Comparative analysis of the small upper stages implementation schemes

Abstract

This article is devoted to a review of existing small upper stages, including
perspective upper stages under development or testing, actively used in the tasks of launching small spacecraft into target orbit, the relevance of which has recently been increasing against the background of the trend of miniaturization of spacecraft and, consequently, the reduction of
payload mass. The paper considers the main classification features of upper stages, including mass, type of propulsion system, design and layout schemes. In particular, the advantages and disadvantages of the above schemes are discussed in terms of layout flexibility, design weight,
manufacturability, ease of assembly, and operational reliability. A comparative analysis between them is given for such key parameters as thrust developed by the propulsion system, the mass of the payload to be launched to the target orbit, and the method of propellant supply. The peculiarities of the use of single-component and two-component fuel are also considered, as well as the influence of fuel pair selection on the efficiency and safety of the upper stage. The purpose of this study is to select and justify a scheme for the realization of a small upper stage combining optimal technical characteristics, high reliability, economic efficiency and environmental safety. The key element of scientific novelty is the application of a multi-criteria analysis method to evaluate various designs for small upper stages. This method allows formalizing and balancing conflicting engineering criteria, including mass efficiency, specific impulse, multiple firing capability, technological maturity, etc.