Abstract
An adequate physical model for the ablative pulsed plasma thrusters (APPT) processes was developed as a result of complex theoretical and experimental studies conducted by RIAME for the processes of plasma acceleration in the APPT and determination of plasma parameters, electric currents, magnetic fields, volumetric electromagnetic forces inside and outside the discharge channel. Possibility for reaching higher thrust efficiency values for such thrusters due to the transfer from oscillative discharge to a quasi-aperiodic discharge was proved by test. Such transfer favors better matching for the distributions of volumetric electromagnetic forces and accelerated plasma (propellant) in the thruster. Analysis for the ways to increase the APPT operating process efficiency is presented. An important role of the elements of external power supply circuit for increasing thruster efficiency is shown. The studies conducted allowed development for the models of highly efficient APPT of new generation characterized by specific thrust pulse of up to 15– 22 km / s and thrust efficiency of up to 25–35%, which differ by high stability of operating process, design, technologic and operational simplicity, and low cost. Development of flight models of a highly efficient APPT for the Russian small spacecraft of “Vulkan” type was started.
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