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Problems appearing in the development of small SPT are analyzed and some results of the small SPT development and characterization are represented in a paper, namely: general relationships reflecting the thruster performance level dependence on the thruster scale, results of the special SPT-80 methodical model tests, illustrating the restrictions caused by the scaling factor impact results of the SPT-30 as well as results of the SPT-25 development and characterization. These results confirm that it is possible to ensure the accelerator thrust efficiency (calculated without cathode mass flow rate) level of 0.25...0.30 at least in a power range (100-200)W under specific impulse (1000-1400)s and thruster life time (500-1000)hours. INTRODUCTIONAs it is well known one of the modern space technology development tendencies is an increase of small spacecraft number in space allowing to reduce a mission cost. Therefore it is necessary to develop adequate propulsion subsystems (PS) and, in particular, the PS based on electric propulsion. Taking into account the great flight heritage of SPT it was natural to investigate the performance level of such thrusters of reduced scale and power. There are some physical particularities of these thrusters limiting the possibility to ensure high level of thrust efficiency while thruster scale is reduced. To check these particularities there was developed, manufactured and tested in a wide range of operation modes SPT-80 methodical model. This study had been fulfilled in the frames of International Space Technology, Inc. R&D efforts.Then there was developed and tested the SPT-30 demo model for the NASA LeRC having external accelerating channel diameter 30 mm and according to

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