Pub Date : 2018-02-28DOI: 10.15866/IREASE.V11I1.13595
V. Vavilov, F. Ismagilov, I. Khayrullin, R. Karimov
The paper proposes the use of High-Speed Permanent Magnet Generators Short-Time together with a gas turbine to start a starter generator. This paper describes the design features of the High-Speed Permanent Magnet Generators Short-Time with galvanically unconnected windings of the Gram using the example of a 3-phase and 6-phase HSPMGST with two biased three-phase windings with a pulse power of up to 10 kW and an operating time of not more than 1 minute with the breaks between starts not more than 5 minutes. The losses in these electric generators have been estimated, their thermal calculations have been carried out and experimental studies have also been carried out.
{"title":"High-Voltage Generator with Constant Magnets and Toroidal Winding for Intermitted Mode of Operation","authors":"V. Vavilov, F. Ismagilov, I. Khayrullin, R. Karimov","doi":"10.15866/IREASE.V11I1.13595","DOIUrl":"https://doi.org/10.15866/IREASE.V11I1.13595","url":null,"abstract":"The paper proposes the use of High-Speed Permanent Magnet Generators Short-Time together with a gas turbine to start a starter generator. This paper describes the design features of the High-Speed Permanent Magnet Generators Short-Time with galvanically unconnected windings of the Gram using the example of a 3-phase and 6-phase HSPMGST with two biased three-phase windings with a pulse power of up to 10 kW and an operating time of not more than 1 minute with the breaks between starts not more than 5 minutes. The losses in these electric generators have been estimated, their thermal calculations have been carried out and experimental studies have also been carried out.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"86 1","pages":"39-47"},"PeriodicalIF":0.0,"publicationDate":"2018-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"74199195","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2018-02-28DOI: 10.15866/IREASE.V11I1.12807
Khoan Tran
{"title":"Modified GA Tuning IPD Control for a Single Tilt Tri-Rotors UAV","authors":"Khoan Tran","doi":"10.15866/IREASE.V11I1.12807","DOIUrl":"https://doi.org/10.15866/IREASE.V11I1.12807","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"19 1","pages":"1"},"PeriodicalIF":0.0,"publicationDate":"2018-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"81023832","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2017-12-31DOI: 10.15866/IREASE.V10I6.13120
R. D. Sante, M. Vanali, E. Manconi, A. Perazzolo
In this work, the mechanical power transferred from the main gearbox to the cabin of a helicopter is obtained experimentally and used as an input to the vibroacoustic model of the fuselage for interior noise prediction. The estimation of the transmitted mechanical power is based on the experimental evaluation of the coupled mechanical mobility and in-flight accelerations measured at the points connecting the main gearbox to the fuselage, i.e. the antitorque plate and struts. The predicted values, together with the airborne noise sources (upper deck cavity noise and aerodynamic excitation due to the turbulent boundary layer on the fuselage skin) are then fed into the vibroacoustic model of the fuselage/cabin, which is obtained using a Statistical Energy Analysis (SEA) approach. The reliability of the approach is finally demonstrated by comparing the SEA simulation results and in-flight noise measurements in terms of sound pressure level in the passenger cabin compartment.
{"title":"Experimental and Statistical Energy Analysis of the Structure-borne Noise in a Helicopter Cabin","authors":"R. D. Sante, M. Vanali, E. Manconi, A. Perazzolo","doi":"10.15866/IREASE.V10I6.13120","DOIUrl":"https://doi.org/10.15866/IREASE.V10I6.13120","url":null,"abstract":"In this work, the mechanical power transferred from the main gearbox to the cabin of a helicopter is obtained experimentally and used as an input to the vibroacoustic model of the fuselage for interior noise prediction. The estimation of the transmitted mechanical power is based on the experimental evaluation of the coupled mechanical mobility and in-flight accelerations measured at the points connecting the main gearbox to the fuselage, i.e. the antitorque plate and struts. The predicted values, together with the airborne noise sources (upper deck cavity noise and aerodynamic excitation due to the turbulent boundary layer on the fuselage skin) are then fed into the vibroacoustic model of the fuselage/cabin, which is obtained using a Statistical Energy Analysis (SEA) approach. The reliability of the approach is finally demonstrated by comparing the SEA simulation results and in-flight noise measurements in terms of sound pressure level in the passenger cabin compartment.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"74 1","pages":"323-328"},"PeriodicalIF":0.0,"publicationDate":"2017-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"84386147","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2017-12-31DOI: 10.15866/IREASE.V10I6.13250
F. Ismagilov, V. Vavilov, D. Gusakov, V. Ayguzina
This paper examines the electromagnetic processes created by eddy currents in the rotor shroud and in the permanent magnets of high-speed electrical machines with a tooth-coil winding and high-coercivity permanent magnets. To estimate the influence of eddy currents, computer modelings of the electrical machines were made using the Ansys Maxwell software package. Losses and magnetic fields created by eddy currents were examined by these computer models. The harmonic composition of currents and voltages induced by eddy currents was investigated. It was found that the magnetic fields created by the eddy currents in the rotor shroud and the permanent magnets lead to the appearance of even harmonics in the output voltage and current of the electrical machine. To confirm the results of the computer simulation, an experimental study was carried out.
{"title":"Eddy Currents in the Rotor Shroud and Permanent Magnets of High-Speed Electrical Machines","authors":"F. Ismagilov, V. Vavilov, D. Gusakov, V. Ayguzina","doi":"10.15866/IREASE.V10I6.13250","DOIUrl":"https://doi.org/10.15866/IREASE.V10I6.13250","url":null,"abstract":"This paper examines the electromagnetic processes created by eddy currents in the rotor shroud and in the permanent magnets of high-speed electrical machines with a tooth-coil winding and high-coercivity permanent magnets. To estimate the influence of eddy currents, computer modelings of the electrical machines were made using the Ansys Maxwell software package. Losses and magnetic fields created by eddy currents were examined by these computer models. The harmonic composition of currents and voltages induced by eddy currents was investigated. It was found that the magnetic fields created by the eddy currents in the rotor shroud and the permanent magnets lead to the appearance of even harmonics in the output voltage and current of the electrical machine. To confirm the results of the computer simulation, an experimental study was carried out.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"73 1","pages":"329-336"},"PeriodicalIF":0.0,"publicationDate":"2017-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"86418276","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2017-12-31DOI: 10.15866/IREASE.V10I6.11841
A. D. Pizzo, L. P. D. Noia, R. Rizzo
The research in aviation is recently focusing on the so-called All Electric Aircraft which only utilizes the electric power to supply propulsion and all the airframe systems. Electric propulsion systems require a strategy of on-board energy management and of optimization criteria for electrical drives and energy storage systems to reduce the weights and balance the loads on-board the aircraft. The sizing of the energy storage system has a significant impact on the range, the energy consumption, and the related energy cost of the aircraft. In the paper is proposed an optimized sizing procedure for the battery energy storage system of an AEA, first is defined and modeled the propulsion system, then the optimized procedure is described and validated by means of simulations in case of a commercial twin engine four-seat aircraft. The study carried out an analysis of feasibility of all electric aircraft, focusing on one of the most critical parameters which is the energy storage mass. This parameter has a great influence on the aircraft performance, due in particular to the low energy density of the actual energy storage systems, which determines that a greatest part of energy is used for the battery transportation. The results reported and discussed at the end of the paper show the good results in terms of mass reduction and energy saving obtained by validating the proposed sizing procedure without affecting the safety.
{"title":"Energy Storage System sizing for a Twin Engine Four-seat Aircraft Electrical Propulsion","authors":"A. D. Pizzo, L. P. D. Noia, R. Rizzo","doi":"10.15866/IREASE.V10I6.11841","DOIUrl":"https://doi.org/10.15866/IREASE.V10I6.11841","url":null,"abstract":"The research in aviation is recently focusing on the so-called All Electric Aircraft which only utilizes the electric power to supply propulsion and all the airframe systems. Electric propulsion systems require a strategy of on-board energy management and of optimization criteria for electrical drives and energy storage systems to reduce the weights and balance the loads on-board the aircraft. The sizing of the energy storage system has a significant impact on the range, the energy consumption, and the related energy cost of the aircraft. In the paper is proposed an optimized sizing procedure for the battery energy storage system of an AEA, first is defined and modeled the propulsion system, then the optimized procedure is described and validated by means of simulations in case of a commercial twin engine four-seat aircraft. The study carried out an analysis of feasibility of all electric aircraft, focusing on one of the most critical parameters which is the energy storage mass. This parameter has a great influence on the aircraft performance, due in particular to the low energy density of the actual energy storage systems, which determines that a greatest part of energy is used for the battery transportation. The results reported and discussed at the end of the paper show the good results in terms of mass reduction and energy saving obtained by validating the proposed sizing procedure without affecting the safety.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"40 1","pages":"315-322"},"PeriodicalIF":0.0,"publicationDate":"2017-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"86283453","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2017-12-31DOI: 10.15866/IREASE.V10I6.12498
R. Bardera-Mora, A. Conesa, Mario Sánchez García
The flow control over an airfoil was experimentally investigated with a Dielectric Barrier Discharge (DBD) plasma actuator. A NACA 4418 airfoil was used and the fact that it is metallic is the main difference with the numerous articles about plasma actuators over airfoils. Metallic airfoils are normally avoided to reduce risk of arcing and electromagnetic interferences. The plasma actuator was located at x/c = 0.1 measured from the leading edge. Through the Schlieren visualization, the characteristics of the actuator in a quiescent ambient was observed, showing a double wall jet due to the interaction of the plasma actuator and the metallic airfoil used as substrate. One of them is a co-flow wall jet and the other one is a counter-flow wall jet. Time-averaged Particle Image Velocimetry (PIV) images were used to examine the flow for different angles of attack at Rec = 40.000 and Rec = 200.000 when plasma is on and off. Velocity maps show that the plasma actuation delays the separation for both low and moderate Reynolds numbers. The turbulent kinetic energy (TKE) and Reynolds stress values are reduced when plasma can control the flow, however plasma actuator increases these values when it does not avoid the separation. The velocity magnitude profiles show the influence of the co-flow wall jet near exposed-electrode but the counter-flow is not observed. A reduction of the wake with plasma actuation is also seen. The results confirm the authority of plasma actuators to control the flow separation over a metallic airfoil. The effectiveness and the global performance in applications such as wind turbines or UAVs at moderate Reynolds number, where metallic airfoils are used, is expected to be improved avoiding the separation with plasma actuators.
{"title":"Flow Separation Control with a Plasma Actuator Over a Metallic NACA 4418","authors":"R. Bardera-Mora, A. Conesa, Mario Sánchez García","doi":"10.15866/IREASE.V10I6.12498","DOIUrl":"https://doi.org/10.15866/IREASE.V10I6.12498","url":null,"abstract":"The flow control over an airfoil was experimentally investigated with a Dielectric Barrier Discharge (DBD) plasma actuator. A NACA 4418 airfoil was used and the fact that it is metallic is the main difference with the numerous articles about plasma actuators over airfoils. Metallic airfoils are normally avoided to reduce risk of arcing and electromagnetic interferences. The plasma actuator was located at x/c = 0.1 measured from the leading edge. Through the Schlieren visualization, the characteristics of the actuator in a quiescent ambient was observed, showing a double wall jet due to the interaction of the plasma actuator and the metallic airfoil used as substrate. One of them is a co-flow wall jet and the other one is a counter-flow wall jet. Time-averaged Particle Image Velocimetry (PIV) images were used to examine the flow for different angles of attack at Rec = 40.000 and Rec = 200.000 when plasma is on and off. Velocity maps show that the plasma actuation delays the separation for both low and moderate Reynolds numbers. The turbulent kinetic energy (TKE) and Reynolds stress values are reduced when plasma can control the flow, however plasma actuator increases these values when it does not avoid the separation. The velocity magnitude profiles show the influence of the co-flow wall jet near exposed-electrode but the counter-flow is not observed. A reduction of the wake with plasma actuation is also seen. The results confirm the authority of plasma actuators to control the flow separation over a metallic airfoil. The effectiveness and the global performance in applications such as wind turbines or UAVs at moderate Reynolds number, where metallic airfoils are used, is expected to be improved avoiding the separation with plasma actuators.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"112 1 1","pages":"308-314"},"PeriodicalIF":0.0,"publicationDate":"2017-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"83074306","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2017-12-31DOI: 10.15866/IREASE.V10I6.13458
M. Fakir, S. Khatun
In this paper an analysis is carried out to study the efficiency of heat distribution through fins using finite element method (FEM) and differential quadrature method ( DQM). Numerical solutions are obtained using both methods for temperature distribution over the fin surface. Analysis of surface solutions in terms of temperature and error distributions have been presented here. Solutions are also obtained using equally spaced (conventional) and non-equally spaced (optimum) mesh (nodal points) distribution techniques. Two-dimensional heat conduction problem has been solved in both equal and non-equal nodal points distribution cases (called here conventional FEM (CFEM) and conventional DQM (CDQM) and optimum FEM (OFEM) and optimum DQM (ODQM)). The obtained results are compared and investigated with exact results. The best results are found in OFEM solutions. It is also found that, ODQM solutions reach very close to OFEM solutions with negligible error, whereas CFEM and CDQM solutions diverges with increasing number of nodal(mesh) points.
{"title":"A Numerical Approach for Efficiency Analysis of Heat Distribution Through Fin","authors":"M. Fakir, S. Khatun","doi":"10.15866/IREASE.V10I6.13458","DOIUrl":"https://doi.org/10.15866/IREASE.V10I6.13458","url":null,"abstract":"In this paper an analysis is carried out to study the efficiency of heat distribution through fins using finite element method (FEM) and differential quadrature method ( DQM). Numerical solutions are obtained using both methods for temperature distribution over the fin surface. Analysis of surface solutions in terms of temperature and error distributions have been presented here. Solutions are also obtained using equally spaced (conventional) and non-equally spaced (optimum) mesh (nodal points) distribution techniques. Two-dimensional heat conduction problem has been solved in both equal and non-equal nodal points distribution cases (called here conventional FEM (CFEM) and conventional DQM (CDQM) and optimum FEM (OFEM) and optimum DQM (ODQM)). The obtained results are compared and investigated with exact results. The best results are found in OFEM solutions. It is also found that, ODQM solutions reach very close to OFEM solutions with negligible error, whereas CFEM and CDQM solutions diverges with increasing number of nodal(mesh) points.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"27 1","pages":"337"},"PeriodicalIF":0.0,"publicationDate":"2017-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"91093552","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2017-10-31DOI: 10.15866/IREASE.V10I5.12914
A. Perov
The paper is aimed at synthesizing and analyzing an optimal algorithm for co-tracking delays and phases of pseudolite signals of different power in local navigation systems using a theory of optimal parameter estimation for several signals received by a navigation receiver in the additive mixture of the receiver internal noise. The analysis of the synthesized tracking algorithm is based on the simulation modeling of a navigation receiver taking account of nonlinear processing in discriminators. New equations describing an optimal complex tracking system that compensate the interfering signals in the processing paths of several incoming signals have been obtained. It has been shown that the use of this system ensures a reliable reception of navigational signals of significantly different power, which is relevant for local navigation systems based on pseudolites. The obtained tracking algorithms can be used in navigation equipment of local pseudolite-based navigation systems and satellite radio navigation systems GLONASS, GPS, Galileo, etc., working with the support of local navigation systems, robust principal component analysis (RPCA), total variation (TV), discriminating internal layers from radio echo sounding data of ice sheets, conjugate gradient method.
{"title":"Synthesis of Processing Algorithm for Signals with Different Powers in Local Radio Navigation Systems","authors":"A. Perov","doi":"10.15866/IREASE.V10I5.12914","DOIUrl":"https://doi.org/10.15866/IREASE.V10I5.12914","url":null,"abstract":"The paper is aimed at synthesizing and analyzing an optimal algorithm for co-tracking delays and phases of pseudolite signals of different power in local navigation systems using a theory of optimal parameter estimation for several signals received by a navigation receiver in the additive mixture of the receiver internal noise. The analysis of the synthesized tracking algorithm is based on the simulation modeling of a navigation receiver taking account of nonlinear processing in discriminators. New equations describing an optimal complex tracking system that compensate the interfering signals in the processing paths of several incoming signals have been obtained. It has been shown that the use of this system ensures a reliable reception of navigational signals of significantly different power, which is relevant for local navigation systems based on pseudolites. The obtained tracking algorithms can be used in navigation equipment of local pseudolite-based navigation systems and satellite radio navigation systems GLONASS, GPS, Galileo, etc., working with the support of local navigation systems, robust principal component analysis (RPCA), total variation (TV), discriminating internal layers from radio echo sounding data of ice sheets, conjugate gradient method.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"151 1","pages":"282-288"},"PeriodicalIF":0.0,"publicationDate":"2017-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"83276812","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2017-10-31DOI: 10.15866/IREASE.V10I5.13818
L. P. D. Noia, A. D. Pizzo, S. Meo
The paper presents a generalized averaged model and a reduced-order averaged model of a dual active bridge bidirectional dc-dc converter, taking into account parasitic components. On the basis of these models, a particular non-linear voltage control scheme is suggested using an integral sliding mode control approach for driving the adopted single phase shift modulation technique. The main operative conditions of the converter have been examined through extensive simulations. The numerical results confirm the effectiveness of the proposed strategy. The suggested control exhibits a strong robustness against parameters variations and disturbances and presents a very simple implementation.
{"title":"Reduced-Order Averaged Model and Non-Linear Control of a Dual Active Bridge DC-DC Converter for Aerospace Applications","authors":"L. P. D. Noia, A. D. Pizzo, S. Meo","doi":"10.15866/IREASE.V10I5.13818","DOIUrl":"https://doi.org/10.15866/IREASE.V10I5.13818","url":null,"abstract":"The paper presents a generalized averaged model and a reduced-order averaged model of a dual active bridge bidirectional dc-dc converter, taking into account parasitic components. On the basis of these models, a particular non-linear voltage control scheme is suggested using an integral sliding mode control approach for driving the adopted single phase shift modulation technique. The main operative conditions of the converter have been examined through extensive simulations. The numerical results confirm the effectiveness of the proposed strategy. The suggested control exhibits a strong robustness against parameters variations and disturbances and presents a very simple implementation.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"155 1","pages":"259-266"},"PeriodicalIF":0.0,"publicationDate":"2017-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77479100","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2017-10-31DOI: 10.15866/IREASE.V10I5.12132
I. Penkov, D. Aleksandrov
The article discusses three-, four-, six-, and eight-rotor UAV (Unmanned Aerial Vehicle) mini helicopters in respect to power consumption. A tricopter has most long flight time, but despite this fact, the most effective is a quadcopter. CFD (Computational Fluid Dynamics) simulations were made with purpose to find more optimal relationship between coaxial rotors. It is shown that the total lifting force generated by a pair of coaxial rotors is less than the lifting force generated by two separately standing rotors of the same size. The flow from the upper rotor in a coaxial rotor pair partially compensates the pressure near the lower rotor. The most effective is use of two rotors with the same geometrical parameters. A less efficient scheme is with the smaller rotor located on top and the larger one in the bottom.
{"title":"Efficiency Optimization of Mini Unmanned Multicopter","authors":"I. Penkov, D. Aleksandrov","doi":"10.15866/IREASE.V10I5.12132","DOIUrl":"https://doi.org/10.15866/IREASE.V10I5.12132","url":null,"abstract":"The article discusses three-, four-, six-, and eight-rotor UAV (Unmanned Aerial Vehicle) mini helicopters in respect to power consumption. A tricopter has most long flight time, but despite this fact, the most effective is a quadcopter. CFD (Computational Fluid Dynamics) simulations were made with purpose to find more optimal relationship between coaxial rotors. It is shown that the total lifting force generated by a pair of coaxial rotors is less than the lifting force generated by two separately standing rotors of the same size. The flow from the upper rotor in a coaxial rotor pair partially compensates the pressure near the lower rotor. The most effective is use of two rotors with the same geometrical parameters. A less efficient scheme is with the smaller rotor located on top and the larger one in the bottom.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"31 1","pages":"267-276"},"PeriodicalIF":0.0,"publicationDate":"2017-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"81224836","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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