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At least 451 records · Page 25

Amorphous Carbon Coatings with Controlled Density and Composition

Inertial confinement fusion (ICF) experiments rely on the compression of a spherical capsule containing tritium and deuterium fuel as a way to achieve thermonuclear fusion. Rapid ablation of the capsule surface produces the reactive force that compresses the capsule. Carbon-based capsule materials currently used include low density glow discharge polymer (GDP) and polycrystalline diamond. An ideal capsule material would have the high density of diamond, with the amorphous nature of GDP, which would reduce asymmetries during compression caused by a random crystalline structure. An intermediate material, diamond-like carbon (DLC), has an amorphous structure, and densities between GDP and diamond, but has been difficult to produce with low stress and low impurity levels. The goal of this Feasibility Study was to investigate the practicality of using a magnetically enhanced, hollow-cathode, plasma source to produce thick (50-200 µm), low-stress, diamond-like carbon films for ICF ablator applications. The coatings produced during the course of this work have been shown to be amorphous, to have a higher density than traditional GDP ablators (1.6-1.7 g/cc), to have low stress (67-113 MPa), and can be deposited at the high thicknesses required for ICF capsule requirements. Atomic-force microscopy on a 45-micron-thick coating also measured the films to have grain sizes on the order of 20 nanometers, and a root-mean squared surface roughness of 0.5 nanometers.

36 MATERIALS SCIENCE↗

Fabricating Diamond-like Amorphous Carbon

Using a magnetically confined hot hollow cathode PE-CVD, hydrocarbon gas is decomposed under a diluent gas to deposit hydrogenated amorphous carbon onto a sample holder. During the fabrication of the hydrogenated amorphous carbon, the electric potential, electron temperature, and electron density of the plasma are measured with a Langmuir probe. Raman spectroscopy is used to determine the structural and electronic characterization of the final hydrogenated amorphous carbon solid.

75 CONDENSED MATTER PHYSICS, SUPERCONDUCTIVITY AND↗

Research and advanced concepts

Hollow cathode operation and plasma discharge in mercury ion engine, potential distribution of glow discharge, and liquid metal MHD power conversion

Source record↗

Improved electron emitter

Emitter applies to devices in which a plasma is generated by electron bombardment. Device is conventional hollow cathode modified by addition of integral keeper cap containing small aperture which encloses outlet of the cathode and is held in position by ceramic tube.

Nakanishi, S.↗

Characteristics of the optical radiation from Kaufman thrusters

The optical radiation from plasma discharges of electron-bombardment mercury-ion thrusters was investigated. Spectrographic measurements indicated that the discharge was composed primarily of mercury atoms and singly charged ions. Excitation spectra of doubly charged mercury ions was measured to obtain the fraction of such ions in the discharge. Accomplishments of spectroscopic measurements of a hollow cathode thruster included the identification of two diagnostic lines in the mercury spectrum and the interpretation of the spectral amplitudes in terms of a superposition of primary and Maxwellian electron distributions. Potential application of optical techniques to thruster control applications was also suggested by the measurements.

Milder, N. L.↗

Performance of a neutralizer for electron bombardment thruster

Results of the SERT II flight indicate that the hollow cathode neutralizer not only represents a power and propellant weight penalty but can be a contributing cause to accelerator grid erosion. Tests with a 30-cm diameter thruster show that a neutralizer position of approximately 9 cm axially downstream of the accelerator grid and approximately 9 cm radially away from the outer edge of the accelerator grid and pointing parallel to the thruster axis provides the best overall performance. The estimated grid wear rate was less than 0.08 mm in 10,000 hours. The coupling voltage was approximately 17 volts at a neutralizer flow rate of 22 equivalent milliamperes of mercury and a beam current of 1.5 amperes. Neutralizer power was 31 watts and the effect of neutralizer flow on overall propellant utilization efficiency is a 1.2 percentage point reduction at a thruster utilization efficiency of 90 percent. The neutralizer position defined in tests with a 30 cm thruster was tested with a 15 cm SERT II thruster. When the neutralizer was relocated further downstream with this different orientation, accelerator impingement current due to neutralizer operation was reduced by approximately a factor of seven and was nearly independent of neutralizer operation.

Bechtel, R. T.↗

Power processing requirements for solar electric propulsion.

The successful integration of a light-weight, high-efficiency power conditioning (PC) unit with an electron bombardment ion thruster using a hollow cathode at JPL has been reported recently. This paper summarizes the presently conceived requirements by which the next generation of PCs should be judged and evaluated. The requirements are formulated in terms of a deep space mission, which implies that the characteristics of the solar source will vary in terms of output power and output voltage. The requirements identified by practical experience during long-term evaluation between 1968-1970 are described and explained.

Macie, T. W.↗

Performance of a neutralizer for electron bombardment thruster.

Results of the SERT II flight indicate that the hollow cathode neutralizer not only represents a power and propellant weight penalty but can be a contributing cause to accelerator grid erosion. Tests with a 30-cm diameter thruster have shown that a neutralizer position of approximately 9 cm axially downstream of the accelerator grid and approximately 9 cm radially away from the outer edge of the accelerator grid and pointing parallel to the thruster axis provides the best overall performance. The estimated grid wear rate was less than 0.08 mm in 10,000 hr. The coupling voltage (neutralizer to beam voltage) was approximately 17 volts at a neutralizer flow rate of 22 equivalent milliamperes of mercury and a beam current of 1.5 amperes. Neutralizer power (excluding heaters) was 31 watts and the effect of neutralizer flow on overall propellant utilization efficiency is a 1.2 percentage point reduction at a thruster utilization efficiency of 90 percent.

Bechtel, R. T.↗

A 30-cm diameter bombardment thruster with a variable magnetic baffle.

Thruster performance and stability over a range of beam currents is a function of the hollow cathode propellant flow which depends in part on the baffle geometry. Variable magnetic baffles have been used to allow a change in baffle geometry to improve thruster performance and stability. Test results of a 30-cm thruster with magnetic baffle are presented. Thruster performance characteristics are analyzed to show how the magnetic baffle field strength can improve performance at a fixed beam current, as well as increase the range of ion beam current for throttling.

Bechtel, R. T.↗

Ion thruster thermal characteristics and performance.

Experimental and analytical studies of mercury-fed hollow cathode ion thrusters are presented. Pertinent thermal properties and plasma heating characteristics of the system have been determined through correlation and integration of temperature measurement data with a single stage Wiener-Kalman estimation technique. The resultant analytical network model is applied to predict the thermal performance of specified thruster systems under various operating conditions. The effects of solar intensity levels on the thruster thermal behavior, the dependency on the thruster dimension and multithruster design arrangements have been examined.

Wen, L.↗

The variable magnetic baffle as a control device for Kaufman thrusters.

The variable magnetic baffle described in this paper aids in control of electron flow from the hollow cathode plasma into the main discharge region by augmenting the fringe magnetic field which impedes this electron flow in conventionally baffled Kaufman thrusters. A passive, low loss, and automatic control device is obtained by using the discharge current to excite the control winding. Used in conjunction with typical thruster control loops, stable operation has been obtained over a 10:1 throttling range with a 30 cm thruster. Discharge ignition and overcurrent recycling is also facilitated through use of this device in a permanent magnet thruster.

Poeschel, R. L.↗