Research of design parameters and the analysis of efficiency of application of the unified platforms with electric propulsion thrusters as a part of small spacecrafts

Аuthors

Kul'kov V. M.

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

e-mail: vmk_1@mail.ru

Abstract

In work principles of development of small spacecrafts (SSC) with electric propulsion thrusters (EPT) are considered. Possible variants of application SSC with EPT are defined; recommendations about use EPT in structure SSC of various types are developed. With a view of expansion of possibilities and increase of efficiency of application SSC it is supposed to use power-thruster systems and modules, and also the unified platforms with electric propulsion thrusters and power supply systems on the basis of solar batteries. Methodical maintenance of designing of small spacecrafts with EPT is developed, mathematical models for design researches and the analysis of characteristics SSC with EPT on the basis of stationary plasma thrusters (SPT) and pulse plasma thrusters (PPT) and solar power unit are offered.

Keywords:

a small spacecraft, the electric propulsion thruster, the unified platform, methods of design researches.