3 edition of Rapid evaluation of ion thruster lifetime using optical emission spectroscopy found in the catalog.
Rapid evaluation of ion thruster lifetime using optical emission spectroscopy
Brian A. Rock
by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, DC], [Springfield, Va
Written in English
|Statement||Brian A. Rock, Maris A. Mantenieks, and Michael L. Parsons.|
|Series||NASA technical memorandum -- 87103.|
|Contributions||Mantenieks, Maris A., Parsons, M. L. 1940-, United States. National Aeronautics and Space Administration.|
|The Physical Object|
Experimental and Modeling Studies of Low-Energy Ion Sputtering for Ion Thrusters Michael R. Nakles (ABSTRACT) This thesis investigates low-energy xenon-molybdenum (Xe+-Mo) sputtering yields for ion energies of eV and less. Sputtering yield data at these ener-gies are important for ion thruster design and lifetime prediction. The basic. Dan M. Goebel received a B.S. in physics, an M.S. in electrical engineering, and a Ph.D. in applied plasma physics from the University of California, Los Angeles, in , and respectively. He is a Fellow and Senior Research Scientist at the Jet Propulsion Laboratory, an Adjunct Professor of Electrical Engineering and Aerospace.
A key component of the propulsion system is the ion thruster. The NEXT ion thruster is a low specific mass, cylindrical thruster with a beam extraction diameter of 36 cm. Though originally a 40 cm extraction diameter, analyses following an early wear test showed that service life could be improved by reducing the perforatedCited by: Colorado State University Electric Propulsion & Plasma Engineering (CEPPE) Laboratory. The CEPPE Laboratory researches ion and hall thrusters, plasma propulsion technologies, and spacecraft propulsion systems as well as other applications of plasma technology including hydroxyapatite thin films, erosion and sputtering problems, ion optics, and computational .
Electrostatic ion thrusters use the Coulomb force and accelerate the ions in the direction of the electric field. Electromagnetic ion thrusters use the Lorentz force to move the ions. Power supplies for ion thrusters are usually electric solar panels, but at sufficiently large distances from the Sun, nuclear power is used. In each case, the power supply mass is proportional to the . CuIn 1-x Ga x Se 2 (CIGS) thin films with x = 0, and 1 were prepared by the sputtering of Cu, In and Ga in HiPIMS (High Power Impulse Magnetron Sputtering) or DC magnetron and subsequently selenized in an Ar+Se atmosphere. Optical emission spectroscopy (OES) was used to monitor differences in HiPIMS and DC plasma during Cited by: 1.
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Emission spectroscopy was applied by Wehner about 20 yr ago in an attempt to measure relative sputtering rates of various target materials by inert gas ions at low energies (ref.
The ion thruster plasma. however. represents a much more complicated system than the experimental arrangement of ~ehner. First, the thruster discharge plasma was characterized. Get this from a library. Rapid evaluation of ion thruster lifetime using optical emission spectroscopy.
[Brian A Rock; Maris A Mantenieks; M L Parsons; United States. National Aeronautics and Space Administration.]. A major life-limiting phenomenon of electric thrusters is the sputter erosion of discharge chamber components. Thrusters for space propulsion are required to operate for extended periods of time, usually in excess of 10, hr.
Lengthy and very costly life-tests in high-vacuum facilities have been required in the past to determine the erosion rates of thruster components. Evaluation of a steady state MPD thruster test facility.
REED, L. CARLSON, H. HERMAN, Rapid evaluation of ion thruster lifetime using optical emission spectroscopy. ROCK, M. PARSONS and; Measurement of MPD thruster erosion using surface layer activation. VON JASKOWSKY, A. KELLY and. through the grids in an anisotropic beam once per rf cycle as observed using the Ar(2ps2) optical emission.
The intensity of the optical emission and EEPFs are consistent with increasing fractional power coupling to the grids for increasing self-bias voltage, where the peak ion energy and IEDF are controlled via the combined rf-dc grid voltage.
Non-invasive methods of plasma diagnostics through optical emission spectroscopy (OES) and analysis of discharge current oscillations are also briefly discussed.
In this paper, we highlight how these non-invasive methods are employed to study the lifetime of thrusters through prolonged periods of operation in scaled space environment simulators Cited by: 5.
The principal life-limiting component of ion thrusters is the ion optical used to electrostatically accelerate ionized propellant from the thruster's discharge chamber. Optical emission spectra are recorded in the nm spectral range for the near-field plume of a BHT Hall effect thruster fueled by iodine propellant.
The most prominent emissions are observed in the near-infrared region from low-lying excited electronic states of neutral iodine and xenon, respectively.
In recent years, Harbin Institute of Technology developed a way to obtain a focused magnetic field from a low power coaxial (i.e., traditionally designed) Hall thruster, using two permanent magnet rings, where the maximum strength of the magnetic field is outside of the channel (Br exit /Br max = can be obtained) to increase the lifetime Cited by: Spark-optical emission spectroscopy (Spark-OES) for the analysis of metals offers rapid turnaround times.
Since the technique is almost non-destructive, little of the product is lost during analysis. The technique is also well established in the PGM industry. It. by the use of ion thrusters or a similar electric propulsion device. Ion thrusters are low thrust devices; fractions of a pound.
There-fore, in order for ion thrusters to impart the large energy change to a spacecraft required for electric propulsion missions, the ion thrusters must operate for a long period of time.
Where typical chemical rocketsFile Size: 8MB. Optical Emission Spectroscopy of Low Temperature CVD Diamond. Fig. 2 Photograph of the plasma produced as seen from the viewport.
perature controller. The chamber has a view port for observing the plasma inside the chamber. Figure 2 shows the DC glow discharge produced, cylindrical in shape (approx. cm diameter).
Finally, non-invasive plasma diagnostics through analysis of discharge current oscillations as well as optical emission spectroscopy is presented to give a holistic overview of possible diagnostic methods for real-time measurements pertaining to the evaluation of plasma thruster by: 5.
Use of emission spectroscopy for real-time assessment of relative wall erosion rate of BHT hall thruster for various regimes of operation Vacuum, Vol. 84, No. 9 Non-local collisionless and collisional electron transport in low-temperature plasmaCited by: International Journal of Mass Spectrometry and Ion Physics, 24 () Elsevier Scientific Publishing Company, Amsterdam -- Printed in The Netherlands EMISSION CURRENT REGULATOR FOR ION CYCLOTRON RESONANCE SPECTROMETERS USING AN OPTICAL COUPLER * C.
AMANO and M. INOUE Department of Engineering Physics, The University of Cited by: 1. discharge of a cylindrical Hall thruster Here, nanosecond optical imaging spectroscopy with 2ns resolution19 is undertaken to investigate the dynamics of the plasma plume expanding from the “Pocket Rocket” thruster.
Four peaks of optical-emission intensity are observed within the rf cycle. Optical emission, which isCited by: Plume characteristics of a magnetic layer type Hall thruster were evaluated by laser absorption spectroscopy and single probe measurement.
Translational temperature and total number density distributions of xenon atom were deduced using an absorption line of XeI nm and electron temperature. As a result, the temperature was around ±50Cited by: 5. Jagoš R. Radović, Renzo C. Silva, Ryan W.
Snowdon, Melisa Brown, Steve Larter and Thomas B. Oldenburg, A rapid method to assess a broad inventory of organic species in marine sediments using ultra‐high resolution mass spectrometry, Rapid Communications in Mass Spectrometry, 30, 11, (), (). qualified RITA Radio frequency ion propulsion system has an operating life in excess of 20, hours and a nominal specific impulse of then APCON realized the following types of RFG's: RFGW for RIT−22/ ASTRIUM (thrust is mN) (The thruster has achieved a File Size: KB.
cycles. In addition, the feasibility of using OES as a process monitoring tool will be evaluated. OPTICAL EMISSION SPECTROSCOPY OES exploits the fact that a plasma emits light.
Emission lines in an emission spectrum originate from the decay of electronically excited states of the atoms and molecules which are present in the by:. The tradeoff for this high top speed is low thrust (or low acceleration). Thrust is the force that the thruster applies to the spacecraft.
Modern ion thrusters can deliver up to Newtons ( pounds) of thrust, which is equivalent to the force you File Size: KB.and more detailed design of the thruster can be found in.2 B.
Optical Emission Spectroscopy measurements The spectral intensity of the plasma in its region of generation and con nement has been measured by means of a simple optical emission spectroscopy setup.
The plasma emission is collected by means of an optical.The most widely used ion thruster concept generates ions by the electron bombardment method. A typical (Kaufman-type) ion thruster is shown in Figure ; it includes a gas feed system, a hollow cathode, a discharge chamber (usually used as an anode), permanent magnets, an ion optics system, and a neutralizer.