| 摘要 |
plasma engineering for spacecraft jet engines; research and development of vacuum process installations. SUBSTANCE: plasma is produced and accelerated as result of action of electron flow coming from self-contained source on gaseous working medium in axisymmetric annular chamber to build up homogeneous magnetic field throughout entire length of system its intensity Ho, being determined on condition that system is fully demagnetized at outlet; prior to do so, working medium uniform in cross-section is produced and introduced in system at distance from its outlet exceeding magnetron cutoff length at the same time ensuring plasma concentration at system outlet not lower than plasma concentration within system. Proposed process is implemented by plasma accelerator with closed-circuit electron drift that has axisymmetric magnetic system with source of magnetomotive force; pole shoes are arranged throughout entire length of discharge chamber and connected, just as compensating cathode, with negative pole of power supply; anode combined with working medium supply system has porous partition and is deepened at distance RH, from accelerator cut that is greater than magnetron cutoff length by at least Larmor radius. Porous partition surface follows form of magnetic lines of force to ensure laminar ion flow. Gaps between surfaces of pole shoes and respective edges of porous partition are chosen considering ion beam divergence angle on RH length and their electric strength. For producing uniform electron flow to discharge chamber and controlling electron concentration of cathode plasma, compensating cathode is arranged coaxially to accelerator on its cut surface. In addition, for reducing gas flow through compensating cathode, cathode plasma production zone is closed by diffuser provided with outlet hole. Pole shoe surfaces are made in the form of truncated cones. EFFECT: improved efficiency of process, increased service life of accelerator. 3 cl, 2 dwg
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