TY  - CONF
AU  - Dančuo, Zorana
AU  - Kostić, Ivan
AU  - Kostić, Olivera
AU  - Bengin, Aleksandar
AU  - Vorotović, Goran
PY  - 2024
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7386
PB  - Springer Nature Switzerland AG
T1  - Influence of Thickness Ratio on the Aerodynamic Characteristics of a Family of Hybrid Semielliptical Dolphin Airfoils
DO  - 10.1007/978-3-031-42041-2_1
ER  - 

@conference{
author = "Dančuo, Zorana and Kostić, Ivan and Kostić, Olivera and Bengin, Aleksandar and Vorotović, Goran",
year = "2024",
publisher = "Springer Nature Switzerland AG",
title = "Influence of Thickness Ratio on the Aerodynamic Characteristics of a Family of Hybrid Semielliptical Dolphin Airfoils",
doi = "10.1007/978-3-031-42041-2_1"
}

Dančuo, Z., Kostić, I., Kostić, O., Bengin, A.,& Vorotović, G.. (2024). Influence of Thickness Ratio on the Aerodynamic Characteristics of a Family of Hybrid Semielliptical Dolphin Airfoils. 
Springer Nature Switzerland AG..
https://doi.org/10.1007/978-3-031-42041-2_1

Dančuo Z, Kostić I, Kostić O, Bengin A, Vorotović G. Influence of Thickness Ratio on the Aerodynamic Characteristics of a Family of Hybrid Semielliptical Dolphin Airfoils. 2024;.
doi:10.1007/978-3-031-42041-2_1 .

Dančuo, Zorana, Kostić, Ivan, Kostić, Olivera, Bengin, Aleksandar, Vorotović, Goran, "Influence of Thickness Ratio on the Aerodynamic Characteristics of a Family of Hybrid Semielliptical Dolphin Airfoils" (2024),
https://doi.org/10.1007/978-3-031-42041-2_1 . .

TY  - JOUR
AU  - Dančuo, Zorana
AU  - Kostić, Ivan
AU  - Kostić, Olivera
AU  - Bengin, Aleksandar
AU  - Vorotović, Goran
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3712
AB  - Iosif Taposu has formulated a mathematical model and generated a family of air-foils whose geometry resembles the dolphin shape. These airfoils are characterized by a sharp leading edge and experiments have proven that they can achieve better aerodynamic characteristics at very high angles of attack than certain classical airfoils, with the nose geometry inclined downwards. On the other hand, they have not been applied to any commercial general aviation aircraft. The authors of this paper have been motivated to compare the aerodynamic characteristics of widely used NACA 2415 airfoil with Taposu???s Dolphin that would have the same princi-pal geometric characteristics. A CFD calculation model has been established and applied on NACA 2415. The results were compared with NACA experiments and very good agreements have been achieved in the major domains of lift and polar curves. The same CFD model has been applied on the counterpart Dolphin 2415. Results have shown that the Dolphin has a slightly higher lift/drag ratio in the lift coefficient domain 0.1-0.35 than NACA. On the other hand, at higher and lower lift coefficients, its aerodynamic characteristics were drastically below those of the NACA section, due to the unfavorable influence of the Dolphin???s sharp nose. A series of the Dolphin???s leading edge modifications has been investigated, gradually improving its aerodynamics. Finally, version M4, consisting of about 70% of Dol-phin???s original rear domain and 30% of the new nose shape, managed to exceed the NACA???s characteristics, thus paving the way to investigate the Dolphin hybrids that could be suitable for the general aviation industry.
PB  - Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd
T2  - Thermal Science
T1  - Initial development of the hybrid semielliptical-dolphin airfoil
EP  - 2210
IS  - 3
SP  - 2199
VL  - 26
DO  - 10.2298/TSCI210515234D
ER  - 

@article{
author = "Dančuo, Zorana and Kostić, Ivan and Kostić, Olivera and Bengin, Aleksandar and Vorotović, Goran",
year = "2022",
abstract = "Iosif Taposu has formulated a mathematical model and generated a family of air-foils whose geometry resembles the dolphin shape. These airfoils are characterized by a sharp leading edge and experiments have proven that they can achieve better aerodynamic characteristics at very high angles of attack than certain classical airfoils, with the nose geometry inclined downwards. On the other hand, they have not been applied to any commercial general aviation aircraft. The authors of this paper have been motivated to compare the aerodynamic characteristics of widely used NACA 2415 airfoil with Taposu???s Dolphin that would have the same princi-pal geometric characteristics. A CFD calculation model has been established and applied on NACA 2415. The results were compared with NACA experiments and very good agreements have been achieved in the major domains of lift and polar curves. The same CFD model has been applied on the counterpart Dolphin 2415. Results have shown that the Dolphin has a slightly higher lift/drag ratio in the lift coefficient domain 0.1-0.35 than NACA. On the other hand, at higher and lower lift coefficients, its aerodynamic characteristics were drastically below those of the NACA section, due to the unfavorable influence of the Dolphin???s sharp nose. A series of the Dolphin???s leading edge modifications has been investigated, gradually improving its aerodynamics. Finally, version M4, consisting of about 70% of Dol-phin???s original rear domain and 30% of the new nose shape, managed to exceed the NACA???s characteristics, thus paving the way to investigate the Dolphin hybrids that could be suitable for the general aviation industry.",
publisher = "Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd",
journal = "Thermal Science",
title = "Initial development of the hybrid semielliptical-dolphin airfoil",
pages = "2210-2199",
number = "3",
volume = "26",
doi = "10.2298/TSCI210515234D"
}

Dančuo, Z., Kostić, I., Kostić, O., Bengin, A.,& Vorotović, G.. (2022). Initial development of the hybrid semielliptical-dolphin airfoil. in Thermal Science
Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd., 26(3), 2199-2210.
https://doi.org/10.2298/TSCI210515234D

Dančuo Z, Kostić I, Kostić O, Bengin A, Vorotović G. Initial development of the hybrid semielliptical-dolphin airfoil. in Thermal Science. 2022;26(3):2199-2210.
doi:10.2298/TSCI210515234D .

Dančuo, Zorana, Kostić, Ivan, Kostić, Olivera, Bengin, Aleksandar, Vorotović, Goran, "Initial development of the hybrid semielliptical-dolphin airfoil" in Thermal Science, 26, no. 3 (2022):2199-2210,
https://doi.org/10.2298/TSCI210515234D . .

TY  - JOUR
AU  - Ranđelović, Dušan M.
AU  - Vorotović, Goran
AU  - Bengin, Aleksandar
AU  - Petrović, Pavle N.
PY  - 2021
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3554
AB  - Cilj ovog istraživanja je procena različitih low-cost senzora za merenje visine leta bespilotne letelice sa više rotora na malim visinama. Primenjene su metode filtriranja podataka i druge metode u cilju optimizacije performansi i tačnosti merenja senzora. Izvšrena su merenja visine leta, a podaci su uskladišteni za kasniju analizu u odnosu na stvarnu visinu leta. Izračunati su stepeni korelacije i srednja kvadratna greška u merenju senzora sa ciljem procene rada senzora. Na osnovu rezultata istraživanja moguće je odrediti izbor adekvatnog senzora za ovu specifičnu primenu. Ovo istraživanje je pokazalo da je u uslovima ovog eksperimenta najbolje rezultate imao lidar senzor Garmin LIDAR-Lite V3HP i senzor Bosch Sensortech BME280 sa mogućnošću istovremenog merenja vlažnosti vazduha, atmosferskog pritiska i temperature.
AB  - The goal of this research is to assess the different low-cost sensors for flight altitude measuring of a multirotor UAV at low altitude flight. For optimizing the sensor performances and accuracy, data filtering and other methods were applied. The flight altitude data were collected and stored for later analysis with reference to the true altitude. The correlation coefficient and the mean squared error were calculated in order to assess the sensors' performance. On the basis of the results of the study, it was possible to determine the choice of the adequate sensor for this specific use. The study showed that the best characteristics for this experiment conditions had the Garmin LIDAR-Lite V3HP sensor and the Bosch Sensortech BME280 that combined air humidity, atmospheric pressure, and air temperature sensor.
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Merenje visine leta kvadkoptera pomoću low-cost barometarskog, infracrvenog, ultrazvučnog i lidar senzora
T1  - Quadcopter altitude estimation using low-cost barometric, infrared, ultrasonic and LIDAR sensors
EP  - 28
IS  - 1
SP  - 21
VL  - 49
DO  - 10.5937/fme2101021R
ER  - 

@article{
author = "Ranđelović, Dušan M. and Vorotović, Goran and Bengin, Aleksandar and Petrović, Pavle N.",
year = "2021",
abstract = "Cilj ovog istraživanja je procena različitih low-cost senzora za merenje visine leta bespilotne letelice sa više rotora na malim visinama. Primenjene su metode filtriranja podataka i druge metode u cilju optimizacije performansi i tačnosti merenja senzora. Izvšrena su merenja visine leta, a podaci su uskladišteni za kasniju analizu u odnosu na stvarnu visinu leta. Izračunati su stepeni korelacije i srednja kvadratna greška u merenju senzora sa ciljem procene rada senzora. Na osnovu rezultata istraživanja moguće je odrediti izbor adekvatnog senzora za ovu specifičnu primenu. Ovo istraživanje je pokazalo da je u uslovima ovog eksperimenta najbolje rezultate imao lidar senzor Garmin LIDAR-Lite V3HP i senzor Bosch Sensortech BME280 sa mogućnošću istovremenog merenja vlažnosti vazduha, atmosferskog pritiska i temperature., The goal of this research is to assess the different low-cost sensors for flight altitude measuring of a multirotor UAV at low altitude flight. For optimizing the sensor performances and accuracy, data filtering and other methods were applied. The flight altitude data were collected and stored for later analysis with reference to the true altitude. The correlation coefficient and the mean squared error were calculated in order to assess the sensors' performance. On the basis of the results of the study, it was possible to determine the choice of the adequate sensor for this specific use. The study showed that the best characteristics for this experiment conditions had the Garmin LIDAR-Lite V3HP sensor and the Bosch Sensortech BME280 that combined air humidity, atmospheric pressure, and air temperature sensor.",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Merenje visine leta kvadkoptera pomoću low-cost barometarskog, infracrvenog, ultrazvučnog i lidar senzora, Quadcopter altitude estimation using low-cost barometric, infrared, ultrasonic and LIDAR sensors",
pages = "28-21",
number = "1",
volume = "49",
doi = "10.5937/fme2101021R"
}

Ranđelović, D. M., Vorotović, G., Bengin, A.,& Petrović, P. N.. (2021). Merenje visine leta kvadkoptera pomoću low-cost barometarskog, infracrvenog, ultrazvučnog i lidar senzora. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 49(1), 21-28.
https://doi.org/10.5937/fme2101021R

Ranđelović DM, Vorotović G, Bengin A, Petrović PN. Merenje visine leta kvadkoptera pomoću low-cost barometarskog, infracrvenog, ultrazvučnog i lidar senzora. in FME Transactions. 2021;49(1):21-28.
doi:10.5937/fme2101021R .

Ranđelović, Dušan M., Vorotović, Goran, Bengin, Aleksandar, Petrović, Pavle N., "Merenje visine leta kvadkoptera pomoću low-cost barometarskog, infracrvenog, ultrazvučnog i lidar senzora" in FME Transactions, 49, no. 1 (2021):21-28,
https://doi.org/10.5937/fme2101021R . .

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

TY  - CONF
AU  - Komarov, Dragan
AU  - Svorcan, Jelena
AU  - Isaković, Jovan
AU  - Bengin, Aleksandar
AU  - Ivanov, Toni
PY  - 2014
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4455
AB  - Experimental investigation of supersonic flow at Mach number of 2 around a finned ogive cylinder at angles-of-attack ranging from 0° to 16° has been conducted in T-38 trisonic blow-down wind tunnel of the Serbian Military Technical Institute. A short description of testing process and measuring equipment is given. Results of a comparison of experimental and numerical results, that primarily include aerodynamic coefficients and pressure distribution, are presented and discussed. Numerical simulations were performed in ANSYS FLUENT with three Reynolds Averaged Navier-Stokes turbulence models of different complexity. Both structured and unstructured grids were generated, tested and compared and the influence of their nature and size has been considered. Base flow at zero angle-of-attack has been investigated in more detail and the accuracy and applicability of the used models is discussed. Computed fluid flow is presented in the form of pressure coefficient and Mach number contours and velocity vectors.
PB  - Belgrade : Military Technical Institute - VTI
C3  - 6th International scientific conference on defensive technologies OTEH 2014
T1  - Numerical and experimental assessment of supersonic turbulent flow around a finned ogive cylinder
EP  - 60
SP  - 55
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4455
ER  - 

@conference{
author = "Komarov, Dragan and Svorcan, Jelena and Isaković, Jovan and Bengin, Aleksandar and Ivanov, Toni",
year = "2014",
abstract = "Experimental investigation of supersonic flow at Mach number of 2 around a finned ogive cylinder at angles-of-attack ranging from 0° to 16° has been conducted in T-38 trisonic blow-down wind tunnel of the Serbian Military Technical Institute. A short description of testing process and measuring equipment is given. Results of a comparison of experimental and numerical results, that primarily include aerodynamic coefficients and pressure distribution, are presented and discussed. Numerical simulations were performed in ANSYS FLUENT with three Reynolds Averaged Navier-Stokes turbulence models of different complexity. Both structured and unstructured grids were generated, tested and compared and the influence of their nature and size has been considered. Base flow at zero angle-of-attack has been investigated in more detail and the accuracy and applicability of the used models is discussed. Computed fluid flow is presented in the form of pressure coefficient and Mach number contours and velocity vectors.",
publisher = "Belgrade : Military Technical Institute - VTI",
journal = "6th International scientific conference on defensive technologies OTEH 2014",
title = "Numerical and experimental assessment of supersonic turbulent flow around a finned ogive cylinder",
pages = "60-55",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4455"
}

Komarov, D., Svorcan, J., Isaković, J., Bengin, A.,& Ivanov, T.. (2014). Numerical and experimental assessment of supersonic turbulent flow around a finned ogive cylinder. in 6th International scientific conference on defensive technologies OTEH 2014
Belgrade : Military Technical Institute - VTI., 55-60.
https://hdl.handle.net/21.15107/rcub_machinery_4455

Komarov D, Svorcan J, Isaković J, Bengin A, Ivanov T. Numerical and experimental assessment of supersonic turbulent flow around a finned ogive cylinder. in 6th International scientific conference on defensive technologies OTEH 2014. 2014;:55-60.
https://hdl.handle.net/21.15107/rcub_machinery_4455 .

Komarov, Dragan, Svorcan, Jelena, Isaković, Jovan, Bengin, Aleksandar, Ivanov, Toni, "Numerical and experimental assessment of supersonic turbulent flow around a finned ogive cylinder" in 6th International scientific conference on defensive technologies OTEH 2014 (2014):55-60,
https://hdl.handle.net/21.15107/rcub_machinery_4455 .

TY  - JOUR
AU  - Rašuo, Boško
AU  - Dinulović, Mirko
AU  - Veg, Aleksandar
AU  - Grbović, Aleksandar
AU  - Bengin, Aleksandar
PY  - 2014
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1925
AB  - In this paper the harmonization of new wind turbine rotor blades development is given as well as the analysis of behavior by verification testing for a wind turbine rotor blade of composite materials. The design, fabrication, the status of wind energy standards and the analysis of behavior by full-scale verification testing for wind turbine rotor blades of composite laminated materials is given, too. The experimental methodology of static, vibratory and fatigue tests for the wind turbine rotor blade of composite laminated materials is presented. These verification tests were performed after the rotor blade development had been completed. The development of the rotor blade was performed using the PC computer with the CATIA designing system and the Gerber Garment cutter system. The blade was fabricated from composite laminated materials. The contour of airfoil was formed by a continuous structural pocket and a fiberglass skin.
PB  - Pergamon-Elsevier Science Ltd, Oxford
T2  - Renewable & Sustainable Energy Reviews
T1  - Harmonization of new wind turbine rotor blades development process: A review
EP  - 882
SP  - 874
VL  - 39
DO  - 10.1016/j.rser.2014.07.137
ER  - 

@article{
author = "Rašuo, Boško and Dinulović, Mirko and Veg, Aleksandar and Grbović, Aleksandar and Bengin, Aleksandar",
year = "2014",
abstract = "In this paper the harmonization of new wind turbine rotor blades development is given as well as the analysis of behavior by verification testing for a wind turbine rotor blade of composite materials. The design, fabrication, the status of wind energy standards and the analysis of behavior by full-scale verification testing for wind turbine rotor blades of composite laminated materials is given, too. The experimental methodology of static, vibratory and fatigue tests for the wind turbine rotor blade of composite laminated materials is presented. These verification tests were performed after the rotor blade development had been completed. The development of the rotor blade was performed using the PC computer with the CATIA designing system and the Gerber Garment cutter system. The blade was fabricated from composite laminated materials. The contour of airfoil was formed by a continuous structural pocket and a fiberglass skin.",
publisher = "Pergamon-Elsevier Science Ltd, Oxford",
journal = "Renewable & Sustainable Energy Reviews",
title = "Harmonization of new wind turbine rotor blades development process: A review",
pages = "882-874",
volume = "39",
doi = "10.1016/j.rser.2014.07.137"
}

Rašuo, B., Dinulović, M., Veg, A., Grbović, A.,& Bengin, A.. (2014). Harmonization of new wind turbine rotor blades development process: A review. in Renewable & Sustainable Energy Reviews
Pergamon-Elsevier Science Ltd, Oxford., 39, 874-882.
https://doi.org/10.1016/j.rser.2014.07.137

Rašuo B, Dinulović M, Veg A, Grbović A, Bengin A. Harmonization of new wind turbine rotor blades development process: A review. in Renewable & Sustainable Energy Reviews. 2014;39:874-882.
doi:10.1016/j.rser.2014.07.137 .

Rašuo, Boško, Dinulović, Mirko, Veg, Aleksandar, Grbović, Aleksandar, Bengin, Aleksandar, "Harmonization of new wind turbine rotor blades development process: A review" in Renewable & Sustainable Energy Reviews, 39 (2014):874-882,
https://doi.org/10.1016/j.rser.2014.07.137 . .

TY  - JOUR
AU  - Ilić, Zoran
AU  - Rašuo, Boško
AU  - Jovanović, Miroslav
AU  - Pekmezović, Sladjan
AU  - Bengin, Aleksandar
AU  - Dinulović, Mirko
PY  - 2014
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1959
AB  - Improving aircraft pilot comfort requires continuous work in decreasing vibrations in the seat. In order to determine the suitability and potential of cockpit floor - seat connections we conducted an experiment where measurements were taken and seat vibration analysis conducted. Vibrations parameters were measured for maximum engine and propeller speed. This analysis indicates that passive vibrations damping or cockpit floor - seat connections functionality depends on flights profile and vibrations frequency. The connection in question was behaving like a vibration multiplier on the 3rd and 4th harmonic as well as on the 3,5 sub-harmonic in individual flight modes on basic propeller rotation frequency, however, it behaved as a vibration silencer on all other frequencies. Analysis of the experimental data has shown that it would be justified to start improving the self adaptive unit for active vibration reduction for pilot seats.
PB  - Strojarski Facultet
T2  - Tehnički vjesnik
T1  - Potential connections of cockpit floor-seat on passive vibration reduction at a piston propelled airplane
EP  - 478
IS  - 3
SP  - 471
VL  - 21
UR  - https://hdl.handle.net/21.15107/rcub_machinery_1959
ER  - 

@article{
author = "Ilić, Zoran and Rašuo, Boško and Jovanović, Miroslav and Pekmezović, Sladjan and Bengin, Aleksandar and Dinulović, Mirko",
year = "2014",
abstract = "Improving aircraft pilot comfort requires continuous work in decreasing vibrations in the seat. In order to determine the suitability and potential of cockpit floor - seat connections we conducted an experiment where measurements were taken and seat vibration analysis conducted. Vibrations parameters were measured for maximum engine and propeller speed. This analysis indicates that passive vibrations damping or cockpit floor - seat connections functionality depends on flights profile and vibrations frequency. The connection in question was behaving like a vibration multiplier on the 3rd and 4th harmonic as well as on the 3,5 sub-harmonic in individual flight modes on basic propeller rotation frequency, however, it behaved as a vibration silencer on all other frequencies. Analysis of the experimental data has shown that it would be justified to start improving the self adaptive unit for active vibration reduction for pilot seats.",
publisher = "Strojarski Facultet",
journal = "Tehnički vjesnik",
title = "Potential connections of cockpit floor-seat on passive vibration reduction at a piston propelled airplane",
pages = "478-471",
number = "3",
volume = "21",
url = "https://hdl.handle.net/21.15107/rcub_machinery_1959"
}

Ilić, Z., Rašuo, B., Jovanović, M., Pekmezović, S., Bengin, A.,& Dinulović, M.. (2014). Potential connections of cockpit floor-seat on passive vibration reduction at a piston propelled airplane. in Tehnički vjesnik
Strojarski Facultet., 21(3), 471-478.
https://hdl.handle.net/21.15107/rcub_machinery_1959

Ilić Z, Rašuo B, Jovanović M, Pekmezović S, Bengin A, Dinulović M. Potential connections of cockpit floor-seat on passive vibration reduction at a piston propelled airplane. in Tehnički vjesnik. 2014;21(3):471-478.
https://hdl.handle.net/21.15107/rcub_machinery_1959 .

Ilić, Zoran, Rašuo, Boško, Jovanović, Miroslav, Pekmezović, Sladjan, Bengin, Aleksandar, Dinulović, Mirko, "Potential connections of cockpit floor-seat on passive vibration reduction at a piston propelled airplane" in Tehnički vjesnik, 21, no. 3 (2014):471-478,
https://hdl.handle.net/21.15107/rcub_machinery_1959 .

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

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

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

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

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

TY  - CHAP
AU  - Mitrović, Časlav
AU  - Bengin, Aleksandar
AU  - Petrović, Nebojša
AU  - Janković, Jovan
PY  - 2012
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/6679
AB  - Aerospace engineering is the primary branch of engineering concerned with the design, 
construction and science of flight vehicle. Consequently, they are usually the products of 
various technological and engineering disciplines including aerodynamics, propulsion, 
avionics, materials science, structural analysis and manufacturing. These technologies are 
collectively known as aerospace engineering. It is divided into two major and overlapping 
branches: aeronautical engineering and astronautical engineering. 
It is typically a large combination of many disciplines that makes up aeronautical 
engineering. The development and manufacturing of a modern flight vehicle is an extremely 
complex process and demands careful balance and compromise between abilities, design, 
available technology and costs. Aeronautical engineers design, test, and supervise the 
manufacture of aircraft. They also develop new technologies for use in aviation. 
Aeronautical Engineering is a chapter that encompasses challenging areas such as aircraft 
design, light-weight structures, stability and control of aeronautical vehicles, propulsion 
systems, and low and high speed aerodynamics. The field also covers their aerodynamic 
characteristics and behaviors, airfoil, control surfaces, lift, drag, and other properties. 
The chapter will include all our research and published papers.
PB  - IntechOpen Limited, London, SW7
T2  - Mechanical Engineering
T1  - Aeronautical Engineering
EP  - 442
IS  - chapter 18
SP  - 402
DO  - 10.5772/35789
ER  - 

@inbook{
author = "Mitrović, Časlav and Bengin, Aleksandar and Petrović, Nebojša and Janković, Jovan",
year = "2012",
abstract = "Aerospace engineering is the primary branch of engineering concerned with the design, 
construction and science of flight vehicle. Consequently, they are usually the products of 
various technological and engineering disciplines including aerodynamics, propulsion, 
avionics, materials science, structural analysis and manufacturing. These technologies are 
collectively known as aerospace engineering. It is divided into two major and overlapping 
branches: aeronautical engineering and astronautical engineering. 
It is typically a large combination of many disciplines that makes up aeronautical 
engineering. The development and manufacturing of a modern flight vehicle is an extremely 
complex process and demands careful balance and compromise between abilities, design, 
available technology and costs. Aeronautical engineers design, test, and supervise the 
manufacture of aircraft. They also develop new technologies for use in aviation. 
Aeronautical Engineering is a chapter that encompasses challenging areas such as aircraft 
design, light-weight structures, stability and control of aeronautical vehicles, propulsion 
systems, and low and high speed aerodynamics. The field also covers their aerodynamic 
characteristics and behaviors, airfoil, control surfaces, lift, drag, and other properties. 
The chapter will include all our research and published papers.",
publisher = "IntechOpen Limited, London, SW7",
journal = "Mechanical Engineering",
booktitle = "Aeronautical Engineering",
pages = "442-402",
number = "chapter 18",
doi = "10.5772/35789"
}

Mitrović, Č., Bengin, A., Petrović, N.,& Janković, J.. (2012). Aeronautical Engineering. in Mechanical Engineering
IntechOpen Limited, London, SW7.(chapter 18), 402-442.
https://doi.org/10.5772/35789

Mitrović Č, Bengin A, Petrović N, Janković J. Aeronautical Engineering. in Mechanical Engineering. 2012;(chapter 18):402-442.
doi:10.5772/35789 .

Mitrović, Časlav, Bengin, Aleksandar, Petrović, Nebojša, Janković, Jovan, "Aeronautical Engineering" in Mechanical Engineering, no. chapter 18 (2012):402-442,
https://doi.org/10.5772/35789 . .

TY  - JOUR
AU  - Rašuo, Boško
AU  - Bengin, Aleksandar
PY  - 2010
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1019
AB  - U radu je predstavljen metod određivanja optimalnih položaja vetrogeneratora u okviru farme, postavljene na terenu proizvoljne orografije. Optimalni položaji pojedinačnih vetrogeneratora su određeni tako da se postigne njihova maksimalna efikasnost. Metod je zasnovan na genetskom algoritmu kao optimizacionoj tehnici. Aerodinamički proračun vetrogeneratora je izveden na nestacionarnom potencijalnom strujnom polju. Lopatice vetrogeneratora su modelirane kao vrtložne površine, a vrtložni trag je modeliran upotrebom 'freewake' metode. Optimizacioni model je razvijen za dve funkcije cilja. Obe funkcije koriste ukupnu energiju dobijenu iz farme kao jednu od ključnih promenljivih. Druga funkcija cilja uključuje i ukupno ulaganje u svaku pojedinačnu turbinu, tako da optimizacioni proces uključuje i ukupan broj vetrogeneratora kao promenljivu. Metod je testiran na nekoliko proizvoljnih konfiguracija terena, pri čemu je posebna pažnja posvećena izboru parametara genetskog algoritma, kako bi se postigle povoljne performanse optimizacionog procesa.
AB  - This paper presents a method for determination of optimum positions of single wind turbines within the wind farms installed on arbitrary configured terrains, in order to achieve their maximum production effectiveness. This method is based on use of the genetic algorithm as optimization technique. The wind turbine aerodynamic calculation is unsteady, based on the blade modeled as a vortex lattice and a free-wake type airflow behind the blade. Optimization method is developed for two different fitness functions. Both functions use the total energy obtained from the farm as one of the key variables. The second also involves the total investments in a single wind turbine, so the optimization process can also include the total number of turbines as an additional variable. The method has been tested on several different terrain configurations, with special attention paid to the overall algorithm performance improvements by selecting certain genetic algorithm parameters.
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Optimizacija rasporeda vetrogeneratora unutar farme
T1  - Optimization of wind farm layout
EP  - 114
IS  - 3
SP  - 107
VL  - 38
UR  - https://hdl.handle.net/21.15107/rcub_machinery_1019
ER  - 

@article{
author = "Rašuo, Boško and Bengin, Aleksandar",
year = "2010",
abstract = "U radu je predstavljen metod određivanja optimalnih položaja vetrogeneratora u okviru farme, postavljene na terenu proizvoljne orografije. Optimalni položaji pojedinačnih vetrogeneratora su određeni tako da se postigne njihova maksimalna efikasnost. Metod je zasnovan na genetskom algoritmu kao optimizacionoj tehnici. Aerodinamički proračun vetrogeneratora je izveden na nestacionarnom potencijalnom strujnom polju. Lopatice vetrogeneratora su modelirane kao vrtložne površine, a vrtložni trag je modeliran upotrebom 'freewake' metode. Optimizacioni model je razvijen za dve funkcije cilja. Obe funkcije koriste ukupnu energiju dobijenu iz farme kao jednu od ključnih promenljivih. Druga funkcija cilja uključuje i ukupno ulaganje u svaku pojedinačnu turbinu, tako da optimizacioni proces uključuje i ukupan broj vetrogeneratora kao promenljivu. Metod je testiran na nekoliko proizvoljnih konfiguracija terena, pri čemu je posebna pažnja posvećena izboru parametara genetskog algoritma, kako bi se postigle povoljne performanse optimizacionog procesa., This paper presents a method for determination of optimum positions of single wind turbines within the wind farms installed on arbitrary configured terrains, in order to achieve their maximum production effectiveness. This method is based on use of the genetic algorithm as optimization technique. The wind turbine aerodynamic calculation is unsteady, based on the blade modeled as a vortex lattice and a free-wake type airflow behind the blade. Optimization method is developed for two different fitness functions. Both functions use the total energy obtained from the farm as one of the key variables. The second also involves the total investments in a single wind turbine, so the optimization process can also include the total number of turbines as an additional variable. The method has been tested on several different terrain configurations, with special attention paid to the overall algorithm performance improvements by selecting certain genetic algorithm parameters.",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Optimizacija rasporeda vetrogeneratora unutar farme, Optimization of wind farm layout",
pages = "114-107",
number = "3",
volume = "38",
url = "https://hdl.handle.net/21.15107/rcub_machinery_1019"
}

Rašuo, B.,& Bengin, A.. (2010). Optimizacija rasporeda vetrogeneratora unutar farme. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 38(3), 107-114.
https://hdl.handle.net/21.15107/rcub_machinery_1019

Rašuo B, Bengin A. Optimizacija rasporeda vetrogeneratora unutar farme. in FME Transactions. 2010;38(3):107-114.
https://hdl.handle.net/21.15107/rcub_machinery_1019 .

Rašuo, Boško, Bengin, Aleksandar, "Optimizacija rasporeda vetrogeneratora unutar farme" in FME Transactions, 38, no. 3 (2010):107-114,
https://hdl.handle.net/21.15107/rcub_machinery_1019 .

TY  - JOUR
AU  - Bekrić, Dragoljub
AU  - Mitrović, Časlav
AU  - Cvetković, Dragan
AU  - Bengin, Aleksandar
PY  - 2010
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1013
AB  - Efficiency and justification of hypergeometric functions application in achieving simple formulas used in numerical simulation of helicopter rotor blades theory are presented in this paper. Basic equations of stream field over helicopter rotor are formulated, their decomposition is made and mean induced velocity harmonics are integrally presented. Theoretical basis of hypergeometric function application in transformation of integral equations of k-bladed rotor average induced velocity into special functions follows. The necessary conditions for transformation hypergeometric functions into special functions are defined. Variants of integral transformation of expressions obtained are presented by a numerical simulation and solutions are found. This approach to cecure the effectivity of hypergeometric function application in helicopter rotor blades theory by numerical simulation provides a synthetic method, which can be used to define helicopter k-bladed main rotor optimal characteristics.
T2  - Strojniski Vestnik/Journal of Mechanical Engineering
T1  - Effectivity of Hypergeometric Function Application in the Numerical Simulation of the Helicopter Rotor Blades Theory
EP  - 22
IS  - 1
SP  - 18
VL  - 56
UR  - https://hdl.handle.net/21.15107/rcub_machinery_1013
ER  - 

@article{
author = "Bekrić, Dragoljub and Mitrović, Časlav and Cvetković, Dragan and Bengin, Aleksandar",
year = "2010",
abstract = "Efficiency and justification of hypergeometric functions application in achieving simple formulas used in numerical simulation of helicopter rotor blades theory are presented in this paper. Basic equations of stream field over helicopter rotor are formulated, their decomposition is made and mean induced velocity harmonics are integrally presented. Theoretical basis of hypergeometric function application in transformation of integral equations of k-bladed rotor average induced velocity into special functions follows. The necessary conditions for transformation hypergeometric functions into special functions are defined. Variants of integral transformation of expressions obtained are presented by a numerical simulation and solutions are found. This approach to cecure the effectivity of hypergeometric function application in helicopter rotor blades theory by numerical simulation provides a synthetic method, which can be used to define helicopter k-bladed main rotor optimal characteristics.",
journal = "Strojniski Vestnik/Journal of Mechanical Engineering",
title = "Effectivity of Hypergeometric Function Application in the Numerical Simulation of the Helicopter Rotor Blades Theory",
pages = "22-18",
number = "1",
volume = "56",
url = "https://hdl.handle.net/21.15107/rcub_machinery_1013"
}

Bekrić, D., Mitrović, Č., Cvetković, D.,& Bengin, A.. (2010). Effectivity of Hypergeometric Function Application in the Numerical Simulation of the Helicopter Rotor Blades Theory. in Strojniski Vestnik/Journal of Mechanical Engineering, 56(1), 18-22.
https://hdl.handle.net/21.15107/rcub_machinery_1013

Bekrić D, Mitrović Č, Cvetković D, Bengin A. Effectivity of Hypergeometric Function Application in the Numerical Simulation of the Helicopter Rotor Blades Theory. in Strojniski Vestnik/Journal of Mechanical Engineering. 2010;56(1):18-22.
https://hdl.handle.net/21.15107/rcub_machinery_1013 .

Bekrić, Dragoljub, Mitrović, Časlav, Cvetković, Dragan, Bengin, Aleksandar, "Effectivity of Hypergeometric Function Application in the Numerical Simulation of the Helicopter Rotor Blades Theory" in Strojniski Vestnik/Journal of Mechanical Engineering, 56, no. 1 (2010):18-22,
https://hdl.handle.net/21.15107/rcub_machinery_1013 .

TY  - JOUR
AU  - Mitrović, Časlav
AU  - Bengin, Aleksandar
AU  - Cvetković, Dragan
AU  - Bekrić, Dragoljub
PY  - 2010
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/1078
AB  - This paper presents on airfoil model which provides a method for optimal main helicopter rotor projection by viscous effect and unsteady lift simulation through algorithm and set of program entireties, applicable to the ideological and mail project of helicopter rotor. Based on real rotors theoretical consideration and the, numerical analysis considerations in this paper can be applied with sufficient accuracy in the analysis and constructive realizations of helicopter rotor in real conditions. The method for unsteady viscous flow simulations by inviscid techniques is developed. The aim of this paper is to determine helicopter rotor blade lift with the highest possible accuracy by using a singularity method and to define an optimal conception model of aerodynamic rotor projection corresponding to rotor behavior in real conditions and with sunk:lent quality nom the aspect of engineer use.
PB  - Assoc Mechanical Engineers Technicians Slovenia, Ljubljana
T2  - Strojniski Vestnik-Journal of Mechanical Engineering
T1  - An Optimal Main Helicopter Rotor Projection Model Obtained by Viscous Effects and Unsteady Lift Simulation
EP  - 367
IS  - 6
SP  - 357
VL  - 56
UR  - https://hdl.handle.net/21.15107/rcub_machinery_1078
ER  - 

@article{
author = "Mitrović, Časlav and Bengin, Aleksandar and Cvetković, Dragan and Bekrić, Dragoljub",
year = "2010",
abstract = "This paper presents on airfoil model which provides a method for optimal main helicopter rotor projection by viscous effect and unsteady lift simulation through algorithm and set of program entireties, applicable to the ideological and mail project of helicopter rotor. Based on real rotors theoretical consideration and the, numerical analysis considerations in this paper can be applied with sufficient accuracy in the analysis and constructive realizations of helicopter rotor in real conditions. The method for unsteady viscous flow simulations by inviscid techniques is developed. The aim of this paper is to determine helicopter rotor blade lift with the highest possible accuracy by using a singularity method and to define an optimal conception model of aerodynamic rotor projection corresponding to rotor behavior in real conditions and with sunk:lent quality nom the aspect of engineer use.",
publisher = "Assoc Mechanical Engineers Technicians Slovenia, Ljubljana",
journal = "Strojniski Vestnik-Journal of Mechanical Engineering",
title = "An Optimal Main Helicopter Rotor Projection Model Obtained by Viscous Effects and Unsteady Lift Simulation",
pages = "367-357",
number = "6",
volume = "56",
url = "https://hdl.handle.net/21.15107/rcub_machinery_1078"
}

Mitrović, Č., Bengin, A., Cvetković, D.,& Bekrić, D.. (2010). An Optimal Main Helicopter Rotor Projection Model Obtained by Viscous Effects and Unsteady Lift Simulation. in Strojniski Vestnik-Journal of Mechanical Engineering
Assoc Mechanical Engineers Technicians Slovenia, Ljubljana., 56(6), 357-367.
https://hdl.handle.net/21.15107/rcub_machinery_1078

Mitrović Č, Bengin A, Cvetković D, Bekrić D. An Optimal Main Helicopter Rotor Projection Model Obtained by Viscous Effects and Unsteady Lift Simulation. in Strojniski Vestnik-Journal of Mechanical Engineering. 2010;56(6):357-367.
https://hdl.handle.net/21.15107/rcub_machinery_1078 .

Mitrović, Časlav, Bengin, Aleksandar, Cvetković, Dragan, Bekrić, Dragoljub, "An Optimal Main Helicopter Rotor Projection Model Obtained by Viscous Effects and Unsteady Lift Simulation" in Strojniski Vestnik-Journal of Mechanical Engineering, 56, no. 6 (2010):357-367,
https://hdl.handle.net/21.15107/rcub_machinery_1078 .

TY  - JOUR
AU  - Bengin, Aleksandar
AU  - Mitrović, Časlav
AU  - Cvetković, Dragan
AU  - Bekrić, Dragoljub
AU  - Pegić, Slavko
PY  - 2008
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/789
AB  - This paper presents the numerical model developed for rotor blade aerodynamics loads calculation. The model is unsteady and fully three-dimensional. Helicopter blade is assumed to be rigid, and its motion during rotation is modeled in the manner that rotor presents a model of rotor of helicopter Aerospatiale SA 341 "Gazelle" (the blade is attached to the hub by flap, pitch and pseudo lead-lag hinges). Flow field around the blade is observed in succession of several azimuth locations. Flow field around helicopter rotor is modeled as fully three-dimensional, unsteady and potential. Blade aerodynamics is modeled using a lifting surface model. Rotor wake is generated from the straight elements of constant vorticity, released from the trailing edge, at fixed azimuth angles. These vortices represent both trailed and shed wake components, and are allowed to freely convect along local velocity vectors. Wake is modeled as free one, and its shape at certain moment can be calculated from simple kinematics laws applied on collocation points of the wake. Wake distortion is calculated only in the rotor near-field, i.e. in finite number of rotor revolutions. Vortex elements are modeled with vortex core. The radius of the vortex core is assumed independent of time, and it depends on circulation gradient at the point of vortex element released from the blade.
T2  - Strojniski Vestnik/Journal of Mechanical Engineering
T1  - Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight
EP  - 178
IS  - 3
SP  - 170
VL  - 54
UR  - https://hdl.handle.net/21.15107/rcub_machinery_789
ER  - 

@article{
author = "Bengin, Aleksandar and Mitrović, Časlav and Cvetković, Dragan and Bekrić, Dragoljub and Pegić, Slavko",
year = "2008",
abstract = "This paper presents the numerical model developed for rotor blade aerodynamics loads calculation. The model is unsteady and fully three-dimensional. Helicopter blade is assumed to be rigid, and its motion during rotation is modeled in the manner that rotor presents a model of rotor of helicopter Aerospatiale SA 341 "Gazelle" (the blade is attached to the hub by flap, pitch and pseudo lead-lag hinges). Flow field around the blade is observed in succession of several azimuth locations. Flow field around helicopter rotor is modeled as fully three-dimensional, unsteady and potential. Blade aerodynamics is modeled using a lifting surface model. Rotor wake is generated from the straight elements of constant vorticity, released from the trailing edge, at fixed azimuth angles. These vortices represent both trailed and shed wake components, and are allowed to freely convect along local velocity vectors. Wake is modeled as free one, and its shape at certain moment can be calculated from simple kinematics laws applied on collocation points of the wake. Wake distortion is calculated only in the rotor near-field, i.e. in finite number of rotor revolutions. Vortex elements are modeled with vortex core. The radius of the vortex core is assumed independent of time, and it depends on circulation gradient at the point of vortex element released from the blade.",
journal = "Strojniski Vestnik/Journal of Mechanical Engineering",
title = "Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight",
pages = "178-170",
number = "3",
volume = "54",
url = "https://hdl.handle.net/21.15107/rcub_machinery_789"
}

Bengin, A., Mitrović, Č., Cvetković, D., Bekrić, D.,& Pegić, S.. (2008). Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight. in Strojniski Vestnik/Journal of Mechanical Engineering, 54(3), 170-178.
https://hdl.handle.net/21.15107/rcub_machinery_789

Bengin A, Mitrović Č, Cvetković D, Bekrić D, Pegić S. Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight. in Strojniski Vestnik/Journal of Mechanical Engineering. 2008;54(3):170-178.
https://hdl.handle.net/21.15107/rcub_machinery_789 .

Bengin, Aleksandar, Mitrović, Časlav, Cvetković, Dragan, Bekrić, Dragoljub, Pegić, Slavko, "Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight" in Strojniski Vestnik/Journal of Mechanical Engineering, 54, no. 3 (2008):170-178,
https://hdl.handle.net/21.15107/rcub_machinery_789 .

TY  - JOUR
AU  - Bengin, Aleksandar
PY  - 2005
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/539
AB  - U radu je prikazan numerički model za izračunavanje aerodinamičkih sila na glavnom rotoru helikoptera. Model je nestacionaran i u potpunosti trodimenzionalan. Lopatica rotora helikoptera se smatra kruti telom, a njeno kretanje u toku rotacije je modelovano tako da rotor predstavlja model rotora helikoptera Aerospatiale SA 341 "Gazela" (lopatica je povezana sa glavom rotora preko zgloba mahanja, zgloba za promenu koraka i pseudo-zabacujućeg zgloba). Strujno polje oko lopatice se proračunava u nizu sukcesivnih azimutnih položaja. Strujno polje oko rotora je modelovano kao potpuno trodimenzionalno, nestacionarno i potencijalno. Lopatica je aerodinamički modelovana kao tanka noseća površina. Vrtložni krak rotora se sastoji od pravolinijskih vrtložnih niti konstantne vrtložnost koje napuštaju izlaznu ivicu lopatice u određenim azimutnim uglovima. Vrtložni trag se modeluje kao slobodan (free-wake model), a njegov oblik se izračunava u svakom trenutku vremena na osnovu jednostavnog kinematskog zakona primenjenog u kolokacionim tačkama vrtložnog traga. Promena oblika vrtložnog traga se izračunava samo u blizini lopatice, tj. za određeni broj revolucija rotora. Vrtložni elementi traga se modeluju sa jezgrom vrtloga. Poluprečnik jezgra je nepromenljiv tokom vremena, a zavisi jedino od gradijenta cirkulacije u tački u kojoj vrtložni trag napušta lopaticu.
AB  - This paper presents the numerical model developed for rotor blade aerodynamics loads calculation. The model is unsteady and fully three-dimensional. Helicopter blade is assumed to be rigid, and its motion during rotation is modeled in the manner that rotor presents a model of rotor of helicopter Aerospatiale SA 341 "Gazelle" (the blade is attached to the hub by flap, pitch and pseudo lead-lag hinges). Flow field around the blade is observed in succession of several azimuth locations. Flow field around helicopter rotor is modeled as fully three-dimensional, unsteady and potential. Blade aerodynamics is modeled using a lifting surface model. Rotor wake is generated from the straight elements of constant vorticity, released from the trailing edge, at fixed azimuth angles. These vortices represent both trailed and shed wake components, and are allowed to freely convect along local velocity vectors. Wake is modeled as free one, and its shape at certain moment can be calculated from simple kinematics laws applied on collocation points of the wake. Wake distortion is calculated only in the rotor near-field, i.e. in finite number of rotor revolutions. Vortex elements are modeled with vortex core. The radius of the vortex core is assumed independent of time, and it depends on circulation gradient at the point of vortex element released from the blade.
PB  - Univerzitet u Beogradu - Mašinski fakultet, Beograd
T2  - FME Transactions
T1  - Proračun trodimenzionalnog strujnog polja oko rotora helikoptera
T1  - Three-dimensional rotor flow calculation
EP  - 39
IS  - 1
SP  - 33
VL  - 33
UR  - https://hdl.handle.net/21.15107/rcub_machinery_539
ER  - 

@article{
author = "Bengin, Aleksandar",
year = "2005",
abstract = "U radu je prikazan numerički model za izračunavanje aerodinamičkih sila na glavnom rotoru helikoptera. Model je nestacionaran i u potpunosti trodimenzionalan. Lopatica rotora helikoptera se smatra kruti telom, a njeno kretanje u toku rotacije je modelovano tako da rotor predstavlja model rotora helikoptera Aerospatiale SA 341 "Gazela" (lopatica je povezana sa glavom rotora preko zgloba mahanja, zgloba za promenu koraka i pseudo-zabacujućeg zgloba). Strujno polje oko lopatice se proračunava u nizu sukcesivnih azimutnih položaja. Strujno polje oko rotora je modelovano kao potpuno trodimenzionalno, nestacionarno i potencijalno. Lopatica je aerodinamički modelovana kao tanka noseća površina. Vrtložni krak rotora se sastoji od pravolinijskih vrtložnih niti konstantne vrtložnost koje napuštaju izlaznu ivicu lopatice u određenim azimutnim uglovima. Vrtložni trag se modeluje kao slobodan (free-wake model), a njegov oblik se izračunava u svakom trenutku vremena na osnovu jednostavnog kinematskog zakona primenjenog u kolokacionim tačkama vrtložnog traga. Promena oblika vrtložnog traga se izračunava samo u blizini lopatice, tj. za određeni broj revolucija rotora. Vrtložni elementi traga se modeluju sa jezgrom vrtloga. Poluprečnik jezgra je nepromenljiv tokom vremena, a zavisi jedino od gradijenta cirkulacije u tački u kojoj vrtložni trag napušta lopaticu., This paper presents the numerical model developed for rotor blade aerodynamics loads calculation. The model is unsteady and fully three-dimensional. Helicopter blade is assumed to be rigid, and its motion during rotation is modeled in the manner that rotor presents a model of rotor of helicopter Aerospatiale SA 341 "Gazelle" (the blade is attached to the hub by flap, pitch and pseudo lead-lag hinges). Flow field around the blade is observed in succession of several azimuth locations. Flow field around helicopter rotor is modeled as fully three-dimensional, unsteady and potential. Blade aerodynamics is modeled using a lifting surface model. Rotor wake is generated from the straight elements of constant vorticity, released from the trailing edge, at fixed azimuth angles. These vortices represent both trailed and shed wake components, and are allowed to freely convect along local velocity vectors. Wake is modeled as free one, and its shape at certain moment can be calculated from simple kinematics laws applied on collocation points of the wake. Wake distortion is calculated only in the rotor near-field, i.e. in finite number of rotor revolutions. Vortex elements are modeled with vortex core. The radius of the vortex core is assumed independent of time, and it depends on circulation gradient at the point of vortex element released from the blade.",
publisher = "Univerzitet u Beogradu - Mašinski fakultet, Beograd",
journal = "FME Transactions",
title = "Proračun trodimenzionalnog strujnog polja oko rotora helikoptera, Three-dimensional rotor flow calculation",
pages = "39-33",
number = "1",
volume = "33",
url = "https://hdl.handle.net/21.15107/rcub_machinery_539"
}

Bengin, A.. (2005). Proračun trodimenzionalnog strujnog polja oko rotora helikoptera. in FME Transactions
Univerzitet u Beogradu - Mašinski fakultet, Beograd., 33(1), 33-39.
https://hdl.handle.net/21.15107/rcub_machinery_539

Bengin A. Proračun trodimenzionalnog strujnog polja oko rotora helikoptera. in FME Transactions. 2005;33(1):33-39.
https://hdl.handle.net/21.15107/rcub_machinery_539 .

Bengin, Aleksandar, "Proračun trodimenzionalnog strujnog polja oko rotora helikoptera" in FME Transactions, 33, no. 1 (2005):33-39,
https://hdl.handle.net/21.15107/rcub_machinery_539 .

TY  - CONF
AU  - Mitrović, Časlav
AU  - Kostić, Ivan
AU  - Cvetković, D.
AU  - Bengin, Aleksandar
PY  - 2002
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/258
AB  - This paper presents a simulation model of absorption effects during helmet collision with a hard obstacle.lt is based on a necessity to predict undesired consequences that may occur in case of helemet colision and impact with a hard obstacle. The primary aim of the paper is to determine real deformations during helmet collision with a hard obstacle by method of simulation of energy absorption effects and to establish a successfull model of optimum helmet design, from the aspect of engineering purposes, which corresponds to helmet behaviour in real conditions. Finite elements of the thin laminar shell type are used in helmet discretisation. Boundary conditions and loads are applied in such a way to simulate impact in the most realistic way.
C3  - 40th AIAA Aerospace Sciences Meeting and Exhibit
T1  - Numerical simulation of impact effects during helmet - Hard obstacle collision
UR  - https://hdl.handle.net/21.15107/rcub_machinery_258
ER  - 

@conference{
author = "Mitrović, Časlav and Kostić, Ivan and Cvetković, D. and Bengin, Aleksandar",
year = "2002",
abstract = "This paper presents a simulation model of absorption effects during helmet collision with a hard obstacle.lt is based on a necessity to predict undesired consequences that may occur in case of helemet colision and impact with a hard obstacle. The primary aim of the paper is to determine real deformations during helmet collision with a hard obstacle by method of simulation of energy absorption effects and to establish a successfull model of optimum helmet design, from the aspect of engineering purposes, which corresponds to helmet behaviour in real conditions. Finite elements of the thin laminar shell type are used in helmet discretisation. Boundary conditions and loads are applied in such a way to simulate impact in the most realistic way.",
journal = "40th AIAA Aerospace Sciences Meeting and Exhibit",
title = "Numerical simulation of impact effects during helmet - Hard obstacle collision",
url = "https://hdl.handle.net/21.15107/rcub_machinery_258"
}

Mitrović, Č., Kostić, I., Cvetković, D.,& Bengin, A.. (2002). Numerical simulation of impact effects during helmet - Hard obstacle collision. in 40th AIAA Aerospace Sciences Meeting and Exhibit.
https://hdl.handle.net/21.15107/rcub_machinery_258

Mitrović Č, Kostić I, Cvetković D, Bengin A. Numerical simulation of impact effects during helmet - Hard obstacle collision. in 40th AIAA Aerospace Sciences Meeting and Exhibit. 2002;.
https://hdl.handle.net/21.15107/rcub_machinery_258 .

Mitrović, Časlav, Kostić, Ivan, Cvetković, D., Bengin, Aleksandar, "Numerical simulation of impact effects during helmet - Hard obstacle collision" in 40th AIAA Aerospace Sciences Meeting and Exhibit (2002),
https://hdl.handle.net/21.15107/rcub_machinery_258 .

TY  - CONF
AU  - Kostić, Ivan
AU  - Mitrović, Časlav
AU  - Cvetković, D.
AU  - Bengin, Aleksandar
PY  - 2002
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/259
AB  - Most of the modern airliners, civilian and military cargo aircraft and fighters, cruise at speeds slightly lower than the speed of sound, in the so called lower transonic domain. For many of these aircraft, relevant design conditions imply wing optimization exactly for this speed domain. In that case, one of the primary steps is selection or design of airfoils for the wing and other lifting surfaces, which produce the least possible shock wave drag. For that purpose, an algorithm, presented in this paper, has been developed. It enables the numerical calculation of wave drag both for the existing and newly designed airfoils for certain aircraft, primarily aimed for use in the operational aircraft design. This algorithm is fairly simple and very reliable, which has been proven by comparing it's results, obtained through the computer program Tranpro, with the experimental results for airfoils tested at a number of most competent aeronautical institutions throughout the world.
C3  - 40th AIAA Aerospace Sciences Meeting and Exhibit
T1  - An algorithm of computation of airfoil drag in lower transonic domain
UR  - https://hdl.handle.net/21.15107/rcub_machinery_259
ER  - 

@conference{
author = "Kostić, Ivan and Mitrović, Časlav and Cvetković, D. and Bengin, Aleksandar",
year = "2002",
abstract = "Most of the modern airliners, civilian and military cargo aircraft and fighters, cruise at speeds slightly lower than the speed of sound, in the so called lower transonic domain. For many of these aircraft, relevant design conditions imply wing optimization exactly for this speed domain. In that case, one of the primary steps is selection or design of airfoils for the wing and other lifting surfaces, which produce the least possible shock wave drag. For that purpose, an algorithm, presented in this paper, has been developed. It enables the numerical calculation of wave drag both for the existing and newly designed airfoils for certain aircraft, primarily aimed for use in the operational aircraft design. This algorithm is fairly simple and very reliable, which has been proven by comparing it's results, obtained through the computer program Tranpro, with the experimental results for airfoils tested at a number of most competent aeronautical institutions throughout the world.",
journal = "40th AIAA Aerospace Sciences Meeting and Exhibit",
title = "An algorithm of computation of airfoil drag in lower transonic domain",
url = "https://hdl.handle.net/21.15107/rcub_machinery_259"
}

Kostić, I., Mitrović, Č., Cvetković, D.,& Bengin, A.. (2002). An algorithm of computation of airfoil drag in lower transonic domain. in 40th AIAA Aerospace Sciences Meeting and Exhibit.
https://hdl.handle.net/21.15107/rcub_machinery_259

Kostić I, Mitrović Č, Cvetković D, Bengin A. An algorithm of computation of airfoil drag in lower transonic domain. in 40th AIAA Aerospace Sciences Meeting and Exhibit. 2002;.
https://hdl.handle.net/21.15107/rcub_machinery_259 .

Kostić, Ivan, Mitrović, Časlav, Cvetković, D., Bengin, Aleksandar, "An algorithm of computation of airfoil drag in lower transonic domain" in 40th AIAA Aerospace Sciences Meeting and Exhibit (2002),
https://hdl.handle.net/21.15107/rcub_machinery_259 .

TY  - CONF
AU  - Cvetković, D.
AU  - Kostić, Ivan
AU  - Mitrović, Časlav
AU  - Bengin, Aleksandar
AU  - Radaković, D.
PY  - 2002
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/261
AB  - The helicopter is specific in regards to other traffictransportation means, not just by its structure but also by its motion possibilities. The helicopter can move vertically, float in the air, turn in place, move forward and lateral, and can perform these movements in combinations. Because of this, helicopter dynamics modeling and testing is a very complex problem. In the present, problems in helicopter flight dynamics are mostly solved in aid of modern computers. Though inevitable in many complex problems, computers do not make it possible to understand the physical nature of the problem. Fortunately, many problems considering helicopters can be analyzed without overly complex calculus and usually it is possible to obtain simple formulas. Though not suitable for calculus, these formulas, when designing the helicopter, enable a satisfactory interpretation of required aerodynamic and dynamic phenomena. The helicopter belongs to the group of aerospace systems and its traditional modeling may be divided into: a) three-dimensional (space) geometry and kinematics, and b) rigid body dynamics and fluid dynamics through which it moves. Recently, following models are being developed: c) elasticity model in intersubordinance with fluid, d) propulsion system model, e) hydraulic model and other actuators that achieve aerodynamic control, f) pilot behavior model, g) navigation system model, and h) beacon problem model. The mathematical model described in this paper is related to a) and b).
C3  - 40th AIAA Aerospace Sciences Meeting and Exhibit
T1  - Mathematical models of helicopter flight dynamics
UR  - https://hdl.handle.net/21.15107/rcub_machinery_261
ER  - 

@conference{
author = "Cvetković, D. and Kostić, Ivan and Mitrović, Časlav and Bengin, Aleksandar and Radaković, D.",
year = "2002",
abstract = "The helicopter is specific in regards to other traffictransportation means, not just by its structure but also by its motion possibilities. The helicopter can move vertically, float in the air, turn in place, move forward and lateral, and can perform these movements in combinations. Because of this, helicopter dynamics modeling and testing is a very complex problem. In the present, problems in helicopter flight dynamics are mostly solved in aid of modern computers. Though inevitable in many complex problems, computers do not make it possible to understand the physical nature of the problem. Fortunately, many problems considering helicopters can be analyzed without overly complex calculus and usually it is possible to obtain simple formulas. Though not suitable for calculus, these formulas, when designing the helicopter, enable a satisfactory interpretation of required aerodynamic and dynamic phenomena. The helicopter belongs to the group of aerospace systems and its traditional modeling may be divided into: a) three-dimensional (space) geometry and kinematics, and b) rigid body dynamics and fluid dynamics through which it moves. Recently, following models are being developed: c) elasticity model in intersubordinance with fluid, d) propulsion system model, e) hydraulic model and other actuators that achieve aerodynamic control, f) pilot behavior model, g) navigation system model, and h) beacon problem model. The mathematical model described in this paper is related to a) and b).",
journal = "40th AIAA Aerospace Sciences Meeting and Exhibit",
title = "Mathematical models of helicopter flight dynamics",
url = "https://hdl.handle.net/21.15107/rcub_machinery_261"
}

Cvetković, D., Kostić, I., Mitrović, Č., Bengin, A.,& Radaković, D.. (2002). Mathematical models of helicopter flight dynamics. in 40th AIAA Aerospace Sciences Meeting and Exhibit.
https://hdl.handle.net/21.15107/rcub_machinery_261

Cvetković D, Kostić I, Mitrović Č, Bengin A, Radaković D. Mathematical models of helicopter flight dynamics. in 40th AIAA Aerospace Sciences Meeting and Exhibit. 2002;.
https://hdl.handle.net/21.15107/rcub_machinery_261 .

Cvetković, D., Kostić, Ivan, Mitrović, Časlav, Bengin, Aleksandar, Radaković, D., "Mathematical models of helicopter flight dynamics" in 40th AIAA Aerospace Sciences Meeting and Exhibit (2002),
https://hdl.handle.net/21.15107/rcub_machinery_261 .