Standardization and technical regulation involve the digitization of international and regional standards into "smart" standards, introducing new requirements for the presentation of complex industrial manuals. The introduction of artificial intelligence and machine learning into the process of standardization, improving process automation, data analysis will provide an opportunity to create innovative standards. Creation of machine-readable standards and their presentation in the form of a database will contribute to better interoperability between systems. The article demonstrates the method of ontological engineering for the automation of partial methodological examination of documents in accordance with the National Standardization Plan. As part of the experiment, an independent tool was developed, based on the extraction of qualitative data, using an uncontrolled automatic keyword extraction algorithm. The algorithm does not require the creation of a learning corpus, can be applied to any text and language, and does not have limitations on the amount of processed data. The algorithm provides adjustment of the parameters of the repetition of keywords, with the possibility of taking into account less important keywords. The work presents the following components: model classification standards, essence extraction module, categorization, thesaurus formation, monitoring and analysis. Calculations were carried out using formalization, determination of the target function, establishment of similarity measures, and description of document features. The work presents the theoretical aspect of application, design and description of the functional system.

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.

Electric pump-fed liquid rocket engines require coordinated propellant delivery under coupled hydraulic, electrical, actuator, and thermal constraints. This study develops an integrated reduced-order model of a dual-channel electric pump-fed propellant system, including the battery and DC bus, power converters, two independently driven motor–pump units, hydraulic feed lines, control valves, combustion chamber, and thermal states. A hierarchical constrained multi-criteria supervisory controller is formulated to regulate chamber pressure, oxidizer-to-fuel mixture ratio, feed-channel coordination, electrical loading, and thermal response. Performance is compared with a conventional PI controller and an enhanced PI configuration incorporating feedforward and disturbance compensation under nominal, degraded, long-duration, and constraint-active scenarios. Relative to the baseline PI controller, the proposed controller reduced the startup pressure peak from 2.64 to 2.32 MPa, pressure RMSE from 0.016 to 0.006 MPa, and mean branch synchronization error from 0.112 to 0.028 MPa. The minimum battery voltage increased from 87.0 to 90.4 V, while the peak motor current decreased from approximately 88 to 65 A. In the 1800 s thermal case, the maximum fuel-drive temperature decreased from approximately 104 to 74 °C. Numerical verification and comparison with published experimental benchmarks supported the physical plausibility and equilibrium-scale behavior of the reduced-order model, while differences in absolute transient time scales limit its use for quantitative prediction of hardware transient dynamics. The results indicate improved coordinated control within the investigated operating envelope and support the use of the framework for comparative system-level assessment and preliminary design of small-class electric-pump propulsion systems.

This article presents a constraint-aware multiparameter methodology for mass optimization and volume assessment of an electric-pump feed system (EPFS) for a liquid-propellant rocket engine. Preliminary EPFS sizing must account for coupled battery energy and peak-power limits, electrical-distribution mass, and thermal feasibility across operating conditions. The proposed framework combines component-based mass estimation with DC-bus-dependent distribution sizing, motor–inverter thermal screening, and preliminary core hardware-envelope volume assessment across prescribed thrust and burn-duration scenarios. Particular attention is paid to the combined consideration of the energy and power limitations of the battery pack, which allows for determining the transition between power-limited and energy-limited modes. Additionally, the model treats battery peak-power capability and motor–inverter thermal admissibility as feasibility constraints, while the total EPFS mass is used as the primary launch-oriented objective. The results demonstrate that the governing EPFS limitation changes with operating duration, transitioning from peak-power-controlled battery sizing to energy-controlled sizing and ultimately to the subsystem mass constraint. For a 25 kN, 120 s scenario, the minimum-mass configuration identified within the evaluated design set yielded model-predicted reductions of 47.4% in EPFS mass and 47.1% in estimated core hardware-envelope volume relative to the adopted baseline. The methodology provides a quantitative basis for preliminary EPFS configuration screening, mass minimization, and core-hardware packaging assessment, subject to design-point efficiency assumptions and simplified thermal and volumetric models.

This article discusses the development of a control system for an electric propellant pump for a light-lift launch vehicle. The relevance of this work stems from the need to create compact and energy-efficient propellant supply systems capable of ensuring stable operation within the weight, size, and energy resource constraints of onboard equipment. The research object is presented as a single electromechanical-hydraulic system comprising an electric drive, a pump unit, a hydraulic circuit, and a digital control system. A mathematical model of the electric pump unit is developed, its numerical parameterization is performed, and a cascade control structure with a feedforward channel is proposed. A series of computational experiments are conducted, including an analysis of transient processes during pressure target changes, a study of the system’s response to hydraulic disturbances, and a robustness assessment under parameter uncertainty. It is established that the proposed control system provides higher response speed, a smaller integral control error, and better resistance to external disturbances compared to a classical cascade PI structure. The obtained results confirm the potential of the proposed approach for electric pump units for fuel supply of ultra-light launch vehicles.