Measurement of Static and Dynamic Performance Characteristics of Electric Propulsion Systems

Brezina, Aron Jon

doi:10.2514/6.2013-500

Cited by 21 publications

(13 citation statements)

References 8 publications

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“…For example, at close measured rotational velocities, the propeller with rectangular blades generated 2.91N (at = 7147 RPM), but the propeller with bio-inspired blades produced 2.35N (at = 7134 RPM), which is about 20% difference. The thrust profiles for both propellers qualitatively agree with the results obtained in [14][15][16][17] for quadrotor-type propellers. Other important characteristic is how thrust varies with respect to the power supply.…”

Section: B Performance Of Propellerssupporting

confidence: 85%

Experimental study of the effects of bio-inspired blades and 3D printing on the performance of a small propeller

Hintz

Khanbolouki

Pérez

et al. 2018

2018 Applied Aerodynamics Conference

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The paper presents results of an experimental study conducted to understand the effect of a bio-inspired blade planform on the small propeller thrust and energy consumption. In the study, the Cicada wing was used as a prototype for the blade planform. This blade planform was combined with symmetric (NACA 0015) and asymmetric (NACA 64(4)-221) airfoils resulting in two propellers with bio-inspired blades. The comparative analysis of these two propellers is complimented with the analysis of two propellers with rectangular blades with the same profiles: NACA 0015 and NACA 64(4)-221. The two airfoils were selected for the study based on a review of airfoils suitable for small rotorcrafts, which are of interest for our research. The blade span and the blade planform area of the four propellers are the same. The propellers were manufactured using the 3D printing technology, which affects the blade shape and surface. A study was conducted to analyze the effect of 3D printing on the performance of the propellers with the NACA 0015 blade profiles. In the paper, the performance of propellers with untreated blades, that is, right after their printing, is compared with that of the same propellers, but with the blades soaked several times in a chemical solvent that smoothed the blade surface/shape.

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Section: B Performance Of Propellerssupporting

confidence: 85%

Experimental study of the effects of bio-inspired blades and 3D printing on the performance of a small propeller

Hintz

Khanbolouki

Pérez

et al. 2018

2018 Applied Aerodynamics Conference

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“…Manufacturers of A2212/6T recommend a 7×5 in propeller on 2 batteries of 2 cells and a 5×5 or 6×4 prop on 3 cells. Matching propeller with motor on an experimental test rig is invaluable for a UAV designer, this is necessary to validate manufacturer's claims (Brezina and Thomas, 2013). We ended up matching the motor A2212/6T with a propeller of dimension 10×4 inch.…”

Section: Discussion Of Resultsmentioning

confidence: 99%

Conceptual Design, Analysis and Construction of a Fixed-Wing Unmanned Arial Vehicle for Oil and Gas Pipeline Surveillance

Kisabo¹,

Osheku²,

Sholiyi³

2017

Journal of Aircraft and Spacecraft Technology

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Oil and Gas Pipelines consists of pipes, compressors and pumps. These are frequently located in environments that are difficult to monitor and secure (e.g., creeks and remote areas). Attacks or damage to such installations can lead to enormous ecological impact and loss of revenue. Developing and implementing monitoring systems that can continuously assess the state and condition of oil and gas pipelines is very essential. Current solutions for monitoring such facilities are very manual and risky. Unmanned Aerial Vehicle (UAV) offers great new alternative solutions. In this study, we present a conceptual design of a UAV with a battery powered propulsion system for such application. Here, we show by example how a mission statement can be translated into a physical aircraft from first principle. Notably, five (5) novel mathematical equations were formulated to aid and optimise the design process. These novel equations basically relate the take-off mass of the aircraft with the wingspan, chord length and fuselage length. With such equations, for a designed take-off mass, there exist several variant of the aircraft concept by varying wingspan, chord length and fuselage length of the UAV. In addition, we used thrust-to-weight ratio in a novel approach to ensure that the power available at the propeller will be sufficient for the mission. For this phase of the design, the basic objective among others is to attain lift-off at a very short take off distance. The method proposed in this study proved to be very effective after several successful flight tests.

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“…Typical efficiencies for the power system components range from 70 to 90% and depend on operating temperature and electrical load. 6 The battery represents another efficiency term, but as the power is measured downstream, it does not impact the overall system efficiency. Figure 25 shows the electrical efficiency for the three representative propellers tested at full power.…”

Section: E System Efficiencymentioning

confidence: 99%

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

McCrink

Gregory

2015

33rd AIAA Applied Aerodynamics Conference

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A model for the propulsion system of a small-scale electric Unmanned Aircraft System (UAS) is presented. This model is based on a Blade Element Momentum (BEM) model of the propeller, with corrections for tip losses, Mach effects, three-dimensional flow components, and Reynolds scaling. Particular focus is placed on the estimation of scale effects not commonly encountered in the full-scale application of the BEM modeling method. Performance predictions are presented for geometries representative of several commercially available propellers. These predictions are then compared to experimental wind tunnel measurements of the propellers' performance. The experimental data supports the predictions of the proposed BEM model and points to the importance of scale effects on prediction of the overall system performance. Nomenclature a 0 = axial inflow correction factor a 1 = radial inflow correction factor A = test section area, m 2 B = number of blades c = chord, m C = faring area, m 2 C D = drag coefficient C L = lift coefficient , L pot C = lift coefficient from potential flow theoryPrandtl tip loss correction factor F = Prandtl tip loss correction factor I = current, A J = advance ratio K = local velocity correction factor L = lift, N M = Mach number n = rotation rate, rev/sec P = power, W AIAA Aviation 2 American Institute of Aeronautics and Astronautics q = dynamic pressure, Pa Q = torque, N-m r = radius, m Re = Reynolds number T = thrust, N V = velocity, m/s V l = local section velocity, m/s V r = radial velocity m/s V ∞ = freestream velocity, m/s V 1 = velocity across propeller disk, m/s V 2 = downstream velocity, m/s Greek  = angle of attack  = efficiency  = geometric angle of attack, rad  = Inflow angle  = density, kg/m 3 σ = propeller solidity  = tunnel correction factor  = rotation rate, rad/s

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Measurement of Static and Dynamic Performance Characteristics of Electric Propulsion Systems

Cited by 21 publications

References 8 publications

Experimental study of the effects of bio-inspired blades and 3D printing on the performance of a small propeller

Experimental study of the effects of bio-inspired blades and 3D printing on the performance of a small propeller

Conceptual Design, Analysis and Construction of a Fixed-Wing Unmanned Arial Vehicle for Oil and Gas Pipeline Surveillance

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

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