N.N.Antropov, G.A.Diakonov, V.Kim, G.A.Popov, A.I.Pokryshkin

Research Institute of Applied Mechanics and Electrodynamics, Moscow, Russia

M.N. Kazeev

Russian Research Centre "Kurchatov Institute", Moscow, Russia

   Assessments for the potentialities of using pulsed plasma thrusters (PPT) for controlling spacecrafts of different types are presented in the paper. Problems of controlling spacecrafts differing substantially in mass and operation orbits and thus in requirements to the propulsion systems are studied.
   It is shown that ablation PPTs may be used as the main thrusters of the attitude control system of a heavy orbital spacecraft of up to 2500 kg in mass. One of the propulsion system options, simultaneously providing spacecraft attitude control, its attitude precision stabilization, and compensation of perturbing torques acting upon the spacecraft, comprises six PPTs each consuming the energy of 150 J per one discharge. Total mass of such propulsion system is less than 75 kg.
   PPT application for precision sun-synchronous orbit keeping for a spacecraft of 250 kg in mass: in this case, a PPT based propulsion system solves the problems of the spacecraft injection into the operation orbit, stabilization of the period of its revolution at an accuracy of about 0.001 s and attitude control. This problem may be solved by eight PPTs each consuming energy from 20 to 100 J. Total mass of propulsion system will be no more than
25- 30 kg.

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