can find the best global solution with all imposed constraints. At the same time, the obtained geometry can be manufactured because integer solutions can be mapped to available discrete values. Geometry is defined with a minimum number of parameters that fully define the mechanism with all constraints. These geometric parameters are then optimized to obtain custom-tailored geometry for aircraft flight simulation.
PB  - MDPI, Basel
T2  - Applied Sciences-Basel
T1  - Real Coded Mixed Integer Genetic Algorithm for Geometry Optimization of Flight Simulator Mechanism Based on Rotary Stewart Platform
IS  - 14
VL  - 12
DO  - 10.3390/app12147085
ER  - 

@article{
author = "Petrašinović, Miloš and Grbović, Aleksandar and Petrašinović, Danilo and Petrović, Mihailo G. and Raičević, Nikola",
year = "2022",
abstract = "Featured Application Low-cost flight simulators with electric rotary actuators and optimized geometry for flight simulation. Designing the motion platform for the flight simulator is closely coupled with the particular aircraft's flight envelope. While in training, the pilot on the motion platform has to experience the same feeling as in the aircraft. That means that flight simulators need to simulate all flight cases and forces acting upon the pilot during flight. Among many existing mechanisms, parallel mechanisms based on the Stewart platform are suitable because they have six degrees of freedom. In this paper, a real coded mixed integer genetic algorithm (RCMIGA) is applied for geometry optimization of the Stewart platform with rotary actuators (6-RUS) to design a mechanism with appropriate physical limitations of workspace and motion performances. The chosen algorithm proved that it can find the best global solution with all imposed constraints. At the same time, the obtained geometry can be manufactured because integer solutions can be mapped to available discrete values. Geometry is defined with a minimum number of parameters that fully define the mechanism with all constraints. These geometric parameters are then optimized to obtain custom-tailored geometry for aircraft flight simulation.",
publisher = "MDPI, Basel",
journal = "Applied Sciences-Basel",
title = "Real Coded Mixed Integer Genetic Algorithm for Geometry Optimization of Flight Simulator Mechanism Based on Rotary Stewart Platform",
number = "14",
volume = "12",
doi = "10.3390/app12147085"
}

Petrašinović, M., Grbović, A., Petrašinović, D., Petrović, M. G.,& Raičević, N.. (2022). Real Coded Mixed Integer Genetic Algorithm for Geometry Optimization of Flight Simulator Mechanism Based on Rotary Stewart Platform. in Applied Sciences-Basel
MDPI, Basel., 12(14).
https://doi.org/10.3390/app12147085

Petrašinović M, Grbović A, Petrašinović D, Petrović MG, Raičević N. Real Coded Mixed Integer Genetic Algorithm for Geometry Optimization of Flight Simulator Mechanism Based on Rotary Stewart Platform. in Applied Sciences-Basel. 2022;12(14).
doi:10.3390/app12147085 .

Petrašinović, Miloš, Grbović, Aleksandar, Petrašinović, Danilo, Petrović, Mihailo G., Raičević, Nikola, "Real Coded Mixed Integer Genetic Algorithm for Geometry Optimization of Flight Simulator Mechanism Based on Rotary Stewart Platform" in Applied Sciences-Basel, 12, no. 14 (2022),
https://doi.org/10.3390/app12147085 . .

TY  - CONF
AU  - Petrašinović, Miloš
AU  - Grbović, Aleksandar
AU  - Petrašinović, Danilo
PY  - 2020
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3287
AB  - Flight simulators are motion platforms used to train pilots in various flight regimes. Theoretically, they need to simulate all flight cases and all forces acting upon the pilot during flight. In order to successfully simulate real flight, a moving part of the simulator needs to have six degrees of freedom. The pilot's body is moved and oriented in the space according to the video shown to him. Among many existing designs, parallel mechanisms based on the Stewart platform are most frequently used. In this paper, geometry optimization of the Stewart platform with rotary actuators (6-RUS) is done with a genetic algorithm. For the sake of optimization, it is necessary to define a minimum number of parameters that fully define mechanism with all constraints. The purpose of geometry optimization is to find a mechanism with a workspace that is suitable for simulating flight.
PB  - Springer International Publishing Ag, Cham
C3  - Computational and Experimental Approaches in Materials Science and Engineering, Cnntech 2019
T1  - Geometry Optimization of Flight Simulator Mechanism Using Genetic Algorithm
EP  - 358
SP  - 340
VL  - 90
DO  - 10.1007/978-3-030-30853-7_20
ER  - 

@conference{
author = "Petrašinović, Miloš and Grbović, Aleksandar and Petrašinović, Danilo",
year = "2020",
abstract = "Flight simulators are motion platforms used to train pilots in various flight regimes. Theoretically, they need to simulate all flight cases and all forces acting upon the pilot during flight. In order to successfully simulate real flight, a moving part of the simulator needs to have six degrees of freedom. The pilot's body is moved and oriented in the space according to the video shown to him. Among many existing designs, parallel mechanisms based on the Stewart platform are most frequently used. In this paper, geometry optimization of the Stewart platform with rotary actuators (6-RUS) is done with a genetic algorithm. For the sake of optimization, it is necessary to define a minimum number of parameters that fully define mechanism with all constraints. The purpose of geometry optimization is to find a mechanism with a workspace that is suitable for simulating flight.",
publisher = "Springer International Publishing Ag, Cham",
journal = "Computational and Experimental Approaches in Materials Science and Engineering, Cnntech 2019",
title = "Geometry Optimization of Flight Simulator Mechanism Using Genetic Algorithm",
pages = "358-340",
volume = "90",
doi = "10.1007/978-3-030-30853-7_20"
}

Petrašinović, M., Grbović, A.,& Petrašinović, D.. (2020). Geometry Optimization of Flight Simulator Mechanism Using Genetic Algorithm. in Computational and Experimental Approaches in Materials Science and Engineering, Cnntech 2019
Springer International Publishing Ag, Cham., 90, 340-358.
https://doi.org/10.1007/978-3-030-30853-7_20

Petrašinović M, Grbović A, Petrašinović D. Geometry Optimization of Flight Simulator Mechanism Using Genetic Algorithm. in Computational and Experimental Approaches in Materials Science and Engineering, Cnntech 2019. 2020;90:340-358.
doi:10.1007/978-3-030-30853-7_20 .

Petrašinović, Miloš, Grbović, Aleksandar, Petrašinović, Danilo, "Geometry Optimization of Flight Simulator Mechanism Using Genetic Algorithm" in Computational and Experimental Approaches in Materials Science and Engineering, Cnntech 2019, 90 (2020):340-358,
https://doi.org/10.1007/978-3-030-30853-7_20 . .

TY  - JOUR
AU  - Grbović, Aleksandar
AU  - Sedmak, Aleksandar
AU  - Kastratović, Gordana
AU  - Petrašinović, Danilo
AU  - Vidanović, Nenad
AU  - Sghayer, Abulgasem
PY  - 2019
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3135
AB  - In this paper, numerical analyses of fatigue crack growth in integral skin-stringer panel produced by means of laser beam welding (LBW) are presented along with fatigue results verified by previously conducted experiments. Skin-stringer panel is fail-safe structure widely used in aircraft industry, which requires a good estimate of fatigue life after crack initiation. In the past, experimental work was the only successful method for fatigue life estimation of complex damaged structure, but nowadays researches have powerful numerical tools, such as extended finite element method (XFEM), for three-dimensional crack growth analysis. In research presented here, XFEM was initially used for crack growth simulation in simple flat plate made of aluminium 6156 T6 and 6156 T4 for the purpose of procedure verification, since fatigue life for simple plate was known from experiment. Then, XFEM was used to simulate fatigue crack growth in the panel reinforced with four stringers. Fatigue life obtained on the basis of calculated stress intensity factors (SIFS) along the crack fronts on LBW skin-stringer panels was, as expected, significantly longer than experimentally measured life of simple flat plate. Finally, several numerical simulations were performed in order to analyse the influence of mesh size on accuracy of estimated fatigue life of damaged LBW skin panels. For that purpose, average element sizes of 1, 2 and 4 mm were used.
PB  - Pergamon-Elsevier Science Ltd, Oxford
T2  - Engineering Failure Analysis
T1  - Effect of laser beam welded reinforcement on integral skin panel fatigue life
EP  - 393
SP  - 383
VL  - 101
DO  - 10.1016/j.engfailanal.2019.03.029
ER  - 

@article{
author = "Grbović, Aleksandar and Sedmak, Aleksandar and Kastratović, Gordana and Petrašinović, Danilo and Vidanović, Nenad and Sghayer, Abulgasem",
year = "2019",
abstract = "In this paper, numerical analyses of fatigue crack growth in integral skin-stringer panel produced by means of laser beam welding (LBW) are presented along with fatigue results verified by previously conducted experiments. Skin-stringer panel is fail-safe structure widely used in aircraft industry, which requires a good estimate of fatigue life after crack initiation. In the past, experimental work was the only successful method for fatigue life estimation of complex damaged structure, but nowadays researches have powerful numerical tools, such as extended finite element method (XFEM), for three-dimensional crack growth analysis. In research presented here, XFEM was initially used for crack growth simulation in simple flat plate made of aluminium 6156 T6 and 6156 T4 for the purpose of procedure verification, since fatigue life for simple plate was known from experiment. Then, XFEM was used to simulate fatigue crack growth in the panel reinforced with four stringers. Fatigue life obtained on the basis of calculated stress intensity factors (SIFS) along the crack fronts on LBW skin-stringer panels was, as expected, significantly longer than experimentally measured life of simple flat plate. Finally, several numerical simulations were performed in order to analyse the influence of mesh size on accuracy of estimated fatigue life of damaged LBW skin panels. For that purpose, average element sizes of 1, 2 and 4 mm were used.",
publisher = "Pergamon-Elsevier Science Ltd, Oxford",
journal = "Engineering Failure Analysis",
title = "Effect of laser beam welded reinforcement on integral skin panel fatigue life",
pages = "393-383",
volume = "101",
doi = "10.1016/j.engfailanal.2019.03.029"
}

Grbović, A., Sedmak, A., Kastratović, G., Petrašinović, D., Vidanović, N.,& Sghayer, A.. (2019). Effect of laser beam welded reinforcement on integral skin panel fatigue life. in Engineering Failure Analysis
Pergamon-Elsevier Science Ltd, Oxford., 101, 383-393.
https://doi.org/10.1016/j.engfailanal.2019.03.029

Grbović A, Sedmak A, Kastratović G, Petrašinović D, Vidanović N, Sghayer A. Effect of laser beam welded reinforcement on integral skin panel fatigue life. in Engineering Failure Analysis. 2019;101:383-393.
doi:10.1016/j.engfailanal.2019.03.029 .

Grbović, Aleksandar, Sedmak, Aleksandar, Kastratović, Gordana, Petrašinović, Danilo, Vidanović, Nenad, Sghayer, Abulgasem, "Effect of laser beam welded reinforcement on integral skin panel fatigue life" in Engineering Failure Analysis, 101 (2019):383-393,
https://doi.org/10.1016/j.engfailanal.2019.03.029 . .

TY  - JOUR
AU  - Eldwaib, Khalid
AU  - Grbović, Aleksandar
AU  - Sedmak, Aleksandar
AU  - Kastratović, Gordana
AU  - Petrašinović, Danilo
AU  - Sedmak, Simon
PY  - 2018
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2897
AB  - This paper presents the application of the extended finite element method (XFEM) in crack propagation simulation on the integral wing spar that should replace existing differential spar of the light aircraft UTVA 75. Numerical model of integral spar was developed in software Abaqus. Stress intensity factors (SIFs) were calculated using add-in Morfeo/Crack for Abaqus and obtained number of cycles that would propagate crack to certain length was compared to the experimentally obtained number of cycles for differential spar. Numerical analysis showed that integral spar with the same dimensions as differential spar has significant increase in fatigue life. Analysis that was carried out showed that XFEM could be efficient and cost beneficial tool for simulation of crack propagation in the 3D structures (such as wing spar) and that it should be used in the future for fatigue analysis of newly designed structures in all phases of development and production.
PB  - Univ Osijek, Tech Fac, Slavonski Brod
T2  - Tehnički vjesnik
T1  - Fatigue Life Estimation of Damaged Integral Wing Spar Using XFEM
EP  - 1842
IS  - 6
SP  - 1837
VL  - 25
DO  - 10.17559/TV-20171007105350
ER  - 

@article{
author = "Eldwaib, Khalid and Grbović, Aleksandar and Sedmak, Aleksandar and Kastratović, Gordana and Petrašinović, Danilo and Sedmak, Simon",
year = "2018",
abstract = "This paper presents the application of the extended finite element method (XFEM) in crack propagation simulation on the integral wing spar that should replace existing differential spar of the light aircraft UTVA 75. Numerical model of integral spar was developed in software Abaqus. Stress intensity factors (SIFs) were calculated using add-in Morfeo/Crack for Abaqus and obtained number of cycles that would propagate crack to certain length was compared to the experimentally obtained number of cycles for differential spar. Numerical analysis showed that integral spar with the same dimensions as differential spar has significant increase in fatigue life. Analysis that was carried out showed that XFEM could be efficient and cost beneficial tool for simulation of crack propagation in the 3D structures (such as wing spar) and that it should be used in the future for fatigue analysis of newly designed structures in all phases of development and production.",
publisher = "Univ Osijek, Tech Fac, Slavonski Brod",
journal = "Tehnički vjesnik",
title = "Fatigue Life Estimation of Damaged Integral Wing Spar Using XFEM",
pages = "1842-1837",
number = "6",
volume = "25",
doi = "10.17559/TV-20171007105350"
}

Eldwaib, K., Grbović, A., Sedmak, A., Kastratović, G., Petrašinović, D.,& Sedmak, S.. (2018). Fatigue Life Estimation of Damaged Integral Wing Spar Using XFEM. in Tehnički vjesnik
Univ Osijek, Tech Fac, Slavonski Brod., 25(6), 1837-1842.
https://doi.org/10.17559/TV-20171007105350

Eldwaib K, Grbović A, Sedmak A, Kastratović G, Petrašinović D, Sedmak S. Fatigue Life Estimation of Damaged Integral Wing Spar Using XFEM. in Tehnički vjesnik. 2018;25(6):1837-1842.
doi:10.17559/TV-20171007105350 .

Eldwaib, Khalid, Grbović, Aleksandar, Sedmak, Aleksandar, Kastratović, Gordana, Petrašinović, Danilo, Sedmak, Simon, "Fatigue Life Estimation of Damaged Integral Wing Spar Using XFEM" in Tehnički vjesnik, 25, no. 6 (2018):1837-1842,
https://doi.org/10.17559/TV-20171007105350 . .

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  - 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  - JOUR
AU  - Rašuo, Boško
AU  - Grbović, Aleksandar
AU  - Petrašinović, Danilo
PY  - 2013
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1824
AB  - The assessment of the service durability of aerospace components and assemblies has become an important segment of design. In order to meet strict safety requirements, a number of complex and long experiments are carried out. The use of finite element method (FEM) and extended finite element method (XFEM) for the estimation of fatigue life and fatigue crack growth predictions has been proved as a good alternative to the expensive experimental methods. In this paper, both experimental and numerical analyses of 2024-T3 aluminum spar of a light aircraft under variable amplitude loading are presented. FEM has been used for estimation of the spar life to crack initiation, whereas XFEM has been used for fatigue crack growth predictions and fatigue life estimation of damaged spar. The values of stress intensity factors were extracted from the XFEM solution in MorfeoCrack for Abaqus software. Numerical results (i.e. number of cycles to failure) have corresponded well with the experimental values obtained for the spar made of 2024-T3 aluminum alloy. The investigations have shown that it's possible, using XFEM, to obtain not only the good estimation of fatigue life of the assembly such as the spar of the light aircraft, but also a good prediction of a number of load cycles which will propagate a crack to a certain length. On the basis of these results, it is possible to determine the proper inspections intervals which could prevent the catastrophic failure of the aircraft structure under variable amplitude loading.
PB  - SAE International
T2  - SAE International Journal of Aerospace
T1  - Investigation of Fatigue Life of 2024-T3 Aluminum Spar Using Extended Finite Element Method (XFEM)
EP  - 416
IS  - 2
SP  - 408
VL  - 6
DO  - 10.4271/2013-01-2143
ER  - 

@article{
author = "Rašuo, Boško and Grbović, Aleksandar and Petrašinović, Danilo",
year = "2013",
abstract = "The assessment of the service durability of aerospace components and assemblies has become an important segment of design. In order to meet strict safety requirements, a number of complex and long experiments are carried out. The use of finite element method (FEM) and extended finite element method (XFEM) for the estimation of fatigue life and fatigue crack growth predictions has been proved as a good alternative to the expensive experimental methods. In this paper, both experimental and numerical analyses of 2024-T3 aluminum spar of a light aircraft under variable amplitude loading are presented. FEM has been used for estimation of the spar life to crack initiation, whereas XFEM has been used for fatigue crack growth predictions and fatigue life estimation of damaged spar. The values of stress intensity factors were extracted from the XFEM solution in MorfeoCrack for Abaqus software. Numerical results (i.e. number of cycles to failure) have corresponded well with the experimental values obtained for the spar made of 2024-T3 aluminum alloy. The investigations have shown that it's possible, using XFEM, to obtain not only the good estimation of fatigue life of the assembly such as the spar of the light aircraft, but also a good prediction of a number of load cycles which will propagate a crack to a certain length. On the basis of these results, it is possible to determine the proper inspections intervals which could prevent the catastrophic failure of the aircraft structure under variable amplitude loading.",
publisher = "SAE International",
journal = "SAE International Journal of Aerospace",
title = "Investigation of Fatigue Life of 2024-T3 Aluminum Spar Using Extended Finite Element Method (XFEM)",
pages = "416-408",
number = "2",
volume = "6",
doi = "10.4271/2013-01-2143"
}

Rašuo, B., Grbović, A.,& Petrašinović, D.. (2013). Investigation of Fatigue Life of 2024-T3 Aluminum Spar Using Extended Finite Element Method (XFEM). in SAE International Journal of Aerospace
SAE International., 6(2), 408-416.
https://doi.org/10.4271/2013-01-2143

Rašuo B, Grbović A, Petrašinović D. Investigation of Fatigue Life of 2024-T3 Aluminum Spar Using Extended Finite Element Method (XFEM). in SAE International Journal of Aerospace. 2013;6(2):408-416.
doi:10.4271/2013-01-2143 .

Rašuo, Boško, Grbović, Aleksandar, Petrašinović, Danilo, "Investigation of Fatigue Life of 2024-T3 Aluminum Spar Using Extended Finite Element Method (XFEM)" in SAE International Journal of Aerospace, 6, no. 2 (2013):408-416,
https://doi.org/10.4271/2013-01-2143 . .

TY  - CONF
AU  - Peković, Ognjen
AU  - Stupar, Slobodan
AU  - Simonović, Aleksandar
AU  - Petrašinović, Danilo
AU  - Zorić, Nemanja
PY  - 2012
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1537
PB  - University of Belgrade
C3  - 29th DANUBlA-ADRIA Symposium on Advances in Experimental Mechanics, DAS 2012
T1  - Experimental determination of guy wire tension
EP  - 241
SP  - 238
UR  - https://hdl.handle.net/21.15107/rcub_machinery_1537
ER  - 

@conference{
author = "Peković, Ognjen and Stupar, Slobodan and Simonović, Aleksandar and Petrašinović, Danilo and Zorić, Nemanja",
year = "2012",
publisher = "University of Belgrade",
journal = "29th DANUBlA-ADRIA Symposium on Advances in Experimental Mechanics, DAS 2012",
title = "Experimental determination of guy wire tension",
pages = "241-238",
url = "https://hdl.handle.net/21.15107/rcub_machinery_1537"
}

Peković, O., Stupar, S., Simonović, A., Petrašinović, D.,& Zorić, N.. (2012). Experimental determination of guy wire tension. in 29th DANUBlA-ADRIA Symposium on Advances in Experimental Mechanics, DAS 2012
University of Belgrade., 238-241.
https://hdl.handle.net/21.15107/rcub_machinery_1537

Peković O, Stupar S, Simonović A, Petrašinović D, Zorić N. Experimental determination of guy wire tension. in 29th DANUBlA-ADRIA Symposium on Advances in Experimental Mechanics, DAS 2012. 2012;:238-241.
https://hdl.handle.net/21.15107/rcub_machinery_1537 .

Peković, Ognjen, Stupar, Slobodan, Simonović, Aleksandar, Petrašinović, Danilo, Zorić, Nemanja, "Experimental determination of guy wire tension" in 29th DANUBlA-ADRIA Symposium on Advances in Experimental Mechanics, DAS 2012 (2012):238-241,
https://hdl.handle.net/21.15107/rcub_machinery_1537 .

TY  - GEN
AU  - Petrašinović, Danilo
AU  - Petrašinović, Nikola
AU  - Stupar, Slobodan
AU  - Grbović, Aleksandar
AU  - Simonović, Aleksandar
AU  - Svorcan, Jelena
PY  - 2012
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4454
T2  - Универзитет у Београду - Машински факултет
T1  - Испитна скела - инсталација за испитивање ваздухопловних конструкција на замор
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4454
ER  - 

@misc{
author = "Petrašinović, Danilo and Petrašinović, Nikola and Stupar, Slobodan and Grbović, Aleksandar and Simonović, Aleksandar and Svorcan, Jelena",
year = "2012",
journal = "Универзитет у Београду - Машински факултет",
title = "Испитна скела - инсталација за испитивање ваздухопловних конструкција на замор",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4454"
}

Petrašinović, D., Petrašinović, N., Stupar, S., Grbović, A., Simonović, A.,& Svorcan, J.. (2012). Испитна скела - инсталација за испитивање ваздухопловних конструкција на замор. in Универзитет у Београду - Машински факултет.
https://hdl.handle.net/21.15107/rcub_machinery_4454

Petrašinović D, Petrašinović N, Stupar S, Grbović A, Simonović A, Svorcan J. Испитна скела - инсталација за испитивање ваздухопловних конструкција на замор. in Универзитет у Београду - Машински факултет. 2012;.
https://hdl.handle.net/21.15107/rcub_machinery_4454 .

Petrašinović, Danilo, Petrašinović, Nikola, Stupar, Slobodan, Grbović, Aleksandar, Simonović, Aleksandar, Svorcan, Jelena, "Испитна скела - инсталација за испитивање ваздухопловних конструкција на замор" in Универзитет у Београду - Машински факултет (2012),
https://hdl.handle.net/21.15107/rcub_machinery_4454 .

TY  - JOUR
AU  - Petrašinović, Danilo
AU  - Rašuo, Boško
AU  - Petrašinović, Nikola
PY  - 2012
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1475
AB  - In the present work, duralumin aircraft spar fatigue life is evaluated by extended finite element method (XFEM) under cyclic loading condition. The effect of the crack growth on the fatigue life of aircraft spar is discussed in detail. The values of stress intensity factors (SIFs) are extracted from the XFEM solution. Standard Paris fatigue crack growth law (currently, the only one incorporated in Abaqus) is used for the fatigue life estimation. Obtained results are compared with previously obtained experimental results.
PB  - Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek
T2  - Tehnički vjesnik
T1  - Extended finite element method (xfem) applied to aircraft duralumin spar fatigue life estimation
EP  - 562
IS  - 3
SP  - 557
VL  - 19
UR  - https://hdl.handle.net/21.15107/rcub_machinery_1475
ER  - 

@article{
author = "Petrašinović, Danilo and Rašuo, Boško and Petrašinović, Nikola",
year = "2012",
abstract = "In the present work, duralumin aircraft spar fatigue life is evaluated by extended finite element method (XFEM) under cyclic loading condition. The effect of the crack growth on the fatigue life of aircraft spar is discussed in detail. The values of stress intensity factors (SIFs) are extracted from the XFEM solution. Standard Paris fatigue crack growth law (currently, the only one incorporated in Abaqus) is used for the fatigue life estimation. Obtained results are compared with previously obtained experimental results.",
publisher = "Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek",
journal = "Tehnički vjesnik",
title = "Extended finite element method (xfem) applied to aircraft duralumin spar fatigue life estimation",
pages = "562-557",
number = "3",
volume = "19",
url = "https://hdl.handle.net/21.15107/rcub_machinery_1475"
}

Petrašinović, D., Rašuo, B.,& Petrašinović, N.. (2012). Extended finite element method (xfem) applied to aircraft duralumin spar fatigue life estimation. in Tehnički vjesnik
Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek., 19(3), 557-562.
https://hdl.handle.net/21.15107/rcub_machinery_1475

Petrašinović D, Rašuo B, Petrašinović N. Extended finite element method (xfem) applied to aircraft duralumin spar fatigue life estimation. in Tehnički vjesnik. 2012;19(3):557-562.
https://hdl.handle.net/21.15107/rcub_machinery_1475 .

Petrašinović, Danilo, Rašuo, Boško, Petrašinović, Nikola, "Extended finite element method (xfem) applied to aircraft duralumin spar fatigue life estimation" in Tehnički vjesnik, 19, no. 3 (2012):557-562,
https://hdl.handle.net/21.15107/rcub_machinery_1475 .