Abstract
Electric pump systems are increasingly being considered as an alternative to turbopumps in liquid rocket engines. Interest is driven by the potential for reduced dry mass and increased system efficiency. This systematic review analyzes 89 peer‐reviewed publications from 2008 to 2025. The applicability limits of EPS architecture are defined based on normalized metrics that ensure comparability of results. Sources were selected through a systematic search of leading scientific databases in accordance with the PRISMA procedure. The “battery‐to‐thrust ratio” indicator was introduced for interarticle comparison. A reduction in the “dry” weight of the engine by 0.23–0.46 kg/kN in the thrust range of 10–100 kN is shown, mainly due to the elimination of the hot turbomachine and a reduction in the number of high‐temperature and mechanically loaded components. The current level of EPS already meets the requirements of light and medium launch vehicles. Further development is linked to an increase in the specific energy of batteries to 600 W·h/kg, the improvement of cryogenic heat dissipation solutions, the qualification of large‐sized products manufactured using additive manufacturing techniques, and the bench validation of multiphysical digital twins. The implementation of these areas will accelerate the transition to serial EPS engines and expand the possibilities for creating reusable and more environmentally friendly rocket systems.