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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 343 records · Page 19
All sourcesNASA NTRSDOE OSTI
DOE OSTI2015

Plasma characteristics of argon glow discharge produced by AC power supply operating at low frequencies

Non-thermal properties of Argon glow discharge operating with various operating pressures were measured and presented in this work. The Argon plasma is produced by a parallel conducting electrodes coupling with a high voltage AC power supply. The power supply can generate high AC voltage at various frequencies. The frequencies for the operation are in the range of a few kHz. The system is capable of generating electric field between the two metal electrodes discharge system. The characteristics of plasma produced were measured by optical emission spectroscopy (OES) technique where electron temperature (T{sub e}) and electron number density (n{sub e}) can be determined by line intensity ratio method. The value of electron number density was then determined from the Saha-Eggert equation. Our results show that the electron number density of the discharge obtained is of the order of 10{sup −17} − 10{sup −18} m{sup −3} where the electron temperature is between 1.00−2.00 eV for various operating frequencies used which are in good agreement with similar results published earlier.

71 CLASSICAL AND QUANTUM MECHANICS, GENERAL PHYSIC↗
DOE OSTI2019

DC-AC electrical transformer

An apparatus and corresponding systems and methods for managing electric power, particularly a transformer system and method, and more specifically a transformer for transforming direct current to alternating current. An example apparatus includes a chamber configured to contain plasma. The apparatus includes input electrodes disposed at least partially within the chamber, and configured to receive direct current input into the chamber. The input electrodes are configured to cause the input direct current to induce motion in the plasma. Motion induced in the plasma transforms current flowing there-through. Output electrodes extend from the chamber, which output electrodes may rotated in a controlled manner. The output electrodes conduct a three or one phase alternating current, from the induced motion in the plasma, for delivery from the chamber.

42 ENGINEERING↗
DOE OSTI2013

Scenarios of transition to chaos competition in low-temperature plasma

Dynamics of a fireball created in front of a positively biased electrode immersed into low-temperature plasma was experimentally investigated. By analyzing the time series of the oscillations of the current collected by the electrode, several successive scenarios of transitions to chaos were identified: by intermittencies, by cascade of sub-harmonic bifurcations and by quasi-periodicity (Ruelle-Takens scenario)

70 PLASMA PHYSICS AND FUSION TECHNOLOGY↗
NASA NTRS1975

Current from a dilute plasma measured through holes in insulators

The current collected from a plasma through holes in insulated electrodes was measured. Holes of 0.051- and 2.54-cm diameters in Kapton H film and plasma number densities of 100 and 10,000 electrons/cu cm were used. The current collected by bare electrodes, that is, electrodes with no surrounding insulation, is also presented. For all the samples the current at a given voltage was a function of the surrounding insulator area rather than of the hole size or the underlying electrode size. In addition, at the low plasma density the I-V characteristic showed very steep rises for voltages below 1 kV. In one case the current jumped by a factor of approximately 70 to 200 V. Results are given for positive biases to 10 kV. For negative biases, sparking prevented testing most samples to the 10-kV limit.

Grier, N. T.↗
NASA NTRSDate not supplied

The Characterization of a DC Glow Discharge in a Tripped Hypersonic Boundary Layer

A direct current glow discharge plasma was generated on a canonical 2.75° half-angle wedge test article. Experiments were conducted in the Texas A&M University Actively Controlled Expansion tunnel at 𝑀 = 5.7 and 𝑅𝑒 = 6 × 10 6 /m. The effect of Reynolds number, polarity, and upstream perturbation were all independently studied via imaging, power measurements, and optical emission spectroscopy (OES). These measurements are the first to be conducted in a tripped hypersonic boundary layer and allow a deeper understanding of the electrohydrodynamics. The plasma, formally characterized as a normal glow discharge, had negligible Joule and cathode heating effects on the boundary layer. Analogously, the installation of trips upstream of the electrodes changed only the appearance of the plasma, creating periodic streaks corresponding to the wakes and vortices produced by each trip but not altering the power across the electrodes. The plasma power peaked at 47 W, which OES revealed was sufficient to generate NO in the positive column and negative glow.

Casey J. Broslawski↗
NASA NTRSDate not supplied

The Characterization of a DC Glow Discharge in a Tripped Hypersonic Boundary Layer

A direct current glow discharge plasma was generated on a canonical 2.75° half-angle wedge test article. Experiments were conducted in the Texas A&M University Actively Controlled Expansion tunnel at 𝑀 = 5.7 and 𝑅𝑒 = 6 × 10 6 /m. The effect of Reynolds number, polarity, and upstream perturbation were all independently studied via imaging, power measurements, and optical emission spectroscopy (OES). These measurements are the first to be conducted in a tripped hypersonic boundary layer and allow a deeper understanding of the electrohydrodynamics. The plasma, formally characterized as a normal glow discharge, had negligible Joule and cathode heating effects on the boundary layer. Analogously, the installation of trips upstream of the electrodes changed only the appearance of the plasma, creating periodic streaks corresponding to the wakes and vortices produced by each trip but not altering the power across the electrodes. The plasma power peaked at 47 W, which OES revealed was sufficient to generate NO in the positive column and negative glow.

Casey Broslawski↗
NASA NTRS2011

Thrust Stand Measurements of the Microwave Assisted Discharge Inductive Plasma Accelerator

Pulsed inductive plasma thrusters [1-3] are spacecraft propulsion devices in which electrical energy is capacitively stored and then discharged through an inductive coil. This type of pulsed thruster is electrodeless, with a time-varying current in the coil interacting with a plasma covering the face of the coil to induce a plasma current. Propellant is accelerated and expelled at a high exhaust velocity (O(10-100 km/s)) by the Lorentz body force arising from the interaction of the magnetic field and the induced plasma current. While this class of thruster mitigates the life-limiting issues associated with electrode erosion, pulsed inductive plasma thrusters require high pulse energies to inductively ionize propellant. The Microwave Assisted Dis- charge Inductive Plasma Accelerator (MAD-IPA), shown in Fig. 1, is a pulsed inductive plasma thruster that addressees this issue by partially ionizing propellant inside a conical inductive coil before the main current pulse via an electron cyclotron resonance (ECR) discharge. The ECR plasma is produced using microwaves and a static magnetic field from a set of permanent magnets arranged to create a thin resonance region along the inner surface of the coil, restricting plasma formation, and in turn current sheet formation, to a region where the magnetic coupling between the plasma and the theta-pinch coil is high. The use of a conical theta-pinch coil also serves to provide neutral propellant containment and plasma plume focusing that is improved relative to the more common planar geometry of the Pulsed Inductive Thruster (PIT) [1, 2]. In this paper, we describe thrust stand measurements performed to characterize the performance (specific impulse, thrust efficiency) of the MAD-IPA thruster. Impulse data are obtained at various pulse energies, mass flow rates and inductive coil geometries. Dependencies on these experimental parameters are discussed in the context of the current sheet formation and electromagnetic plasma acceleration processes.

Hallock, Ashley K.↗
NASA NTRS2012

Effect of Inductive Coil Geometry on the Thrust Efficiency of a Microwave Assisted Discharge Inductive Plasma Accelerator

Pulsed inductive plasma thrusters [1-3] are spacecraft propulsion devices in which electrical energy is capacitively stored and then discharged through an inductive coil. The thruster is electrodeless, with a time-varying current in the coil interacting with a plasma covering the face of the coil to induce a plasma current. Propellant is accelerated and expelled at a high exhaust velocity (O(10-100 km/s)) by the Lorentz body force arising from the interaction of the magnetic field and the induced plasma current. While this class of thruster mitigates the life-limiting issues associated with electrode erosion, pulsed inductive plasma thrusters require high pulse energies to inductively ionize propellant. The Microwave Assisted Discharge Inductive Plasma Accelerator (MAD-IPA) [4, 5] is a pulsed inductive plasma thruster that addressees this issue by partially ionizing propellant inside a conical inductive coil via an electron cyclotron resonance (ECR) discharge. The ECR plasma is produced using microwaves and permanent magnets that are arranged to create a thin resonance region along the inner surface of the coil, restricting plasma formation, and in turn current sheet formation, to a region where the magnetic coupling between the plasma and the inductive coil is high. The use of a conical theta-pinch coil is under investigation. The conical geometry serves to provide neutral propellant containment and plasma plume focusing that is improved relative to the more common planar geometry of the Pulsed Inductive Thruster (PIT) [2, 3], however a conical coil imparts a direct radial acceleration of the current sheet that serves to rapidly decouple the propellant from the coil, limiting the direct axial electromagnetic acceleration in favor of an indirect acceleration mechanism that requires significant heating of the propellant within the volume bounded by the current sheet. In this paper, we describe thrust stand measurements performed to characterize the performance (specific impulse, thrust efficiency) of the MAD-IPA thruster. Impulse data are obtained at various pulse energies, mass flow rates and inductive coil. geometries. Dependencies on these experimental parameters are discussed in the context of the current sheet formation and electromagnetic plasma acceleration processes.

Hallock, Ashley↗
NASA NTRS2012

Thrust Stand Measurements of a Conical Pulsed Inductive Plasma Thruster

Pulsed inductive plasma thrusters [1-3] are spacecraft propulsion devices in which electrical energy is capacitively stored and then discharged through an inductive coil. The thruster is electrodeless, with a time-varying current in the coil interacting with a plasma covering the face of the coil to induce a plasma current. Propellant is accelerated and expelled at a high exhaust velocity (O(10-100 km/s)) by the Lorentz body force arising from the interaction of the magnetic field and the induced plasma current. While this class of thruster mitigates the life-limiting issues associated with electrode erosion, pulsed inductive plasma thrusters can su er from both high pulse energy requirements imposed by the voltage demands of inductive propellant ionization, and low propellant utilization efficiencies. The Microwave Assisted Discharge Inductive Plasma Accelerator (MAD-IPA)[4], shown in Fig. 1 is a pulsed inductive plasma thruster that is able to operate at lower pulse energies by partially ionizing propellant with an electron cyclotron resonance (ECR) discharge inside a conical inductive coil whose geometry serves to potentially increase propellant and plasma plume containment relative to at coil geometries. The ECR plasma is created with the use of permanent mag- nets arranged to produce a thin resonance region along the inner surface of the coil, restricting plasma formation and, in turn, current sheet formation to areas of high magnetic coupling to the driving coil.

Hallock, Ashley K.↗
NASA NTRS2012

Thrust Stand Measurements of a Conical Inductive Pulsed Plasma Thruster

Inductive Pulsed Plasma Thrusters (iPPT) are spacecraft propulsion devices in which electrical energy is capacitively stored and then discharged through an inductive coil. The thruster is electrodeless, with a time-varying current in the coil interacting with a plasma covering the face of the coil to induce a plasma current. Propellant is accelerated and expelled at a high exhaust velocity (O(10 .. 100 km/s)) by the Lorentz body force arising from the interaction of the magnetic field and the induced plasma current. While this class of thruster mitigates the life-limiting issues associated with electrode erosion, inductive pulsed plasma thrusters can suffer from both high pulse energy requirements imposed by the voltage demands of inductive propellant ionization, and low propellant utilization efficiencies. A conical coil geometry may o er higher propellant utilization efficiency over that of a at inductive coil, however an increase in propellant utilization may be met with a decrease in axial electromagnetic acceleration, and in turn, a decrease in the total axially-directed kinetic energy imparted to the propellant.

Hallock, Ashley K.↗
DOE OSTI2013

Photon counting technique applied to time-resolved laser-induced fluorescence measurements on a stabilized discharge

A novel approach to perform time-resolved laser-induced fluorescence (LIF) measurements in plasma discharges is presented. The LIF technique relies on a photon counting method associated with a sinusoidal potential modulation on a floating electrode located in the plasma to ensure time coherence. By tuning the modulation frequency, resonance can be reached with the discharge current in order to guarantee repeatable measurement conditions. Time-averaged characteristics of the discharge (such as T{sub e}, n{sub e}, V{sub p}, and V{sub ion}) remain unaffected by the modulation. As an example, the association of the photon counting method with the modulation system is employed to determine the time evolution of several ion velocity groups inside an E × B discharge. Interesting features of the velocity oscillations are examined and pave the way for more focused studies.

46 INSTRUMENTATION RELATED TO NUCLEAR SCIENCE AND ↗
NASA NTRS1974

Hot ion plasma heating experiments in SUMMA

A new superconducting magnetic mirror apparatus (SUMMA) is described using photographs, diagrams, characteristics graphs, and block diagrams. The apparatus consists of a magnet facility, a plasma test section, the electrode assembly, a charge-exchange neutral particle analyzer, and apparatus for emission spectroscopy. Initial results of hot ion plasma heating experiments conducted in this facility are reported. The purpose of these experiments was twofold: (1) to make a reliable electrode assembly for steady-state operation in the new SUMMA magnetic field configuration and test-section geometry; and (2) to see how ion heating scales as the midplane magnetic field is varied up to 3.5 tesla.

Reinmann, J. J.↗
NASA NTRS1992

Preliminary investigation of power flow and electrode phenomena in a multi-megawatt coaxial plasma thruster

The present report on preliminary results of theoretical and experimental investigations of power flow in a large, unoptimized, multimegawatt coaxial thruster evaluates the significance of these data for the development of efficient, megawatt-class magnetoplasmadynamic (MPD) thrusters. The good agreement obtained between thruster operational performance and model predictions suggests that ideal MHD processes, including those of a magnetic nozzle, play an important role in coaxial plasma thruster dynamics at power levels relevant to advanced space propulsion. An optimized magnetic nozzle design would aid the development of efficient, multimegawatt MPD thrusters.

Schoenberg, Kurt F.↗
NASA NTRS1993

Preliminary investigation of power flow and electrode phenomena in a multi-megawatt coaxial plasma thruster

This paper summarizes preliminary experimental and theoretical research that was directed towards the study of quasisteady-state power flow in a large, un-optimized, multi-megawatt coaxial plasma thruster. The report addresses large coaxial thruster operation and includes evaluation and interpretation of the experimental results with a view to the development of efficient, steady-state megawatt-class magnetoplasmadynamic (MPD) thrusters.

Schoenberg, Kurt↗
NASA NTRS2016

Pulsed Plasma Lubrication Device and Method

Disclosed herein is a lubrication device comprising a solid lubricant disposed between and in contact with a first electrode and a second electrode dimensioned and arranged such that application of an electric potential between the first electrode and the second electrode sufficient to produce an electric arc between the first electrode and the second electrode to produce a plasma in an ambient atmosphere at an ambient pressure which vaporizes at least a portion of the solid lubricant to produce a vapor stream comprising the solid lubricant. Methods to lubricate a surface utilizing the lubrication device in-situ are also disclosed.

Hofer, Richard R.↗
NASA NTRS1978

Plasma cleaning device

High vacuum cleaning of contaminated surfaces such as hydrocarbon containment films can be accomplished by a plasma cleaning device which includes a plasma discharge housing to permit generation of a plasma in an environment having a higher pressure than the surface which is to be cleaned. A ground electrode and a radio frequency electrode partially surround a quartz plasma tube, for the introduction of an ionizable gas. These electrodes ionize the gas and help generate the plasma. This plasma flows through a non-constrictive aperture, through the plasma discharge housing and then on to the contaminated surface.

Shannon, R. L.↗