Abstract:
Field emission nanostructures (18) assist operation of a microdischarge device. The field emission nanostructures are integrated into the microdischarge device(s) or are situated near an electrode (14, 16, 36, 38) of the microdischarge device(s). The field emission nanostructures reduce operating and ignition voltages compared to otherwise identical device lacking the field emission nanostructures, while also increasing the radiative output of the microdischarge device(s).
Abstract:
A hollow cathode gun used in the ion plating through HCD process comprises a hollow cathode (2) consisting of an outer graphite layer (3) and an inner Ta, W or LaB₆ layer (4). A deposition device using the above hollow cathode gun comprises at least one crucible housing an evaporation material, a substrate and a reaction gas inlet, and is provided with a focusing coil surrounding the outer layer of the hollow cathode and another focusing coil surrounding the crucible.
Abstract:
The use of the electride form of 12CaO-7Al 2 O 3 , or C12A7, as a low work function electron emitter in a hollow cathode discharge apparatus (10) is described. No heater is required to initiate operation of the present cathode (12), as is necessary for traditional hollow cathode devices. Because C12A7 has a fully oxidized lattice structure, exposure to oxygen does not degrade the electride. The electride was surrounded by a graphite liner (18) since it was found that the C12A7 electride converts to it's eutectic (CA+C3A) form when heated (through natural hollow cathode operation) in a metal tube.
Abstract:
A method for fabricating microcavity discharge devices and arrays of devices. The devices are fabricated by layering a dielectric (1020, 220) on a first conducting layer or substrate (210, 1010). A second conducting layer or structure is overlaid on the dielectric layer. In some devices, a microcavity (1040, 212) is created that penetrates the second conducting layer or structure and the dielectric layer. In other devices, the microcavity penetrates to the first conducting layer. The second conducting layer or structure together with the inside face of the microcavity is overlaid with a second dielectric layer. The microcavities are then filled with a discharge gas. When a time- varying potential of the appropriate magnitude is applied between the conductors, a microplasma discharge is generated in the microcavity. These devices can exhibit extended lifetimes since the conductors are encapsulated, shielding the conductors from degradation due to exposure to the plasma. Some of the devices are flexible and the dielectric can be chosen to act as a mirror.
Abstract:
The invention is directed to a discharge device and a cathode for use in such a discharge device. By providing a dielectric layer between a first and a second electrode, e.g. between a cathode and an anode, said dielectric layer having an opening aligned with a micro hollow of the first electrode, the light efficiency of the discharge device can be improved.
Abstract:
A gas discharge lamp has a tubular envelope (1) containing tubular electrodes (30) at opposite ends. An annular support member (40) of a compressible ceramic fibre is supported in a groove (33) around each electrode and is compressed against the inside surface of the envelope. Movement of the electrodes (30) relative to the envelope (1) is damped by the support member (40).
Abstract:
A hollow cathode gun used in the ion plating through HCD process comprises a hollow cathode (2) consisting of an outer graphite layer (3) and an inner Ta, W or LaB₆ layer (4). A deposition device using the above hollow cathode gun comprises at least one crucible housing an evaporation material, a substrate and a reaction gas inlet, and is provided with a focusing coil surrounding the outer layer of the hollow cathode and another focusing coil surrounding the crucible.
Abstract:
The present disclosure generally pertains to devices and methods for generating thrust in vehicles, for instance in space applications. A heaterless, insertless hollow cathode utilizes AC and pulsed DC electric fields to ionize the propellant gas and generate a plasma plume. The cathode uses an argon microplasma generated in a quartz tube with a tungsten filament and brass ion collector. Free electrons are then drawn from the plasma plume and supplied to a thruster engine.