Experimental and numerical analyses of electrohydrodynamic force according to air pressure

Quan, Ronghui; Wang, Bo; Yao, Yunjia

doi:10.1088/1674-1056/acac11

Cited by 2 publications

(1 citation statement)

References 25 publications

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“…They found that at air pressures lower than 1 atm, the wind speed remained relatively constant, but the energy consumption of negative coronas increased as the pressure decreased. Quan et al [34] used a wire-cylinder electrode to generate ion wind and studied the effects of air pressure and other factors on the thrust. Their research found that under low air pressure, increasing corona current did not lead to proportional growth in thrust.…”

Section: Introductionmentioning

confidence: 99%

Influence of humidity and air pressure on thrust characteristics of ion wind propulsion systems

Zhao,

Chen,

et al. 2024

J. Phys. D: Appl. Phys.

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Ion wind propulsion systems have potential applications in the field of unmanned aerial vehicle (UAV) due to their compactness, quiet operation, and simple design. Previous studies have focused on the influences of power source, electrode arrangement, size, and shape on the output thrust characteristics. However, few studies have been performed on the environmental conditions, which can be beneficial for the practical applications of ion wind aircraft in various climatic conditions. In this work, a measurement platform of the output characteristics of ion wind propulsion system under various environmental conditions has been established. The experimental pressure range is 1 to 0.7 atm, and the relative humidity (RH) is 30% to 92%. The effects of air pressure and humidity, and voltage level on the thrust, thrust-to-power radio (TPR) corona current have been investigated. The results show that the corona current and thrust of the wire-wing electrode array decrease with RH within the range of 30% to 80%. Under higher humidity, the corona current and thrust tend to increase at most voltage levels. Moreover, the thrust and current both decrease with reduced pressure when keeping the voltage-to-pressure ratio (U/P) unchanged. It was also found that the thrust is roughly proportional to the square of the pressure. Finally, the possible explanations of the coupled influences on the output characteristics were discussed.

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Section: Introductionmentioning

confidence: 99%

Influence of humidity and air pressure on thrust characteristics of ion wind propulsion systems

Zhao,

Chen,

et al. 2024

J. Phys. D: Appl. Phys.

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Wire-to-two-drop plasma thruster: Experimental and numerical investigation of electroaerodynamic jet flow for micro aerial vehicle propulsion

Ahangar,

Alebrahim

2024

Physics of Fluids

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Conventional micro aerial vehicles (MAVs) have primarily relied on complex, flapping-wing mechanisms for propulsion, often exhibiting limitations in terms of reliability and efficiency. To overcome these challenges, this study explores the potential of electroaerodynamic (EAD) thrusters as a novel propulsion system. By accelerating air molecules through ion collisions, EAD jet flow generates thrust, offering advantages such as noiseless operation and zero emissions due to its moving-part-free design. This research presents a comprehensive experimental and numerical investigation of a wire-to-two-drop thruster configuration to elucidate its electromechanical performance, plasma flow dynamics, and EAD jet characteristics. Experimental measurements of key parameters, including current, thrust, power, and effectiveness, were correlated with numerical simulations, demonstrating excellent agreement with a maximum error below 5%. These findings align strongly with established theoretical frameworks, revealing an inverse square root relationship between effectiveness and thrust. To optimize thruster performance, optimal operating voltages were identified at approximately 8.2, 9.4, and 11.6 kV for inter-electrode gap distances of 10, 15, and 20 mm, respectively, achieving a balanced trade-off between thrust and effectiveness. Detailed numerical visualizations of the plasma flow field, including velocity distribution, jet morphology, potential distribution, and electric field lines, provided valuable insights into the thruster's operation. Building upon these insights, a proof-of-concept EAD flier was constructed and tested, incorporating a serrated emitter electrode and lightweight materials. This flier achieved a mass of 0.5 g and generated a thrust of 0.77 g at 15 kV, resulting in a thrust-to-weight ratio of 1.54 and successful liftoff. This demonstration highlights the potential of EAD propulsion for practical MAV applications.

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Experimental and numerical analyses of electrohydrodynamic force according to air pressure

Cited by 2 publications

References 25 publications

Influence of humidity and air pressure on thrust characteristics of ion wind propulsion systems

Influence of humidity and air pressure on thrust characteristics of ion wind propulsion systems

Wire-to-two-drop plasma thruster: Experimental and numerical investigation of electroaerodynamic jet flow for micro aerial vehicle propulsion

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