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

Abstract


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+O 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.


About the authors

B. A. Titov

Samara State Aerospace University

Author for correspondence.
Email: oupt_ssau@mail.ru

Russian Federation

Doctor of technical sciences, professor
Head of the department of transportation organization and management

I. V. Koltsov

Samara State Aerospace University

Email: kolt2721@gmail.com

Russian Federation

Assistant of the department of transportation organization and
management

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