| 摘要 |
FIELD: plasma engineering; electric rocket engines. SUBSTANCE: proposed method and device are meant for designing electric rocket engines built around closed-electron-drift plasma accelerators and ion accelerators used in space conditions for interorbital transport as well as for correcting orbits and orienting space vehicles; they me be also found useful for other industries such as electronics for ion cleaning, milling, producing miscellaneous coatings, and for plasma metallurgy. Engine has acceleration channel for ionizing working medium and accelerating ions provided with system for feeding working medium to closed end region of channel accommodating gas distributing collector that also functions as anode and special working medium inlet. Cathode is placed beyond channel at its open end. Engine is provided in addition with at least one identical acceleration channel and axes of channels are symmetrical to engine axis and form equal angles with the latter. Two or more such angles may be provided and engine may be referred to as multiple-channel engine. Channels may be made in the form of independent accelerators. In order to obtain desired thrust group of k thrust sources (channels) are switched on simultaneously in the amount of 1 to m, where m>=2, and to obtain desired resultant values of modulus vectors and direction of thrust vector in the course of regulation, number of operating thrust sources in group k, where k<=m, components of groups of simultaneously operating thrust sources, and effective time of each group are changed. EFFECT: enlarged capabilities of effective regulation of engine thrust vector to obtain all-duty engine at high characteristics. 5 cl, 1 dwg |
