Estimation of the required thrust impulse for small spacecraft (SSC) control system with a propulsion system using fuel gas components

The subject of research is a small weight and size spacecraft (LSC) equipped with a perspective oxygenhydrogen propulsion system on the basis of water electrolysis and low thrust engine (LTE) using H_2Г+O_2Г gas components. Estimation of the required thrust impulse for performing of LSC transition maneuver from the injection to the working orbit, correction of the orbital altitude and LSC submersion maneuver in the target area of the World ocean is presented. Numerical values of thrust impulse estimation for the given inertial-mass parameters of LSC are given.