Cycloidal rotor coupled with DBD plasma actuators for performance improvement

Benmoussa, Amine; Páscoa, José

doi:10.1016/j.ast.2020.106468

Cited by 18 publications

(6 citation statements)

References 29 publications

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“…The embedded electrode is electrically isolated from the exposed electrode and the surrounding atmosphere and is connected to ground. The exposed electrode, on the other hand, is excited with a sinusoidal voltage signal with a frequency on the order of kilohertz [93][94][95]. The dielectric layer can be made of any dielectric material with good insulating properties and high dielectric strength [96,97].…”

Section: Dielectric Barrier Discharge Plasma Actuators For Ice Mitiga...mentioning

confidence: 99%

Recent Developments on Dielectric Barrier Discharge (DBD) Plasma Actuators for Icing Mitigation

et al. 2022

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Ice accretion is a common issue on aircraft flying in cold climate conditions. The ice accumulation on aircraft surfaces disturbs the adjacent airflow field, increases the drag, and significantly reduces the aircraft’s aerodynamic performance. It also increases the weight of the aircraft and causes the failure of critical components in some situations, leading to premature aerodynamic stall and loss of control and lift. With this in mind, several authors have begun to study the thermal effects of plasma actuators for icing control and mitigation, considering both aeronautical and wind energy applications. Although this is a recent topic, several studies have already been performed, and it is clear this topic has attracted the attention of several research groups. Considering the importance and potential of using dielectric barrier discharge (DBD) plasma actuators for ice mitigation, we aim to present in this paper the first review on this topic, summarizing all the information reported in the literature about three major subtopics: thermal effects induced by DBD plasma actuators, plasma actuators’ ability in deicing and ice formation prevention, and ice detection capability of DBD plasma actuators. An overview of the characteristics of these devices is performed and conclusions are drawn regarding recent developments in the application of plasma actuators for icing mitigation purposes.

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Section: Dielectric Barrier Discharge Plasma Actuators For Ice Mitiga...mentioning

confidence: 99%

Recent Developments on Dielectric Barrier Discharge (DBD) Plasma Actuators for Icing Mitigation

et al. 2022

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“…Whereas the related topic of plasma actuators (PA) for flow control applications is widely studied [9][10][11][12][13][14][15][16][17][18][19][20], there is recently a growing interest in the study of surface dielectric barrier discharges (SDBDs) as an anti-icing and de-icing system [21][22][23][24][25][26][27][28][29][30]. Probably Meng et al [24] and Cai Jinsheng et al [21] were the first who reported experimental results indicating that SDBDs can work as an anti/de-icing system.…”

Section: Introductionmentioning

confidence: 99%

Icing Mitigation by MEMS-Fabricated Surface Dielectric Barrier Discharge

et al. 2021

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Avoiding ice accumulation on aerodynamic components is of enormous importance to flight safety. Novel approaches utilizing surface dielectric barrier discharges (SDBDs) are expected to be more efficient and effective than conventional solutions for preventing ice accretion on aerodynamic components. In this work, the realization of SDBDs based on thin-film substrates by means of micro-electro-mechanical-systems (MEMS) technology is presented. The anti-icing performance of the MEMS SDBDs is presented and compared to SDBDs manufactured by printed circuit board (PCB) technology. It was observed that the 35 μm thick electrodes of the PCB SDBDs favor surface icing with an initial accumulation of supercooled water droplets at the electrode impact edges. This effect was not observed for 0.3 μm thick MEMS-fabricated electrodes indicating a clear advantage for MEMS-technology SDBDs for anti-icing applications. Titanium was identified as the most suitable material for MEMS electrodes. In addition, an optimization of the MEMS-SDBDs with respect to the dielectric materials as well as SDBD design is discussed.

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“…Several parameters defining this dielectric barrier discharge (DBD) setup are described in detail by Shyy et al [66] and the experimental data of Roth et al [75], including the elementary charge, e c = 1.602 × 10 −19 C; the charge density, ρ c = 1 × 10 17 m −3 ; an applied voltage frequency of 3000 Hz; applied voltage of 4000 V rms ; breakdown electric field strength of 30 × 10 5 V/cm; and discharge time of 67 µs. The electrode thickness, t e = 0.1 mm , dielectric thickness t d = 0.75 mm and plasma length l p = 3 mm ; using these parameters, the power consumption of the plasma actuator is given by P p = 1.112 W , as described in Benmoussa and Páscoa [37].…”

Section: Plasma Modelmentioning

confidence: 99%

“…In order to optimize the performance of cycloidal rotors at different flight operations, in our previous work, we proposed the implementation of dielectric barrier discharge (DBD) plasma actuators for boundary layer flow control on the blades [36,37]. Plasma actuators are very promising devices that only started to be studied for flow control purposes at the end of the last century with the works of Liu and Roth [38] and Roth et al [39].…”

Section: Introductionmentioning

confidence: 99%

Plasma Actuators for Cycloidal Rotor Thrust Vectoring Enhancement in Airships

Benmoussa,

Rodrigues,

Páscoa

2023

Actuators

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Airships are a method of transportation with reduced fuel consumption and great potential for different applications. However, these aerial vehicles still present considerable control and maneuverability problems. To overcome these issues, in the current work, we propose the use of plasma-enhanced cycloidal rotor thrusters to increase the controllability and maneuverability of airships. Numerical simulations are carried out to demonstrate the potential of plasma actuators to enhance the efficiency and thrust vectoring capabilities of cycloidal rotors. The fluid dynamics of the flow effects created via the operation of the cycloidal rotor is analyzed with and without plasma actuation. In addition, smart combined plasma actuation is proposed to further optimize the plasma-coupled cycloidal rotor device. The results demonstrated that by using this novel approach, the lift coefficient was increased by about 27%. To summarize, the obtained results for a rotational speed of 100 rpm are compared with results for 200 rpm, and it is demonstrated that for lower rotational speeds, the plasma effect is increased and more significant. This allows us to conclude that airships are an ideal application for plasma-enhanced cycloidal rotors, because since the lift is mostly generated via aerostatic principles, the plasma-enhanced thruster can be operated at lower rotational speeds and effectively increase the controllability and maneuverability of the aerial vehicle.

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Cycloidal rotor coupled with DBD plasma actuators for performance improvement

Cited by 18 publications

References 29 publications

Recent Developments on Dielectric Barrier Discharge (DBD) Plasma Actuators for Icing Mitigation

Recent Developments on Dielectric Barrier Discharge (DBD) Plasma Actuators for Icing Mitigation

Icing Mitigation by MEMS-Fabricated Surface Dielectric Barrier Discharge

Plasma Actuators for Cycloidal Rotor Thrust Vectoring Enhancement in Airships

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