Bulletin of the American Physical Society
75th Annual Gaseous Electronics Conference
Volume 67, Number 9
Monday–Friday, October 3–7, 2022;
Sendai International Center, Sendai, Japan
The session times in this program are intended for Japan Standard Time zone in Tokyo, Japan (GMT+9)
Session EW1: Aerospace Plasmas |
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Chair: Mark Koepke, West Virginia University Room: Sendai International Center Hagi |
Wednesday, October 5, 2022 8:00AM - 8:15AM |
EW1.00001: Regime Transitions of a Pulsed Nanosecond Discharge Driven by Dynamic Flame Instabilities Colin A Pavan, Santosh Shanbhogue, Drew Weibel, Ahmed F Ghoniem, Felipe G del Campo, Carmen Guerra-Garcia Pulsed Nanosecond Discharges are being investigated for suppressing dynamic flame instabilities of lean flames. In this dynamic environment, the gas condition is changing significantly in both composition and temperature at the timescales of the pressure oscillations. This changes the ionization characteristics of the gas, due to different ionization thresholds/cross sections as the reaction progresses, as well as by changes to the reduced electric field as the temperature rises. This contribution will report on the experimental characterization of a discharge used for stabilization of dynamic flame instabilities in a 14kW swirl-stabilized combustor. The discharge properties, in terms of its regime and energy deposition, are a strong function of where the flame is in its instability cycle. Understanding the causes of this transition and the two-way coupling between the plasma and the gas is critical for designing the plasma actuation and control scheme. The presentation will focus on experimental demonstration of the flame's effect on the plasma and discussion of the methods of interaction and the implications for designing the plasma actuation strategy. |
Wednesday, October 5, 2022 8:15AM - 8:30AM |
EW1.00002: Global and PIC Modeling of Air - Breathing Plasma Engines Salman Sarwar, Igor D Kaganovich, Alexander V Khrabrov, Dmytro Sydorenko, Willca Villafana Over the past half century, Earth-orbiting artificial satellites have addressed a wide variety of problems in science and technology, from remote sensing and geodesy to defense and navigation. Satellites in low Earth orbit (LEO), in particular, allow for lowered launch costs and communication latencies at the expense of significant atmospheric drag. With renewed interest in LEO satellite networks for telecommunication and deep space mission support, novel propulsion systems are necessary for efficient orbit keeping over the mission lifespan. Unlike traditional electric and thermodynamic systems, air breathing plasma engines (ABPE) do not require on-board propellant, eliminating associated weight, cost, and complexity while increasing service life. In this work, we study the overall feasibility, plasma chemistry, and physics of an electron beam driven ABPE. |
Wednesday, October 5, 2022 8:30AM - 9:00AM |
EW1.00003: Electroaerodynamic aircraft propulsion Invited Speaker: Steven Barrett Electroaerodynamic (EAD) propulsion entails ionizing air and using electrostatic forces to create an “ionic wind”, which constitutes a propulsive stream. It has long been theorized as a potential method for aircraft propulsion. Such a propulsion mechanism is “solid-state” in the sense that it does not have moving parts. A major potential advantage of solid-state propulsion is the removal of noise associated with propellors or fans. Possible applications for near-silent propulsion could include small aircraft for surveillance, package delivery, environmental monitoring, or military and security applications. In addition, near-silent air handling may have applications in other domains. |
Wednesday, October 5, 2022 9:00AM - 9:15AM |
EW1.00004: Development of Fully Covered Plasma Actuator Mahoro Sakurai, Shintaro Sato, Naofumi Ohnishi Recently, a plasma actuator has been attracting attention due to the growing interest in dynamic fluid control technology. While the plasma actuator has no moving parts and enables highly responsive airflow control, it has not yet been put into practical use due to the low induced flow velocity and durability of the materials. In particular, with regard to the durability of the materials, it is known that exposed electrodes are easy to corrode during discharge. In addition, the thickness of the exposed electrodes may cause unexpected disturbances in the flow field. In this study, we propose a fully covered plasma actuator consisting of only covered electrodes by using a coplanar dielectric barrier discharge. The proposed plasma actuator consists of three electrodes; two electrodes upstream generate charged particles, and another electrode downstream accelerates the charged particles. The induced flow velocity was measured by particle image velocimetry, and it was confirmed that the fully covered plasma actuator can generate an equivalent flow to that driven by a conventional plasma actuator with exposed electrode. The measurements also suggest that the performance can be drastically improved by controlling the surface charge on the actuator. |
Wednesday, October 5, 2022 9:15AM - 9:30AM |
EW1.00005: Analysis of Particle Behavior Using Particle-in-cell Method in Discharge and Acceleration Processes of an Air-breathing Electrostatic Ramjet Engine Hoshiki Sato, Masayuki Takahashi A satellite cost becomes large when 400 km altitude is used for a satellite operation because it is necessary to equip a quality and large device on the satellites to obtain high-resolution images.But, when ultra-low altitude orbits of 100–200 km is selected, we can decrease the device cost of satellites because high-resolution images can be obtained even with the use of inexpensive cameras. Moreover, an air drag gradually decreases the flight altitude of satellites when a propulsion is stopped, which increases an aerodynamic heating and burns up the body of satellites; therefore, becoming space debris can be avoided when the ultra-low altitude satellite is used.Compensating the air drag is required to maintain the flight in ultra-low altitude.Because existing systems have a limit of fuel capacity and life, an air-breathing electrostatic ramjet engine, which generates the thrust by using an atmospheric gas as a propellant, has been proposed for ultra-low altitude missions.In this study, the discharge and acceleration processes of the electrostatic ramjet engine were numerically captured using particle-in-cell (PIC) simulations.The PIC result indicated that the electron was trapped by an external magnetic field, and a strong ion acceleration was obtained around the electrodes. |
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