Efficiency of using electric propulsion engines for the task of keeping in a near-circular orbit

Abstract

The paper deals with the problem of choosing the type and the main design parameters of the correcting propulsion system of spacecraft functioning in low near-circular Earth orbits. The efficiency of using chemical (impulse) and low-thrust electric propulsion engines is analyzed. Analytical relations for calculating spacecraft design parameters and specifying the areas of efficient use of electric propulsion engines are obtained for the criterion of useful load fraction and the assumption of constant power dependent acceleration. The results of calculating the areas of efficient use and design parameters of spacecraft for various operational altitudes are shown.

Keywords

• spacecraft
• electric propulsion engine
• useful load fraction
• characteristic velocity
• ballistic coefficient
• design parameters
• total resource