Bulletin of the American Physical Society
69th Annual Gaseous Electronics Conference
Volume 61, Number 9
Monday–Friday, October 10–14, 2016; Bochum, Germany
Session GT1: Plasma Propulsion and Aerospace Applications IFocus
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Chair: Trevor Lafleur, Ecole Polytechnique Room: 1 |
Tuesday, October 11, 2016 4:00PM - 4:30PM |
GT1.00001: From laboratory plasma experiments to space plasma experiments with `CubeSat' nano-satellites Invited Speaker: Christine Charles `CubeSat' nano-satellites provide low-cost access to space. SP3 laboratory's involvement in the European Union `QB50' `CubeSat' project [www.qb50.eu] which will launch into space 50 `CubeSats' from 27 Countries to study the ionosphere and the lower thermosphere will be presented. The Chi~Kung laboratory plasma experiment and the Helicon Double Layer Thruster prototype can be tailored to investigate expanding magnetized plasma physics relevant to space physics (solar corona, Earth's aurora, adiabatic expansion and polytropic studies). Chi~Kung is also used as a plasma wind tunnel for ground-based calibration of the University College London QB50 Ion Neutral Mass Spectrometer. Space qualification of the three Australian QB50 `CubeSats' (June 2016) is carried out in the WOMBAT XL space simulation chamber. The QB50 satellites have attitude control but altitude control is not a requirement. SP3 is developing end-to-end miniaturised radiofrequency plasma propulsion systems (such as the Pocket Rocket and the MiniHel thrusters with power and propellant sub-systems) for future `CubeSat' missions. [Preview Abstract] |
Tuesday, October 11, 2016 4:30PM - 4:45PM |
GT1.00002: Modeling plasma glow discharges in Air near a Mach 3 bow shock with KRONOS Sebastien Rassou, Julien Labaune, Denis Packan, Paul-Quentin Elias In this work, plasma glow discharge in Air is modeled near a Mach 3 bow shock. Numerical simulations are performed using the coupling KRONOS which have been developed at ONERA. The flow field is modeled using the code CFD: CEDRE from ONERA and the electrical and plasma part by the EDF open-source code CODE\textunderscore SATURNE. The plasma kinetic modeling consists on a two-term Boltzmann equation solver and a chemical reaction solver depending of the electric field. The coupling KRONOS is fully parallelized and run on ONERA supercomputers. The shock wave is formed by the propagation of a supersonic flow (M $=$ 3) through a truncated conical model mounted with a central spike. Depending on the spike's voltage value, corona, glow or arc regime could be obtained in a steady flow. The parameters for the supersonic flow and the spike configurations are chosen to be in glow discharge regime and to reproduce the experimental setup. In our simulations, 12 species and 80 reactions (ionization, electronic or vibrational excitation, attachment etc \textellipsis ) are considered to properly model the glow discharge and the afterglow. In a stationary flow, glow discharge is observed only at the upstream of the shock wave near the high voltage spike. Behind the bow shock, in the afterglow, negative ions are provided by electrons attachment with O2. The negative ions flow convection ensures the electrical conduction and the establishment of the glow discharge. [Preview Abstract] |
Tuesday, October 11, 2016 4:45PM - 5:00PM |
GT1.00003: MHD thrust vectoring of a rocket engine. Julien Labaune, Denis Packan, Fabien Tholin, Laurent Chemartin, Thierry Stillace, Frederic Masson In this work, the possibility to use MagnetoHydroDynamics (MHD) to vectorize the thrust of a solid propellant rocket engine exhaust is investigated. Using a magnetic field for vectoring offers a mass gain and a reusability advantage compared to standard gimbaled, elastomer-joint systems. Analytical and numerical models were used to evaluate the flow deviation with a 1 Tesla magnetic field inside the nozzle. The fluid flow in the resistive MHD approximation is calculated using the KRONOS code from ONERA, coupling the hypersonic CFD platform CEDRE and the electrical code SATURNE from EDF. A critical parameter of these simulations is the electrical conductivity, which was evaluated using a set of equilibrium calculations with 25 species. Two models were used: local thermodynamic equilibrium and frozen flow. In both cases, chlorine captures a large fraction of free electrons, limiting the electrical conductivity to a value inadequate for thrust vectoring applications. However, when using chlorine-free propergols with 1{\%} in mass of alkali, an MHD thrust vectoring of several degrees was obtained. [Preview Abstract] |
Tuesday, October 11, 2016 5:00PM - 5:15PM |
GT1.00004: 2D Particle-In-Cell simulations of the electron-cyclotron instability and associated anomalous transport in Hall-Effect Thrusters. Vivien Croes, Trevor Lafleur, Zdenek Bonaventura, François Péchereau, Anne Bourdon, Pascal Chabert This work studies the electron-cyclotron instability in Hall-Effect Thrusters (HETs) using a 2D Particle-In-Cell (PIC) simulation. The simulation is configured with a Cartesian coordinate system where a magnetic field, B$_{\mathrm{\mathbf{0}}}$, is aligned along the X-axis (radial direction, including absorbing walls), a constant electric field, E$_{\mathrm{\mathbf{0}}}$, along the Z-axis (axial direction, perpendicular to simulation plane), and the E$_{\mathrm{\mathbf{0}}}$xB$_{\mathrm{\mathbf{0}}}$ direction along the Y-axis (O direction, with periodic boundaries). Although for low plasma densities classical electron-neutral collisions theory describes well electron transport, at sufficiently high densities (as measured in HETs) a strong instability can be observed that enhances the electron mobility, even in the absence of collisions. The instability generates high frequency (\textasciitilde MHz) and short wavelength (\textasciitilde mm) fluctuations in both the electric field and charged particle densities. We investigate the correlation between these fluctuations and their role with anomalous electron transport; complementing previous 1D simulations. Plasma is self-consistently heated by the instability, but since the latter does not reach saturation in an infinitely long 2D system, saturation is achieved through implementation of a finite axial length that models convection in E$_{\mathrm{\mathbf{0}}}$ direction. [Preview Abstract] |
Tuesday, October 11, 2016 5:15PM - 5:30PM |
GT1.00005: Effects of Electrode Oxidation on the RailPAc Plasma Actuator Gliding Arc Miles Gray, Young-Joon Choi, Jayant Sirohi, Laxminarayan L Raja The rail plasma actuator (RailPAc) has been proposed as a high momentum atmospheric-pressure aerodynamic flow control technique using the principle of MHD forcing. We have previously studied the physics of the RailPAc device and characterized arc structure and dynamics during operation. We have recently shown that the arc dynamic behavior is strongly influenced by the state of the electrode surface and the arc root mode of attachment to that surface. These plasma surface interaction effects have significant implications for the design of practical gliding arc actuators. In this talk we report on the structure of anode and cathode root attachment as a function of the electrode surface state and their impact on overall motion of arc column and the aerodynamic forcing performance. We find that in particular, anode root attachment is the limiting process that limits the overall motion of the arc column, and hence the device performance. We also find that the oxidation state of the anode surface has strongest influence on the anode root motion and hence can be used to alleviate arc root attachment related limitations on the RailPAc performance. [Preview Abstract] |
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