Comparative Analysis of the Propulsion System Mass for a Small Space Tug

Abstract

The paper considers a problem in designing a small space tug for provision of peripheral launch services during a cluster launch of satellites using a medium or heavy class launch vehicle. Objective of this work is to compare, according to the minimum mass criterion, two types of the chemical propellant propulsion systems for a small space tag. They include those using the self-displacing gaseous components and the liquid components displaced by the boost gas. Mass simplified analytical mathematical models are considered, they are taking into account features of the propulsion system under consideration. Difference in the system mass related to the space tag total mass was studied. Various combinations of the propellant components and various values of the rocket engine specific impulse were analyzed. The paper shows that using an engine on the gaseous components in a small space tug with small reserves of the space tug characteristic velocity provides a gain in the propulsion system mass. In the absolute terms, the mass gain turns out to be insignificant, i.e., approximately 5 % of the space tug starting mass. Thus, when selecting an engine for a small space tug, it is necessary to take into account the following propulsion system characteristics: ecological friendliness of the fuel components, development and operation costs, reliability

The work was carried out as part of the Development program for the advanced engineering school "System Engineering in Rocket and Space Technology" at the Bauman Moscow State Technical University

Please cite this article in English as:

Shcheglov G.A., Shapovalov A.V. Comparative analysis of the propulsion system mass for a small space tug. Herald of the Bauman Moscow State Technical University, Series Mechanical Engineering, 2024, no. 2 (149), pp. 134--157 (in Russ.). EDN: TJLHSA

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