TY  - CONF
AU  - Svorcan, Jelena
AU  - Kovačević, Aleksandar
AU  - Ivanov, Toni
AU  - Jovanović, Miroslav
PY  - 2021
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4215
AB  - The main topic that is investigated in the present research is the turbulent flow around small-scale rotor blades in hovering flight condition. Small-scale rotorcraft imply somewhat specific operating conditions such as low Reynolds numbers, considerable viscous effects, degraded aerodynamic performances, flow separation, rotational flow, cyclic load cases, etc. It is therefore very important to perform as accurate as possible flow simulations that will enable obtaining practical aerodynamic data that can be used in subsequent structural and flight mechanics analyses. This paper provides the description of steps that are to be conducted when simulating hovering flow. Here, a quasi-steady approach, that combines RANS equations closed by k-ω SST turbulence model with the multiple reference frames, is adopted. Both quantitative and qualitative results are presented. Furthermore, the numerical model is validated against the obtained experimental data. The correspondence between the two sets of results can be considered satisfactory (relative differences for thrust coefficient amount to 15%, while they are even lower for the torque coefficient), while the effects of Reynolds number are not significant when throttle is above 40%.
PB  - Belgrade : Serbian Society of Mechanics
C3  - Proceedings / The 8th International Congress of Serbian Society of Mechanics, Kragujevac, Serbia, June 28-30, 2021
T1  - Numerical investigation of Reynolds number effects on rotor aerodynamic performances in hover
EP  - 534
SP  - 527
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4215
ER  - 

@conference{
author = "Svorcan, Jelena and Kovačević, Aleksandar and Ivanov, Toni and Jovanović, Miroslav",
year = "2021",
abstract = "The main topic that is investigated in the present research is the turbulent flow around small-scale rotor blades in hovering flight condition. Small-scale rotorcraft imply somewhat specific operating conditions such as low Reynolds numbers, considerable viscous effects, degraded aerodynamic performances, flow separation, rotational flow, cyclic load cases, etc. It is therefore very important to perform as accurate as possible flow simulations that will enable obtaining practical aerodynamic data that can be used in subsequent structural and flight mechanics analyses. This paper provides the description of steps that are to be conducted when simulating hovering flow. Here, a quasi-steady approach, that combines RANS equations closed by k-ω SST turbulence model with the multiple reference frames, is adopted. Both quantitative and qualitative results are presented. Furthermore, the numerical model is validated against the obtained experimental data. The correspondence between the two sets of results can be considered satisfactory (relative differences for thrust coefficient amount to 15%, while they are even lower for the torque coefficient), while the effects of Reynolds number are not significant when throttle is above 40%.",
publisher = "Belgrade : Serbian Society of Mechanics",
journal = "Proceedings / The 8th International Congress of Serbian Society of Mechanics, Kragujevac, Serbia, June 28-30, 2021",
title = "Numerical investigation of Reynolds number effects on rotor aerodynamic performances in hover",
pages = "534-527",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4215"
}

Svorcan, J., Kovačević, A., Ivanov, T.,& Jovanović, M.. (2021). Numerical investigation of Reynolds number effects on rotor aerodynamic performances in hover. in Proceedings / The 8th International Congress of Serbian Society of Mechanics, Kragujevac, Serbia, June 28-30, 2021
Belgrade : Serbian Society of Mechanics., 527-534.
https://hdl.handle.net/21.15107/rcub_machinery_4215

Svorcan J, Kovačević A, Ivanov T, Jovanović M. Numerical investigation of Reynolds number effects on rotor aerodynamic performances in hover. in Proceedings / The 8th International Congress of Serbian Society of Mechanics, Kragujevac, Serbia, June 28-30, 2021. 2021;:527-534.
https://hdl.handle.net/21.15107/rcub_machinery_4215 .

Svorcan, Jelena, Kovačević, Aleksandar, Ivanov, Toni, Jovanović, Miroslav, "Numerical investigation of Reynolds number effects on rotor aerodynamic performances in hover" in Proceedings / The 8th International Congress of Serbian Society of Mechanics, Kragujevac, Serbia, June 28-30, 2021 (2021):527-534,
https://hdl.handle.net/21.15107/rcub_machinery_4215 .

TY  - JOUR
AU  - Kovacević, Aleksandar
AU  - Svorcan, Jelena
AU  - Hasan, Mohammad Sakib
AU  - Ivanov, Toni
AU  - Jovanović, Miroslav
PY  - 2021
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3503
AB  - Purpose Modern unmanned air vehicles (UAVs) are usually equipped with rotors connected to electric motors that enable them to hover and fly in all directions. The purpose of the paper is to design optimal composite rotor blades for such small UAVs and investigate their aerodynamic performances both computationally and experimentally. Design/methodology/approach Artificial intelligence method (genetic algorithm) is used to optimize the blade airfoil described by six input parameters. Furthermore, different computational methods, e.g. vortex methods and computational fluid dynamics, blade element momentum theory and finite element method, are used to predict the aerodynamic performances of the optimized airfoil and complete rotor as well the structural behaviour of the blade, respectively. Finally, composite blade is manufactured and the rotor performance is also determined experimentally by thrust and torque measurements. Findings Complete process of blade design (including geometry definition and optimization, estimation of aerodynamic performances, structural analysis and blade manufacturing) is conducted and explained in detail. The correspondence between computed and measured thrust and torque curves of the optimal rotor is satisfactory (differences mostly remain below 15%), which validates and justifies the used design approach formulated specifically for low-cost, small-scale propeller blades. Furthermore, the proposed techniques can easily be applied to any kind of rotating lifting surfaces including helicopter or wind turbine blades. Originality/value Blade design methodology is simplified, shortened and made more flexible thus enabling the fast and economic production of propeller blades optimized for specific working conditions.
PB  - Emerald Group Publishing Ltd, Bingley
T2  - Aircraft Engineering and Aerospace Technology
T1  - Optimal propeller blade design, computation, manufacturing and experimental testing
EP  - 1332
IS  - 8
SP  - 1323
VL  - 93
DO  - 10.1108/AEAT-03-2021-0091
ER  - 

@article{
author = "Kovacević, Aleksandar and Svorcan, Jelena and Hasan, Mohammad Sakib and Ivanov, Toni and Jovanović, Miroslav",
year = "2021",
abstract = "Purpose Modern unmanned air vehicles (UAVs) are usually equipped with rotors connected to electric motors that enable them to hover and fly in all directions. The purpose of the paper is to design optimal composite rotor blades for such small UAVs and investigate their aerodynamic performances both computationally and experimentally. Design/methodology/approach Artificial intelligence method (genetic algorithm) is used to optimize the blade airfoil described by six input parameters. Furthermore, different computational methods, e.g. vortex methods and computational fluid dynamics, blade element momentum theory and finite element method, are used to predict the aerodynamic performances of the optimized airfoil and complete rotor as well the structural behaviour of the blade, respectively. Finally, composite blade is manufactured and the rotor performance is also determined experimentally by thrust and torque measurements. Findings Complete process of blade design (including geometry definition and optimization, estimation of aerodynamic performances, structural analysis and blade manufacturing) is conducted and explained in detail. The correspondence between computed and measured thrust and torque curves of the optimal rotor is satisfactory (differences mostly remain below 15%), which validates and justifies the used design approach formulated specifically for low-cost, small-scale propeller blades. Furthermore, the proposed techniques can easily be applied to any kind of rotating lifting surfaces including helicopter or wind turbine blades. Originality/value Blade design methodology is simplified, shortened and made more flexible thus enabling the fast and economic production of propeller blades optimized for specific working conditions.",
publisher = "Emerald Group Publishing Ltd, Bingley",
journal = "Aircraft Engineering and Aerospace Technology",
title = "Optimal propeller blade design, computation, manufacturing and experimental testing",
pages = "1332-1323",
number = "8",
volume = "93",
doi = "10.1108/AEAT-03-2021-0091"
}

Kovacević, A., Svorcan, J., Hasan, M. S., Ivanov, T.,& Jovanović, M.. (2021). Optimal propeller blade design, computation, manufacturing and experimental testing. in Aircraft Engineering and Aerospace Technology
Emerald Group Publishing Ltd, Bingley., 93(8), 1323-1332.
https://doi.org/10.1108/AEAT-03-2021-0091

Kovacević A, Svorcan J, Hasan MS, Ivanov T, Jovanović M. Optimal propeller blade design, computation, manufacturing and experimental testing. in Aircraft Engineering and Aerospace Technology. 2021;93(8):1323-1332.
doi:10.1108/AEAT-03-2021-0091 .

Kovacević, Aleksandar, Svorcan, Jelena, Hasan, Mohammad Sakib, Ivanov, Toni, Jovanović, Miroslav, "Optimal propeller blade design, computation, manufacturing and experimental testing" in Aircraft Engineering and Aerospace Technology, 93, no. 8 (2021):1323-1332,
https://doi.org/10.1108/AEAT-03-2021-0091 . .

TY  - CONF
AU  - Zorić, Nemanja
AU  - Tomović, Aleksandar
AU  - Jovanović, Miroslav
AU  - Lukić, Nebojša
AU  - Stokić, Zoran
PY  - 2017
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4074
AB  - Piezoelectric materials have a wide range of application on the active vibration control of
flexible structures as actuators and sensors due to its inverse and direct piezoelectric effect. In
order to increase performance of active vibration control, piezoelectric fibers are stacked into
single layer composite, making piezoelectric fiber-reinforced composite (PFRC) actuator and
sensor. These actuators and sensors are used for active vibration control of a thin-walled
structures, placing them at the surface of the structure. Since that, control performances depend
on sizes, positions and orientations of PFRC actuators and sensors. The aim of this paper is to
investigate the effect of PFRC actuator orientation and position (top or bottom) on controllability
of cross-ply and angle-ply antisymmetric composite plates for active vibration control. Depending
on layers' orientation, composite laminates possess coupling behavior (bending-stretching,
bending-shear coupling). Since antisymmetric laminates possess bending-stretching coupling
behavior, the effect of this behavior on controllability will be also discussed.
PB  - Serbian Society of Mechanics
C3  - 6th International Congress of Serbian Society of Mechanics, Tara, Serbia, 2017
T1  - Effect of piezoelectric fiber-reinforced composite (PFRC) actuator orientation on controllability of antisymmetric composite plates for active vibration control
IS  - C1a
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4074
ER  - 

@conference{
author = "Zorić, Nemanja and Tomović, Aleksandar and Jovanović, Miroslav and Lukić, Nebojša and Stokić, Zoran",
year = "2017",
abstract = "Piezoelectric materials have a wide range of application on the active vibration control of
flexible structures as actuators and sensors due to its inverse and direct piezoelectric effect. In
order to increase performance of active vibration control, piezoelectric fibers are stacked into
single layer composite, making piezoelectric fiber-reinforced composite (PFRC) actuator and
sensor. These actuators and sensors are used for active vibration control of a thin-walled
structures, placing them at the surface of the structure. Since that, control performances depend
on sizes, positions and orientations of PFRC actuators and sensors. The aim of this paper is to
investigate the effect of PFRC actuator orientation and position (top or bottom) on controllability
of cross-ply and angle-ply antisymmetric composite plates for active vibration control. Depending
on layers' orientation, composite laminates possess coupling behavior (bending-stretching,
bending-shear coupling). Since antisymmetric laminates possess bending-stretching coupling
behavior, the effect of this behavior on controllability will be also discussed.",
publisher = "Serbian Society of Mechanics",
journal = "6th International Congress of Serbian Society of Mechanics, Tara, Serbia, 2017",
title = "Effect of piezoelectric fiber-reinforced composite (PFRC) actuator orientation on controllability of antisymmetric composite plates for active vibration control",
number = "C1a",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4074"
}

Zorić, N., Tomović, A., Jovanović, M., Lukić, N.,& Stokić, Z.. (2017). Effect of piezoelectric fiber-reinforced composite (PFRC) actuator orientation on controllability of antisymmetric composite plates for active vibration control. in 6th International Congress of Serbian Society of Mechanics, Tara, Serbia, 2017
Serbian Society of Mechanics.(C1a).
https://hdl.handle.net/21.15107/rcub_machinery_4074

Zorić N, Tomović A, Jovanović M, Lukić N, Stokić Z. Effect of piezoelectric fiber-reinforced composite (PFRC) actuator orientation on controllability of antisymmetric composite plates for active vibration control. in 6th International Congress of Serbian Society of Mechanics, Tara, Serbia, 2017. 2017;(C1a).
https://hdl.handle.net/21.15107/rcub_machinery_4074 .

Zorić, Nemanja, Tomović, Aleksandar, Jovanović, Miroslav, Lukić, Nebojša, Stokić, Zoran, "Effect of piezoelectric fiber-reinforced composite (PFRC) actuator orientation on controllability of antisymmetric composite plates for active vibration control" in 6th International Congress of Serbian Society of Mechanics, Tara, Serbia, 2017, no. C1a (2017),
https://hdl.handle.net/21.15107/rcub_machinery_4074 .

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  - CONF
AU  - Jovanović, Miroslav
AU  - Guran, Ardeshir
AU  - Simonović, Aleksandar
AU  - Zorić, Nemanja
AU  - Lukić, Nebojša
AU  - Ilić, Slobodan
PY  - 2015
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4049
AB  - This paper present experimental modal analysis of rectangular thin plates with embedded
Piezoelectric Actuators and Sensors. This study gives the difference in natural frequencies of the
rectangular plate without and with integrated PZT actuator and PVDF sensors with the aim to
define the structural changes before the development of active control vibration system.
C3  - 21st International Conference ENGINEERING MECHANICS 2015, Svratka, Czech Republic
T1  - Exprimental modal analysis of a rectangular plate with embedded piezoelectric actuators and sensors
EP  - 129
SP  - 128
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4049
ER  - 

@conference{
author = "Jovanović, Miroslav and Guran, Ardeshir and Simonović, Aleksandar and Zorić, Nemanja and Lukić, Nebojša and Ilić, Slobodan",
year = "2015",
abstract = "This paper present experimental modal analysis of rectangular thin plates with embedded
Piezoelectric Actuators and Sensors. This study gives the difference in natural frequencies of the
rectangular plate without and with integrated PZT actuator and PVDF sensors with the aim to
define the structural changes before the development of active control vibration system.",
journal = "21st International Conference ENGINEERING MECHANICS 2015, Svratka, Czech Republic",
title = "Exprimental modal analysis of a rectangular plate with embedded piezoelectric actuators and sensors",
pages = "129-128",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4049"
}

Jovanović, M., Guran, A., Simonović, A., Zorić, N., Lukić, N.,& Ilić, S.. (2015). Exprimental modal analysis of a rectangular plate with embedded piezoelectric actuators and sensors. in 21st International Conference ENGINEERING MECHANICS 2015, Svratka, Czech Republic, 128-129.
https://hdl.handle.net/21.15107/rcub_machinery_4049

Jovanović M, Guran A, Simonović A, Zorić N, Lukić N, Ilić S. Exprimental modal analysis of a rectangular plate with embedded piezoelectric actuators and sensors. in 21st International Conference ENGINEERING MECHANICS 2015, Svratka, Czech Republic. 2015;:128-129.
https://hdl.handle.net/21.15107/rcub_machinery_4049 .

Jovanović, Miroslav, Guran, Ardeshir, Simonović, Aleksandar, Zorić, Nemanja, Lukić, Nebojša, Ilić, Slobodan, "Exprimental modal analysis of a rectangular plate with embedded piezoelectric actuators and sensors" in 21st International Conference ENGINEERING MECHANICS 2015, Svratka, Czech Republic (2015):128-129,
https://hdl.handle.net/21.15107/rcub_machinery_4049 .

TY  - CONF
AU  - Lukić, Nebojša
AU  - Simonović, Aleksandar
AU  - Zorić, Nemanja
AU  - Stupar, Slobodan
AU  - Jovanović, Miroslav
AU  - Ilić, Slobodan
PY  - 2014
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4047
AB  - This paper presents design, development and experimental verification of the active vibration control system of aluminum plate. The active structure consists of an aluminum rectangular plate as the host structure, strain gages as the sensor element and piezoceramic patch as the actuation element. Based on characteristics of integrated elements, the completely active vibration control system is designed and developed. The active vibration control system is controlled on PID control strategy. Control algorithm was implemented on PIC23MX440F256H microcontroller platform. The experiment considers active damping control under periodic excitation. Experiments are conducted to verify the effectiveness of the vibration suppression and to compare the damping effect with different adjustment of PID gains. Experimental results corresponding to develop active vibration control system are presented and affirmed effectiveness of vibration active damping on proposed active structure.
C3  - 11th International Symposium on Stability, Vibration, and Control of Machines and Structures (SVCS 2014), Belgrade, Serbia
T1  - Effectiveness of active vibration control on smart plate using a PID controller
EP  - 106
SP  - 98
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4047
ER  - 

@conference{
author = "Lukić, Nebojša and Simonović, Aleksandar and Zorić, Nemanja and Stupar, Slobodan and Jovanović, Miroslav and Ilić, Slobodan",
year = "2014",
abstract = "This paper presents design, development and experimental verification of the active vibration control system of aluminum plate. The active structure consists of an aluminum rectangular plate as the host structure, strain gages as the sensor element and piezoceramic patch as the actuation element. Based on characteristics of integrated elements, the completely active vibration control system is designed and developed. The active vibration control system is controlled on PID control strategy. Control algorithm was implemented on PIC23MX440F256H microcontroller platform. The experiment considers active damping control under periodic excitation. Experiments are conducted to verify the effectiveness of the vibration suppression and to compare the damping effect with different adjustment of PID gains. Experimental results corresponding to develop active vibration control system are presented and affirmed effectiveness of vibration active damping on proposed active structure.",
journal = "11th International Symposium on Stability, Vibration, and Control of Machines and Structures (SVCS 2014), Belgrade, Serbia",
title = "Effectiveness of active vibration control on smart plate using a PID controller",
pages = "106-98",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4047"
}

Lukić, N., Simonović, A., Zorić, N., Stupar, S., Jovanović, M.,& Ilić, S.. (2014). Effectiveness of active vibration control on smart plate using a PID controller. in 11th International Symposium on Stability, Vibration, and Control of Machines and Structures (SVCS 2014), Belgrade, Serbia, 98-106.
https://hdl.handle.net/21.15107/rcub_machinery_4047

Lukić N, Simonović A, Zorić N, Stupar S, Jovanović M, Ilić S. Effectiveness of active vibration control on smart plate using a PID controller. in 11th International Symposium on Stability, Vibration, and Control of Machines and Structures (SVCS 2014), Belgrade, Serbia. 2014;:98-106.
https://hdl.handle.net/21.15107/rcub_machinery_4047 .

Lukić, Nebojša, Simonović, Aleksandar, Zorić, Nemanja, Stupar, Slobodan, Jovanović, Miroslav, Ilić, Slobodan, "Effectiveness of active vibration control on smart plate using a PID controller" in 11th International Symposium on Stability, Vibration, and Control of Machines and Structures (SVCS 2014), Belgrade, Serbia (2014):98-106,
https://hdl.handle.net/21.15107/rcub_machinery_4047 .

TY  - CONF
AU  - Jovanović, Miroslav
AU  - Simonović, Aleksandar
AU  - Lukić, Nebojša
AU  - Zorić, Nemanja
AU  - Stupar, Slobodan
AU  - Ilić, Slobodan
PY  - 2014
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4045
AB  - This paper presents a design, development and experimental determination of the active vibration control
system of aluminum plate. Active structure consists of aluminum plate, strain gages like sensor platform and PZT
piezoelectric actuator. Based on characteristics of the integrated elements, the whole active vibration control sistem is
designed and developed. The active vibration control system is controlled by PI, PD and PID control strategies.
Control algorithm was implemented on the PIC32MX440F256H microcontroller platform. The experiment was
considered the change of damping ratio in the case of free vibration for different control strategies. The half-power
bandwidth method was using for determination the damping coeficient for different types of control. The experiments
confirmed the effectiveness of the developed system af active vibration control.
PB  - Belgrade : Military Technical Institute
C3  - 6th International Scientific Conference on Defensive Technologies (OTEH 2014), Beograd, Serbia
T1  - Experimental determination of active structure damping ratio using different control strategies in system of active vibration control
EP  - 544
SP  - 540
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4045
ER  - 

@conference{
author = "Jovanović, Miroslav and Simonović, Aleksandar and Lukić, Nebojša and Zorić, Nemanja and Stupar, Slobodan and Ilić, Slobodan",
year = "2014",
abstract = "This paper presents a design, development and experimental determination of the active vibration control
system of aluminum plate. Active structure consists of aluminum plate, strain gages like sensor platform and PZT
piezoelectric actuator. Based on characteristics of the integrated elements, the whole active vibration control sistem is
designed and developed. The active vibration control system is controlled by PI, PD and PID control strategies.
Control algorithm was implemented on the PIC32MX440F256H microcontroller platform. The experiment was
considered the change of damping ratio in the case of free vibration for different control strategies. The half-power
bandwidth method was using for determination the damping coeficient for different types of control. The experiments
confirmed the effectiveness of the developed system af active vibration control.",
publisher = "Belgrade : Military Technical Institute",
journal = "6th International Scientific Conference on Defensive Technologies (OTEH 2014), Beograd, Serbia",
title = "Experimental determination of active structure damping ratio using different control strategies in system of active vibration control",
pages = "544-540",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4045"
}

Jovanović, M., Simonović, A., Lukić, N., Zorić, N., Stupar, S.,& Ilić, S.. (2014). Experimental determination of active structure damping ratio using different control strategies in system of active vibration control. in 6th International Scientific Conference on Defensive Technologies (OTEH 2014), Beograd, Serbia
Belgrade : Military Technical Institute., 540-544.
https://hdl.handle.net/21.15107/rcub_machinery_4045

Jovanović M, Simonović A, Lukić N, Zorić N, Stupar S, Ilić S. Experimental determination of active structure damping ratio using different control strategies in system of active vibration control. in 6th International Scientific Conference on Defensive Technologies (OTEH 2014), Beograd, Serbia. 2014;:540-544.
https://hdl.handle.net/21.15107/rcub_machinery_4045 .

Jovanović, Miroslav, Simonović, Aleksandar, Lukić, Nebojša, Zorić, Nemanja, Stupar, Slobodan, Ilić, Slobodan, "Experimental determination of active structure damping ratio using different control strategies in system of active vibration control" in 6th International Scientific Conference on Defensive Technologies (OTEH 2014), Beograd, Serbia (2014):540-544,
https://hdl.handle.net/21.15107/rcub_machinery_4045 .

TY  - CONF
AU  - Stanković, Miloš
AU  - Ristić, Miloš
AU  - Simonović, Aleksandar
AU  - Jovanović, Miroslav
PY  - 2012
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7464
AB  - Thin-walled cylindrical shells are widely used in aerospace and automotive industries and in civil engineering. Usually their function is to transmit the axial loading – to be under pressure. When the pressure reaches a critical value, it comes to the buckling of the walls. Furthermore, due to small thickness of walls, there may be local imperfections, which further reduce the value of critical buckling stress. The imperfections present in thin cylinders are classified as geometrical imperfections, material imperfections and other imperfections. The imperfections such as circularity, cylindricity, local indentations, dents, crack, swellings, non-uniform thicknesses, etc., belong to geometrical imperfections whereas imperfections such as in-homogeneity, vacancies, impurities, etc., are classified as material imperfections. The residual stresses and strains induced during manufacturing, etc. are grouped as other imperfections[1]. 
Aim of this paper is to investigate how geometrical imperfections such as dents, positioned in the middle of aluminium-alloy cylindrical shell, have influence to critical buckling stress.
C3  - Proceedings of 29th Symposium on Advances in Experimental Mechanics “DAS 2012”
T1  - Buckling Behaviour of Dented Aluminium Alloy Cylindrical Shell Subjected to Uniform Axial Compression
EP  - 249
SP  - 246
UR  - https://hdl.handle.net/21.15107/rcub_machinery_7464
ER  - 

@conference{
author = "Stanković, Miloš and Ristić, Miloš and Simonović, Aleksandar and Jovanović, Miroslav",
year = "2012",
abstract = "Thin-walled cylindrical shells are widely used in aerospace and automotive industries and in civil engineering. Usually their function is to transmit the axial loading – to be under pressure. When the pressure reaches a critical value, it comes to the buckling of the walls. Furthermore, due to small thickness of walls, there may be local imperfections, which further reduce the value of critical buckling stress. The imperfections present in thin cylinders are classified as geometrical imperfections, material imperfections and other imperfections. The imperfections such as circularity, cylindricity, local indentations, dents, crack, swellings, non-uniform thicknesses, etc., belong to geometrical imperfections whereas imperfections such as in-homogeneity, vacancies, impurities, etc., are classified as material imperfections. The residual stresses and strains induced during manufacturing, etc. are grouped as other imperfections[1]. 
Aim of this paper is to investigate how geometrical imperfections such as dents, positioned in the middle of aluminium-alloy cylindrical shell, have influence to critical buckling stress.",
journal = "Proceedings of 29th Symposium on Advances in Experimental Mechanics “DAS 2012”",
title = "Buckling Behaviour of Dented Aluminium Alloy Cylindrical Shell Subjected to Uniform Axial Compression",
pages = "249-246",
url = "https://hdl.handle.net/21.15107/rcub_machinery_7464"
}

Stanković, M., Ristić, M., Simonović, A.,& Jovanović, M.. (2012). Buckling Behaviour of Dented Aluminium Alloy Cylindrical Shell Subjected to Uniform Axial Compression. in Proceedings of 29th Symposium on Advances in Experimental Mechanics “DAS 2012”, 246-249.
https://hdl.handle.net/21.15107/rcub_machinery_7464

Stanković M, Ristić M, Simonović A, Jovanović M. Buckling Behaviour of Dented Aluminium Alloy Cylindrical Shell Subjected to Uniform Axial Compression. in Proceedings of 29th Symposium on Advances in Experimental Mechanics “DAS 2012”. 2012;:246-249.
https://hdl.handle.net/21.15107/rcub_machinery_7464 .

Stanković, Miloš, Ristić, Miloš, Simonović, Aleksandar, Jovanović, Miroslav, "Buckling Behaviour of Dented Aluminium Alloy Cylindrical Shell Subjected to Uniform Axial Compression" in Proceedings of 29th Symposium on Advances in Experimental Mechanics “DAS 2012” (2012):246-249,
https://hdl.handle.net/21.15107/rcub_machinery_7464 .

TY  - CONF
AU  - Jovanović, Miroslav
AU  - Stupar, Slobodan
AU  - Simonović, Aleksandar
AU  - Zorić, Nemanja
AU  - Lukić, Nebojša
PY  - 2012
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4040
AB  - With advances in technology, the request for monitoring the integrity of aerospace structures is developed in
the direction to integrate the low-cost, light and reliable sensors. The new types of sensors can monitor structures
continuously for detection and assessment of damage progression in modern concept of aircraft structural health
monitoring (SHM). This paper deals with experimental determination the presence of damage on thin aluminium alloy
plate using the PVDF sensors and measures change in plate frequency before and after damage. Damage in structure
alters its dynamic characteristics. The change is characterized by variations in plate parameters i.e. frequencies,
damping values and mode shapes. Measurement of vibration with using the piezo film sensors (PVDF) and analysis
with adequate tools can determine the crack presence of damaged structure. The results of the presented experiment
can be implemented in different types of aircrafts structures in order to advance two modern concepts Aircraft Life
Extending (ALE) and SHM of aircraft and aircraft weapons pods.
PB  - Belgrade : Military Technical Institute
C3  - 5th International Scientific Conference on Defensive Technologies, OTEH 2012, Belgrade, Serbia
T1  - Experimental Determination of Damaged Location on Thin Plate Using Frequency Measurement
EP  - 181
SP  - 178
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4040
ER  - 

@conference{
author = "Jovanović, Miroslav and Stupar, Slobodan and Simonović, Aleksandar and Zorić, Nemanja and Lukić, Nebojša",
year = "2012",
abstract = "With advances in technology, the request for monitoring the integrity of aerospace structures is developed in
the direction to integrate the low-cost, light and reliable sensors. The new types of sensors can monitor structures
continuously for detection and assessment of damage progression in modern concept of aircraft structural health
monitoring (SHM). This paper deals with experimental determination the presence of damage on thin aluminium alloy
plate using the PVDF sensors and measures change in plate frequency before and after damage. Damage in structure
alters its dynamic characteristics. The change is characterized by variations in plate parameters i.e. frequencies,
damping values and mode shapes. Measurement of vibration with using the piezo film sensors (PVDF) and analysis
with adequate tools can determine the crack presence of damaged structure. The results of the presented experiment
can be implemented in different types of aircrafts structures in order to advance two modern concepts Aircraft Life
Extending (ALE) and SHM of aircraft and aircraft weapons pods.",
publisher = "Belgrade : Military Technical Institute",
journal = "5th International Scientific Conference on Defensive Technologies, OTEH 2012, Belgrade, Serbia",
title = "Experimental Determination of Damaged Location on Thin Plate Using Frequency Measurement",
pages = "181-178",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4040"
}

Jovanović, M., Stupar, S., Simonović, A., Zorić, N.,& Lukić, N.. (2012). Experimental Determination of Damaged Location on Thin Plate Using Frequency Measurement. in 5th International Scientific Conference on Defensive Technologies, OTEH 2012, Belgrade, Serbia
Belgrade : Military Technical Institute., 178-181.
https://hdl.handle.net/21.15107/rcub_machinery_4040

Jovanović M, Stupar S, Simonović A, Zorić N, Lukić N. Experimental Determination of Damaged Location on Thin Plate Using Frequency Measurement. in 5th International Scientific Conference on Defensive Technologies, OTEH 2012, Belgrade, Serbia. 2012;:178-181.
https://hdl.handle.net/21.15107/rcub_machinery_4040 .

Jovanović, Miroslav, Stupar, Slobodan, Simonović, Aleksandar, Zorić, Nemanja, Lukić, Nebojša, "Experimental Determination of Damaged Location on Thin Plate Using Frequency Measurement" in 5th International Scientific Conference on Defensive Technologies, OTEH 2012, Belgrade, Serbia (2012):178-181,
https://hdl.handle.net/21.15107/rcub_machinery_4040 .