Blade Element Momentum Modeling of Low-<i>Re </i>Small UAS Electric Propulsion Systems

McCrink, Matthew; Gregory, James W.

doi:10.2514/6.2015-3296

Cited by 43 publications

(25 citation statements)

References 14 publications

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“…As the speed of the propeller is higher than Ma 0.3 at high rotational speeds, thrust coefficient C T and power coefficient C P are corrected by Prandtl-Glauert factor = √ 1 − Ma 2 [13,14]. Propeller thrust is then calculated with the angular velocity = N 2 60 and the air density :…”

Section: Propellermentioning

confidence: 99%

Energy-optimal guidance of a battery-electrically driven airplane

Settele

Bittner

2019

CEAS Aeronaut J

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This study introduces an approach to decrease the electric energy consumption by efficient guidance of a battery-electrically propulsed airplane. An appropriate mathematical model containing a detailed energy consumption estimation is presented. With this, an optimal control problem is formulated and solved using the Matlab Toolbox FALCON.m. Furthermore, steady state efficiency criteria are established for a range optimal climb and a horizontal flight. With the help of steady state grid calculation, values for both efficiency criteria and corresponding guidance parameters are determined. The optimal values of both criteria are correlated with the steady state arcs of the optimal trajectory. For the descend segment, an optimal airspeed is determined and correlated also with the trajectory. As a result, energy optimal steady state guidance parameters can be provided to the pilot for each flight segment. A concept of a cockpit display is introduced that delivers efficient guidance parameters to the pilot.

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Section: Propellermentioning

confidence: 99%

Energy-optimal guidance of a battery-electrically driven airplane

Settele

Bittner

2019

CEAS Aeronaut J

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“…Marten et al [30] documented that the BEM results linearly interpolated based on the real airfoil geometry in comparison to the direct polar data can differ depending on the characteristic of the neighbouring airfoil sections. McCrink and Gregory [31] provided an example for the BEM calculations based on the polynomial interpolation functions in MATLAB [32]. Despite that, the results were not compared to the other interpolation approaches.…”

Section: Motivation and State Of The Artmentioning

confidence: 99%

Comparison of Blade Element Method and CFD Simulations of a 10 MW Wind Turbine

Bangga

2018

Fluids

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The present studies deliver the computational investigations of a 10 MW turbine with a diameter of 205.8 m developed within the framework of the AVATAR (Advanced Aerodynamic Tools for Large Rotors) project. The simulations were carried out using two methods with different fidelity levels, namely the computational fluid dynamics (CFD) and blade element and momentum (BEM) approaches. For this purpose, a new BEM code namely B-GO was developed employing several correction terms and three different polar and spatial interpolation options. Several flow conditions were considered in the simulations, ranging from the design condition to the off-design condition where massive flow separation takes place, challenging the validity of the BEM approach. An excellent agreement is obtained between the BEM computations and the 3D CFD results for all blade regions, even when massive flow separation occurs on the blade inboard area. The results demonstrate that the selection of the polar data can influence the accuracy of the BEM results significantly, where the 3D polar datasets extracted from the CFD simulations are considered the best. The BEM prediction depends on the interpolation order and the blade segment discretization.

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“…There are many studies on the mathematical modeling [7], [8], [9], the efficiency analysis [10], [11], and the performance estimation [6], [12] of multicopter propulsion systems. To our best knowledge, there are few studies on the design optimization of multicopter propulsion systems.…”

Section: Introductionmentioning

confidence: 99%

An Analytical Design-Optimization Method for Electric Propulsion Systems of Multicopter UAVs With Desired Hovering Endurance

Dai

Quan

Ren

et al. 2019

IEEE/ASME Trans. Mechatron.

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Multicopters are becoming increasingly important in both civil and military fields. Currently, most multicopter propulsion systems are designed by experience and trial-anderror experiments, which are costly and ineffective. This paper proposes a simple and practical method to help designers find the optimal propulsion system according to the given design requirements. First, the modeling methods for four basic components of the propulsion system including propellers, motors, electric speed controls, and batteries are studied respectively. Secondly, the whole optimization design problem is simplified and decoupled into several sub-problems. By solving these subproblems, the optimal parameters of each component can be obtained respectively. Finally, based on the obtained optimal component parameters, the optimal product of each component can be quickly located and determined from the corresponding database. Experiments and statistical analyses demonstrate the effectiveness of the proposed method. The proposed method is fast and practical that it has been successfully applied to a web server to provide online optimization design service for users.

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Blade Element Momentum Modeling of Low-Re Small UAS Electric Propulsion Systems

Cited by 43 publications

References 14 publications

Energy-optimal guidance of a battery-electrically driven airplane

Energy-optimal guidance of a battery-electrically driven airplane

Comparison of Blade Element Method and CFD Simulations of a 10 MW Wind Turbine

An Analytical Design-Optimization Method for Electric Propulsion Systems of Multicopter UAVs With Desired Hovering Endurance

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