Optimization of Lift Force of Mini Quadrotor Helicopter by Changing of Gap Size between Rotors

Александров, Д. В.; Penkov, Igor

doi:10.4028/www.scientific.net/ssp.198.226

Cited by 15 publications

(9 citation statements)

References 20 publications

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“…Simulations for lifting force determination and gap distance optimisation were made on the base of a simplified quadrotor helicopter model with 254 mm propellers. Separate simulations for four different rotation speeds 1500 min -1 , 3000 min -1 , 4000 min -1 and 5000 min -1 were done [35]. For each rotation speed, the distance range between the propellers changed from 5 mm to 140 mm ( Figure 11).…”

Section: Simulationsmentioning

confidence: 99%

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Analysis and study of the influence of the geometrical parameters of mini unmanned quad-rotor helicopters to optimise energy saving

Penkov¹,

Александров²

2017

Int. J. Automot. Mech. Eng.

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The article discusses lift force generated by mini UAVs (Unmanned Aerial Vehicles). CFD (Computational Fluid Dynamics) simulations were made on the base of a 3D scanned propeller model. Influence of some geometrical parameters of propeller (like velocity or pitch) and quadcopter (like gap) on lifting force was considered. Different propeller pitches were used and pitch influence on propeller lift force was analysed. Normally, lifting force will increase with the increasing of propeller pitch but for different rotation velocities, this increasing is different and in all cases, it can be approximated by a linear relationship. To obtain dependency functions, an equation for calculation of lift force given took into account the correction coefficients. This equation gave reliable results at pitch values equal to 0.3 -0.7 of the propeller diameter and at rotation velocities of 2000 min -1 -8000 min -1 .Lift force dependency from distance between rotors was also considered. Simulations and experiments showed that the lifting force of a quadcopter increased about 15% on gap distances from 5 mm to 35 mm. From a distance of 70 mm, the lifting force will decrease about 2% and then will stabilise. At increasing of distance between propellers from 5 mm until 25 mm, the power consumption decreased 8% -10% and after the gap distance equal to 40 mm, it will be stable and minimal. It can be asserted that quadcopters have different optimal distances between the propellers at different rotation speeds to generate the same force. Equations for calculation of optimal gap distances for different multicopters were derived and calculation results are presented in graphs and tables.

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Section: Simulationsmentioning

confidence: 99%

“…The work by [33] tried to save system energy by chattering reduction during mini UAV control. Work by [34,35] considered thrust optimisation in rotors with two and three propellers. The main purposes of this research are to consider the influence of rotor pitch and gap between rotors on lift force and power consumption of a quadcopter.…”

Section: Introductionmentioning

confidence: 99%

Analysis and study of the influence of the geometrical parameters of mini unmanned quad-rotor helicopters to optimise energy saving

Penkov¹,

Александров²

2017

Int. J. Automot. Mech. Eng.

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“…As for the flow field characteristics analysis of the quadrotor aircraft, Hwang et al [12] studied the interaction between the rotors and the fuselage of the quadrotor on the hover and forward flight by numerical simulation, and found that he inflow caused by the interaction of the rotors was higher than that of a single rotor. Aleksandrov et al [13] studied aerodynamic interference in hover with different spacing by comparing the result of experiment and CFD simulation. Nguyen et al [14] found that the lift coefficient of rear rotors was decreased obviously due to the interference from the front rotor with wind tunnel test.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Performance of a Quadrotor MAV Considering the Horizontal Wind

Lei

Wang

2020

IEEE Access

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The aerodynamic performance of the quadrotor is usually suffering a lower propulsive efficiency in a windy environment. Especially the horizontal wind may affect the attitude control to provide sufficient thrust to lift the entire vehicle or cause extra power consumption. In this paper, the aerodynamic characteristics of a micro quadrotor aircraft considering the horizontal wind disturbance are studied by both experiments and simulations. First, the aerodynamic model of the quadrotor with the influence of horizontal wind disturbance is deviated in details. Then, the distribution of flow field of the quadrotorr MAV considering the effects of horizontal wind was simulated by computational fluid dynamics (CFD) method. Finally, the thrust and power consumption of quadrotor with rotational speed ranged from 1500 to 2300 r/min were obtained in a low-speed wind tunnel. The comparison of simulation and experimental results shows that the distribution of flow field becomes more complicated with mutual interferences resulted by the distortion of rotor wake and crash of the downwash flow from the front rotors along with the wind direction. The thrust of the rotors gradually increases with wind speed, resulting from the increment of pressure difference between the upper and lower surfaces. However, the power consumption is also increasing because of the possible vibration caused by the strong interactions when the wind speed is up to 4.0 m/s. Also, the power loading of the quadrotor is larger at 2.5 m/s, which shows a good wind resistance with a better aerodynamic performance.

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“…Kaya et al [15] used momentum and blade element theory to deduce the expressions of forces and moments generated by the rotor, and verified them through wind tunnel tests. Aleksandrov et al [16] analyzed the aerodynamic interference between rotors at different rotor spacing by experiment and CFD simulation, but the influence of aerodynamic interference on power is not considered. Lei et al [17] studied the aerodynamic performance of coaxial rotor with different spacing and wind disturbance by wind tunnel tests.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Optimization of a Micro Quadrotor Aircraft with Different Rotor Spacings in Hover

Lei

Wang

2020

Applied Sciences

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In order to study the aerodynamic performance of the quadrotor with different rotor spacings in hover, experiments were performed together with numerical simulations. For experimental study, an experimental platform was designed to measure the thrust and power consumption of the quadrotor with different rotor spacings (L/R = 2.2, 2.6, 3.0, 3.2, 3.6, and 4.0), and to attempt to find out the optimal rotor configuration which makes the quadrotor have the best aerodynamic performance. In addition, the pressure distribution, vorticity of the blade tip, and velocity vector of quadrotor in the flow field were obtained by Computational Fluid Dynamics (CFD) method to visually analyze the aerodynamic interference between adjacent rotors. By the comparison of experimental results and numerical simulations, the final results show that the aerodynamic performance of the quadrotor varies obviously with the change of rotor spacing, and it has a negative impact on hover efficiency if rotor spacing is too much small or large. The rotors pacing at L/R = 3.6 with larger thrust and smaller power is considered to be the best aerodynamic configuration for the quadrotor with better aerodynamic characteristics. Furthermore, compared with the isolated rotor, moderate aerodynamic interference is proved to help improve the aerodynamic performance of the quadrotor with a larger thrust, especially for a rotor spacing at L/R = 3.6.

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Optimization of Lift Force of Mini Quadrotor Helicopter by Changing of Gap Size between Rotors

Cited by 15 publications

References 20 publications

Analysis and study of the influence of the geometrical parameters of mini unmanned quad-rotor helicopters to optimise energy saving

Analysis and study of the influence of the geometrical parameters of mini unmanned quad-rotor helicopters to optimise energy saving

Aerodynamic Performance of a Quadrotor MAV Considering the Horizontal Wind

Aerodynamic Optimization of a Micro Quadrotor Aircraft with Different Rotor Spacings in Hover

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