The ablative pulsed plasma thruster (APPT) with the divided mechanism of plasma ionization and acceleration

Aerospace propulsion engineering


Аuthors

Bogatyy A. V., D'yakonov G. A.*, Nechaev I. L.*

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: riame@sokol.ru

Abstract

Paper is devoted to the perspective direction of development of ablative pulse plasma thrusters (APPT) – engines with two-stage system of acceleration of a working body. The principle of action of APPT’s, various types of thrusters, their merits and demerits, possibilities of increase of there characteristics and problems accompanying are considered.

Keywords:

electrorocket thruster; the ablative pulse plasma thruster; the plasma accelerator; the plasma source; the small space vehicle


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